text:
Based on 5 reviews
Help make it easier for other Avvo users to choose the right lawyer by sharing your experience with this attorney. It's fast, simple, and safe.
Lawyers: Use the Peer Endorsements section to provide input about other attorneys.
Michael is my attorney and represented me in my divorce proceedings. He patiently explained Massachusetts Law to me. He also guided me through the whole process resulting in a divorce last fall. I recommend him to you if you are contemplating a divorce.
Attorney Michael Franklin recently represented me in court when another party was trying to get permanent guardianship of my child. He returned phones calls and emails very quickly. Michael was also very professional. He had less than an hour to help me prepare to testify and feel comfortable in any possible situations I might face. We won that day! I have my son back and couldn't be more grateful. I highly recommend Michael he was a pleasure to work with.
May 25, 2012
Attorney Michael Franklin represented me when I sought custody of my teenage daughter. Her mother had physical custody of her for fourteen years and was her primary caretaker. I had never been married to her mother. Therefore, I knew this fight was going to be an uphill battle.
I have dealt with several other attorneys through the years. However, Michael's knowledge of the law and experience allowed him to navigate the legal system in a manner that was unmatched. He was up front with me from the beginning about what my chances were and about the time and effort that would be needed to see this through. He was a true professional every step of the way and was completely committed to the case. He promptly returned every call I made to him and made himself available after hours and on weekends. He took a genuine interest in the case and the well being of my daughter.
My case went all the way to trial. Michael spent a great deal of time with me in preparation for trial. He knew the facts of my case as if he lived them. He made sure I was familiar and comfortable with all possible situations prior to testifying. This allowed me to express myself appropriately while on the stand and ensured that my side of the story was properly told. Michael remained focused and on point throughout the two day trial. Michael actually forced my daughter's mother to admit acting inappropriately towards my daughter and made her star witness appear foolish.
Thanks to Michael's hard work, dedication and meticulous attention to detail, we won the day. I now have physical custody of my daughter and the future looks bright. I will always be grateful to Michael.
I highly recommend Attorney Michael Franklin. He's a man of integrity and a true credit to his profession.
James F.
Attorney Michael Franklin handled my case very professionally. He is very passionate about the law and his clients. He is extremely adept in the court and settling cases. He tries to settle cases with minimal impact to the client. I would strongly refer him to any of my friends and family. I am extremely pleased with his work.
Not only was the outcome better than I expected, I was impressed by Michael's work. I have worked with many lawyers in the past, and most of them have left me feeling frustrated. Not only did he keep me well informed with letters and copies of all correspondence, Michael returned every call I made to him within hours. I would recommend Michael to anyone I know!"


text:
Furmanite Corporation Reports First Quarter 2011 Results
Furmanite Corporation (NYSE: FRM) today reported results for the quarter ended March 31, 2011. Revenues were up 10% to $73.1 million, compared with $66.4 million for the first quarter 2010. Net income for the quarter increased to $4.0 million after net-of-tax restructuring costs of $89,000 and an income tax benefit of $1.2 million related to the SLM acquisition. This compares with net income for the prior year first quarter of $391,000, which included net-of-tax restructuring costs of $1.6 million. Foreign currency fluctuations favorably impacted the company's first quarter 2011 revenues, operating income and net income by approximately $1.7 million, $176,000 and $68,000, respectively, for the quarter. Earnings per share (diluted) were $0.11, or $0.08 excluding the acquisition related tax benefit in the quarter. This compares with first quarter 2010 earnings per share (diluted) of $0.01.
"Our first quarter performance confirms the progress we anticipated as a result of the restructuring initiatives we substantially completed last year. We benefited from a $6.6 million improvement in revenues and a $745,000 reduction in sales, general and administrative expenses, exclusive of restructuring costs, when compared with the first quarter last year. Those expenses as a percentage of revenue continue to move downward from 2010, and are substantially below 2009 levels," said Charles R. Cox, chairman and CEO of Furmanite Corporation.
Mr. Cox continued, "This improvement is primarily the result of actions we have taken to impact the variables we control. On a global basis, we have not yet seen a consistent pattern of improvement in our markets from the tough conditions we experienced throughout 2009 and 2010. Although we are encouraged by early signs of improvement in some regions and industries we serve, we are taking nothing for granted. We remain focused on doing what is absolutely within our control to maximize our performance and profitability, no matter how dynamic or challenging future markets may prove to be. With our cost structure now balanced to our revenues, we continue a relentless drive to improve customer service, execution fundamentals, organizational effectiveness and marketing outreach, while embedding the culture change needed to support our long term success. These objectives are among our top priorities as we move beyond the turnaround of Furmanite in 2010 to the fundamental transformation needed to assure significant and sustainable future growth. Our first quarter results simply indicate we are doing the right things and moving in the right direction."
Select the service that is right for you!COMPARE ALL SERVICES
Action Alerts PLUSTry it NOW
Jim Cramer and Stephanie Link actively manage a real portfolio and reveal their money management tactics while giving advanced notice before every trade.
Product Features:
- $2.5+ million portfolio
- Large-cap and dividend focus
- Intraday trade alerts from Cramer
- Weekly roundups
TheStreet Quant RatingsTry it NOW
Only $49.95/yr
Access the tool that DOMINATES the Russell 2000 and the S&P 500.
Product Features:
- Buy, hold, or sell recommendations for over 4,300 stocks
- Unlimited research reports on your favorite stocks
- A custom stock screener
- Upgrade/downgrade alerts
Stocks Under $10Try it NOW
David Peltier, uncovers low dollar stocks with extraordinary upside potential that are flying under Wall Street's radar.
Product Features:
- Model portfolio
- Stocks trading below $10
- Intraday trade alerts
- Weekly roundups
Dividend Stock AdvisorTry it NOW
Jim Cramer's protege, David Peltier, identifies the best of breed dividend stocks that will pay a reliable AND significant income stream.
Product Features:
- Diversified model portfolio of dividend stocks
- Alerts when market news affect the portfolio
- Bi-weekly updates with exact steps to take - BUY, HOLD, SELL
Real Money ProTry it NOW
All of Real Money, plus 15 more of Wall Street's sharpest minds delivering actionable trading ideas, a comprehensive look at the market, and fundamental and technical analysis.
Product Features:
- Real Money + Doug Kass Plus 15 more Wall Street Pros
- Intraday commentary & news
- Ultra-actionable trading ideas
Options ProfitsTry it NOW
Our options trading pros provide daily market commentary and over 100 monthly option trading ideas and strategies to help you become a well-seasoned trader.
Product Features:
- 100+ monthly options trading ideas
- Actionable options commentary & news
- Real-time trading community
- Options TV

subset: commoncrawl


text:
Lolly 3 Drawer Dresser ChangerPrice: $399.00
Adding charm and grace to the modern nursery, the Lolly 3-Drawer Dresser Changer provides practical storage and functionality. Natural curves, delicate feet, and simple drawer pulls come together to create Lolly's minimal style. A removable changing tray allows Lolly to grow and change as needs change. Drawers open and close smoothly thanks to the metal drawer glides with stop mechanisms. The anti-tip kit provides additional safety once baby begins exploring. A perfect partner for the Lolly 3-In-1 Convertible Crib, the Lolly 3-Drawer Dresser Changer is a playful addition to the modern home.
Product Features:
- Removable changing tray with two smaller compartments for storage
- Three drawers
- Anti-tip kit included
- Metal glide hardware with stop mechanisms
- Multi-step staining and painting process
- Made from sustainable New Zealand Pine and CARB II Compliant MDF
- Non-toxic finish, lead and phthalate free
- Max Weight: 30 lbs.
NoteChanging pad not included. Recommend Contour Changer Pad
Material(s): 100% Sustainable New Zealand pine wood, CARB II Compliant MDF
Dimensions: 33.5"D X19.13"D X37.75"H
Manufacturer: Babyletto
Babyletto: Sustainable, Safe, Modern Nursery Furniture
Founded in 2010, Babyletto set out to open hearts and spark imagination with their fun and functional children's furniture. With sustainability and longevity at the heart of each design, Babyletto focuses on quality pieces that grow and change right along with the family.
Taking safety seriously, Babyletto incorporates sustainable New Zealand pine, lead and phthalate free finishes, and CARB II compliant MDF into their designs, to create safe and sustainable furniture. Maintaining long-standing partnerships with the same two factories, Babyletto is able to control quality and keep the focus on eco-friendly manufacturing. However, their efforts do not stop there. Babyletto's commitment to the earth extends beyond the factory with solar panels, electric vehicle charging stations, and aggressive recycling programs at all their production and administrative facilities.
Notable for award winning designs, commitment to sustainability and clean, modern aesthetic, Babyletto's designs capture a feeling of unbridled delight and a sense of wonder.View other products from Babyletto


text:
RICH Club Presents:
The Fix-It Panel featuring Alan Hernandez with White Picket Realty, Brian Spitz with Big State Home Buyers and Ray Sasser with Race Management and former RICH Club president.
The discussion will center on your deals and how each would handle the issues and problems that pop-up in structuring deals and resolving issues that occur at each step of the transaction. If you are working on a deal and have hit a roadblock, come Saturday to get ideas on resolving the issue.
RICH Deal-A-Minute will be featured in the morning segment. Bring your deals and don't be late or you'll miss the property that you've been waiting for.
It doesn't matter where you are in your real estate investing, there's something for everyone at RICH. Come and network to Find Your Niche at RICH. Main Event and Trade ShowRICH Club Headquarters 8:30 a.m. – 9:00 a.m. – Registration, coffee & networking 9:00 a.m. - 12:00 p.m. - General Meeting All members and guests welcome! First time guests are free, $30 otherwise.
Disclaimer Notice Speaker presentations and literature distributed during the meeting have not been reviewed or approved in advance by the Board of Directors, and they offer no endorsement of any material, person or idea presented. You are encouraged to do your own research and due diligence regarding any ideas and concepts you hear today. You should always consult with your own professional advisors before making any investment.
8:30 - 9:00 am
Registration, Networking & Trade Show
Guests are invited to attend one General Meeting free of charge. Otherwise, it''s $30.
9:00 am - 12:00 pm
General Session & Presentations
1:30 pm - 4:30 pm
Special Afternoon Session
Guests are invited to attend one Afternoon Session free of charge.
Directions & Map RICH Conference Center 4220 Lockfield Street Houston, TX 77092 713-947-7424
Directions & Map
We will see you on Saturday at 8 A.M.! Be sure to pass this information to your fellow guests, friends and family members!
Member of NationalREIA


text:
A study to be published in the upcoming issue of the journal Learning and Individual Differences explored the relation between personality and homework behavior. Yes, of course, procrastination is a key variable here, and personality does make a difference in students' homework behavior and academic achievement.
Although cognitive ability is the key predictor of grades and overall academic performance, personality also plays a role. The question that researchers explored in this study was how personality affects academic performance. Their basic hypothesis was that the effects of personality on academic performance are mediated by homework behavior. For example, someone who is not very conscientious in terms of personality (lacking a sense of self-discipline, orderliness and need for achievement) would be less likely to do his or her homework, and this would negatively affect grades. In fact, previous research indicates that the personality trait of conscientiousness is the strongest personality predictor of academic performance (as important as cognitive ability in terms of prediction), and it's also a strong predictor of success in the work place.


text:
To embed, copy and paste the code into your website or blog:
[co-author: Chris Elliott]
The EU's Observatory on Infringement of Intellectual Property Rights has launched a survey on the protection and enforcement of intellectual property rights in third countries.
The survey, which runs until 10 June 2014, will collect information in order to identify difficulties encountered by EU entities in enforcing their IPR rights in non-EU countries and will be used by the European Commission in negotiations with third countries over better protection for EU entities' intellectual property rights. EU businesses and IP professionals are invited to participate – complete the survey here.
Topics: EU, Inter Partes Review Proceedings, Patent Infringement, Patents
Published In: Intellectual Property Updates, International Trade Updates
DISCLAIMER: Because of the generality of this update, the information provided herein may not be applicable in all situations and should not be acted upon without specific legal advice based on particular situations.
© DLA Piper - Sports, Media and Entertainment
Read fresh new writing on compliance, cybersecurity, Dodd-Frank, whistleblowers, social media, hiring & firing, patent reform, the NLRB, Obamacare, the SEC…
…or whatever matters the most to you. Follow authors, firms, and topics on JD Supra.
Create your news brief now - it's free and easy »
One legal practice has emerged as the first choice among all parties involved in the sports, media...
View Profile »
See more »
Back to Top
Copyright ©


text:
Serving your area
Serving your area
Serving your area
Serving your area
We Take The Con Out Of Contracting A New Roof! Custom Design and Build from the Ground Up!
Serving your area
Your One Stop Garage Door Shop!
Serving your area
Let our Sales Project Consultants show you the benefits and features of Sears Replacement Windows. Call or Schedule your FREE in-home consultation tod... more.
15067 Bilger Road,, Mount Union, PA 17066
Security Doors & Windows. Update or Improve Your Home Now!
2350 Sollenberger Road,, Chambersburg, PA 17202
Security Doors & Windows. Get an Profile Info, Estimate & More!
259 Burnhill Road,, Shermans Dale, PA 17090
Window Repair & Replacement. Get Estimates, Profile Info & More!
Serving your area
16.1 Miles
(717) 480-2856
Serving New Bloomfield, PA
Products: Safety Covers
Services: Serving All Of Perry County!, Liner Replacement, Renovations, Restoration, Service & Repair, Eq...
Latest review: "I would hire Mike The Pool guy again and I highly recomend his services for a pool liner rep..."
28.0 Miles
(570) 374-1042
1491 Sportsmans Dr, Middleburg, PA 17842
Latest review: "The company name is not correct. It should read Aurand's Machinery and Automation LLC. I h..."
27.3 Miles
(717) 243-0930
812 N Hanover St, Carlisle, PA 17013
Products: Brakes, Transmissions
Services: For All Your Automotive Needs, Complete Brake Service & Repair, State Inspections & Emissions...
Latest review: "Steve's is the best repair shop in the area, without exception. Honesty, fast and reliable s..."
10.9 Miles
(717) 248-6312
838 W 4th St Ste E, Lewistown, PA 17044
Products: Electrical Supplies, Hardware, Lawn & Garden Supplies, Locks, Paints, Plumbing Supplies, Screen...
Services: Windows Repaired (storm & Screen)
Latest review: "Love the store . Great prices but can't fine store hours anywhere online on website. Hate th..."
28.6 Miles
(814) 237-0368
3280 W College Ave, State College, PA 16801
Products: New Cars, Sedans, Used Vehicles
Services: Locator Services
Latest review: "I was treated fine until the sale was final then I was given the run around by sales associa..."
28.7 Miles
(814) 234-4444
605 University Dr, State College, PA 16801
Products: Accessories, Brakes, Engines & Engine Parts, Exhaust Systems, Gasoline, Snacks, Sport Bikes
Services: Balancing, Cars, Domestic, Electrical, Exhaust, Foreign, Inspections, Maintenance, Motorcycles...
Latest review: "These people are theives. Stay away from them... They will on purposely mess your car up so ..."
.7 Miles
(717) 436-8981
3162 William Penn Highway, Mifflintown, PA 17059
Products: Energy Efficient, High Quality Windows, Sales
Services: Svc, Repairs
8.3 Miles
(717) 438-3671
7220 Veterans Way, Ickesburg, PA 17037
.5 Miles
(717) 436-9450
39 Cedar St, Mifflintown, PA 17059
8.2 Miles
(717) 438-3671
7220 Veterans Way, Ickesburg, PA 17037
11.8 Miles
(717) 437-9204
2 Scenic Dr, Lewistown, PA 17044
11.0 Miles
(717) 363-8892
15 Rothermel Dr, Yeagertown, PA 17099
10.0 Miles
(717) 674-4242
3 W Market St, Lewistown, PA 17044
Products: Windshield Replacement, New Windshield, Auto Glass Repair, Car Glass Repair, Door Glass Repair...
Services: Windshield Replacement, New Windshield, Auto Glass Repair, Car Glass Repair, Door Glass Repair...
1.2 Miles
(717) 436-2522
8 Industrial Cir, Mifflintown, PA 17059
Copyright 2014 Local Corporation - US Patent Number 7,231,405. - Privacy Policy - Terms of Service
Some data provided by Acxiom.


text:
Inventors list
Assignees list
Classification tree browser
Top 100 Inventors
Top 100 Assignees
Subclass of:
415 - Rotary kinetic fluid motors or pumps
Patent class list (only not empty are listed)
Deeper subclasses:
|Class / Patent application number
|Number of patent applications / Date published
|Working fluid on at least one side of heat exchange wall
|Cooling fluid contacts shaft, seal or bearing
|FAN AND IMPELLER THEREOF - A fan includes a frame, a motor and an impeller. The motor is disposed on the frame and coupled to the impeller to drive the impeller to rotate. The impeller includes a hub, a plurality of blades and an air exhausting structure. The hub has an opening formed on a top portion of the hub. The blades are disposed around the hub. The air exhausting structure is disposed in the opening for discharging hot airs generated by the motor out of the hub.
|Engine with intake air temperature control system - A gas turbine engine system includes a gas turbine engine using vaporized liquefied gas as fuel. The gas turbine engine is configured to ingest intake air from an intake port and direct exhaust gases to an exhaust port. The gas turbine engine system also includes a heat exchanger with a heat transfer fluid therein. The heat exchanger is configured to create at least a part of the fuel by heating the liquefied gas. The gas turbine engine system also includes an intake air temperature control circuit. The intake air temperature control circuit includes conduits configured to direct the heat transfer fluid to the intake port and the exhaust port. The gas turbine engine system also includes a control system configured to selectively direct the heat transfer fluid to one of the intake port and the exhaust port.
|TURBINE OR COMPRESSOR STAGE FOR A TURBOJET - A turbojet turbine or compressor stage, comprising at least one rotor disk mounted inside a sectorized ring (
|Thermal Shield at Casing Joint - A thermal shield for reducing thermal stress induced proximate to a first joint formed between adjacent engine casing components in a gas turbine engine. The thermal shield includes a cover structure for covering a radially inner portion of at least one of the engine casing components. The cover structure is disposed proximate to the first joint and attached to the respective engine casing component so as to limit exposure of a covered inner portion of the engine casing component to hot gases in an interior volume defined by the engine casing components. A thermally insulating layer is disposed between the cover structure and the engine casing component for effecting a reduced amount of heat transfer to the covered inner portion of the engine casing component from the hot gases in the interior volume defined by the engine casing components.
|TURBINE CASING WITH FALSE FLANGE - A turbine casing may include an outer surface with a false flange and an inner surface with a heat sink positioned adjacent to the false flange.
|EXHAUST-GAS TURBOCHARGER - The invention relates to an exhaust-gas turbocharger (
|Delivery Pump - A delivery pump for conveying a liquid between a pump inlet and a pump outlet, the pump being constructed as a single-stage centrifugal pump with a radial impeller (
|Component with a Protective Layer - The invention relates to a component having a substrate and a protective layer, which consists of an intermediate NiCoCrAlY layer zone on or near the substrate and an outer layer zone which is arranged on the intermediate NiCoCrAlY layer zone, which is characterized in that the intermediate NiCoCrAlY layer zone comprises of (in wt %): 11-13% Co, 20-23% Cr, 10.2-11.5% Al, 0.3-0.5 Y, 1.0-2.5% Re and Ni balance.
|GAS TURBINE ENGINE MOUNTING ARRANGEMENTS - A clamp suitable for use in an anti-icing system of a gas turbine engine is provided is disclosed. The clamp has a clasping portion for clasping a heating element. Two resilient arms extend from the clasping portion to a substantially rigid outer collar. Translational movement of the clasping portion, which may be created by radial expansion of an annular heating element being clasped thereby, can be accommodated by the clamp by elastic deformation of the resilient arms. This allows radial expansion of the heating element to be accommodated without relative rotation between the clasping portion and the heating element.
|STEAM TURBINE - A steam turbine (
|Screw Compressor - A screw compressor includes a compressor body and a shell and tube heat exchanger for cooling of a compressed air discharged from the compressor body. A tube provided in the shell and tube heat exchanger has both ends each having a cylindrical shape, and a center part formed as a multi-lobate tube to have a corrugated shape with crest portions and trough portions alternately arranged in a circumferential direction. The multi-lobate tube provided at the center part of the tube is formed to have a multi-lobate spiral shape through twisting. Size reduction of the shell and tube heat exchanger may make the screw compressor compact as a whole.
|TURBINE VANE OF A GAS TURBINE - A turbine vane of a gas turbine, especially a gas turbine aircraft engine, is disclosed. The turbine vane includes a vane base body with an outer surface forming a suction side and a pressure side, the outer surface of the vane base body being at least partially coated with a thermal barrier coating. The thermal barrier coating extends continuously or uninterruptedly at least largely over the suction side and largely over the pressure side of the surface of the vane base body, with the layer thickness of the thermal barrier coating being variable or adjustable.
|HEAT SHIELD AND TURBOCHARGER HAVING A HEAT SHIELD - A heat shield, in particular for a turbocharger, has a disk or a pot shape which is stepped once or multiple times. The disc or pot shape has an outer edge, and the outer edge is provided with at least one opening section. The opening section forms a web section with the outer edge, said web section being bent outward in order to form a spring arm. The web section is either designed as closed or as open at one point.
|BLOWER APPARATUS - The invention relates to a blower apparatus with an electric motor, which drives a blower wheel, is arranged in a motor housing and has a commutator with at least two brushes, which form in each case an associated brush bearing face with respect to the commutator, wherein a cooling air flow for cooling the electric motor is diverted into a cooling air channel of the motor housing by a blower air flow produced by the blower wheel. The invention is based on the object of designing the motor cooling system of the blower apparatus of the generic type in such a way that it is more efficient. The object is achieved by virtue of the fact that the cooling air channel has an air distributor, which splits the cooling air flow into at least two cooling air subflows, which are in each case supplied to one of the brush bearing faces directly and in targeted fashion.
|CMC VANE INSULATOR AND METHOD OF USE - A method for assembling a gas or steam turbine is provided. The method includes providing an insulator and positioning the insulator between a vane support and a vane such that the insulator facilitates preventing hot gas migration into the vane, and such that during operation, hot gas is channeled from a high pressure side of the vane to a low pressure side of the vane. A vane assembly for a turbine rotor assembly is also provided. The vane assembly includes a vane support and an insulator including a projecting portion. The assembly also includes a vane. The insulator is coupled to the vane support such that the projecting portion is between the vane and a nozzle support strut to facilitate hot gas flow from a pressure side of the projecting portion to a suction side of the projecting portion.
|Use of a Thermal Barrier Coating for a Housing of a Steam Turbine, and a Steam Turbine - The invention relates to the use of a thermal insulating layer for a housing of a steam turbine in order to even out the deformation behaviour of different components based on different heatings of the components.
|COOLING SYSTEM OF RING SEGMENT AND GAS TURBINE - A cooling system of ring segment is provided with: a collision plate that has a plurality of small holes; a cooling space that is enclosed by the collision plate and a main body of the segment body; a first cavity that arranged is the upstream end portion of the segment body in the flow direction of the combustion gas so as to be perpendicular to the axial direction of a rotating shaft; a first cooling passage that communicates from the cooling space to the first cavity; and a second cooling passage that communicates from the first cavity to a fire combustion gas d gas space in the downstream end portion of the segment body in the flow direction of the combustion gas.
|TEMPERATURE CONTROL RING FOR VEHICLE AIR PUMP - An annular device for the temperature control of a pump is provided. That device is in fluid communication with the radiator coolant system of a vehicle, and the engine-warmed coolant flows through the annular device to warm the pump and thaw ice buildup. The device is removable and can be added on to an existing pump without any redesign of the existing pump housing.
|INSULATING A CIRCUMFERENTIAL RIM OF AN OUTER CASING OF A TURBINE ENGINE FROM A CORRESPONDING RING SECTOR - A turbine stage of a turbine engine, the stage including a rotor wheel mounted inside a sectorized ring carried by an outer casing, the outer casing including at least a circumferential rim housed in an annular cavity to attach a downstream end of the ring sector. A bottom wall of the annular cavity of the ring sector remains radially spaced apart from the circumferential rim of the outer casing to provide a thermally insulating space between them and includes a radial positioning mechanism acting on the circumferential rim.
|Turbine Airfoil With Dual Wall Formed from Inner and Outer Layers Separated by a Compliant Structure - A turbine airfoil usable in a turbine engine with a cooling system and a compliant dual wall configuration configured to enable thermal expansion between inner and outer layers while eliminating stress formation is disclosed. The compliant dual wall configuration may be formed a dual wall formed from inner and outer layers separated by a compliant structure. The compliant structure may be configured such that the outer layer may thermally expand without limitation by the inner layer. The compliant structure may be formed from a plurality of pedestals positioned generally parallel with each other. The pedestals may include a first foot attached to a first end of the pedestal and extending in a first direction aligned with the outer layer, and may include a second foot attached to a second end of the pedestal and extending in a second direction aligned with the inner layer.
|Component of a Steam Turbine Plant, Steam Turbine Plant, Application, and Production Method - The aim of the invention is to provide a superheated component of a steam turbine installation with high thermal and mechanical resistance. To this end, the component comprises a lining applied to a body of the component, on a hot side facing a steam chamber, said lining being adapted to the contour of the component body. According to the invention, the lining comprises a number of moulded parts, each moulded part comprising a metallic and ceramic composite layer formed from at least one metallic layer and at least one ceramic layer. The ceramic layer is used especially as a insulating layer, and the metallic layer is especially used as a support or for protection against abrasion and/or erosion.
|Cooling Fan with Oil-impregnated Bearing - A cooling fan with oil-impregnated bearing includes a base portion, a bearing, a fan hub, and a coil assembly. The base portion has a forward extended bearing housing, into which the bearing is tightly fitted with a colloidal material applied between them. The fan hub is mounted on and around the bearing housing, and has a rearward extended rotary shaft extended through a centered shaft hole of the bearing. An oil receiving space is formed on a wall of the shaft hole at a predetermined position. The coil assembly is externally tightly fitted around the bearing housing with a colloidal material applied between them. With the colloidal material, the bearing and the coil assembly can be associated with the bearing housing without detriment to the effective porosity of the bearing and the dimensional precision of the bearing housing. The oil receiving space also prevents the lubricating oil from leaking out.
|TURBINE ENGINE HAVING COOLING GLAND - In one embodiment, a turbine may include a bearing housing for a rotor with a passage along an axis of rotation of the rotor shaft. A cooling gland configured to transfer cooling fluid to the passage may be mounted to the bearing housing with a mounting structure configured to mount the cooling gland substantially in-line with the passage of the rotor.
|SURFACE AREA AUGMENTATION OF HOT-SECTION TURBOMACHINE COMPONENT - An example turbomachine hot-section component protrusion extends away from a base surface of a hot-section component along a longitudinal axis. A radial cross-section of the protrusion has a profile that is non-circular.
|Use of a Thermal Barrier Coating for a Housing of a Steam Turbine, and a Steam Turbine - The invention relates to the use of a thermal insulating layer for a housing of a steam turbine in order to even out the deformation behaviour of different components based on different heatings of the components.
|LINER FOR A TURBINE SECTION, A TURBINE SECTION, A GAS TURBINE ENGINE AND AN AEROPLANE PROVIDED THEREWITH - A liner for a turbine section includes a first wall, a plurality of webs interconnected with and projecting from the first wall, and a plurality of cooling channels, each of the cooling channels being delimited by two adjacent webs and the first wall, wherein each cooling channel presents a height corresponding to the height of its delimiting webs, and a width corresponding to the distance between its delimiting webs. At least one of the cooling channels has a width/height ratio of below 5 or/and the material of the webs has a higher thermal conductivity than the material of the first wall. A turbine section, a gas turbine engine and an aeroplane provided with such a liner are also disclosed.
|Asymmetrical gas turbine cooling port locations - A method is disclosed for improving a turbine's thermal response during transient and steady state operating conditions in which the flow of cooling fluid in the turbine's casing is caused to be asymmetrical relative to the horizontal and vertical symmetry planes of the casing so that the turbine's cooling symmetry planes are rotated relative to its geometric symmetry planes and thereby the heat transfer at locations in the casing with increased mass is increased.
|COOLING SYSTEM FOR A TURBOMACHINE - An embodiment of the present invention may provide an integrated cooling system for multiple compartments of a turbomachine. The cooling system, in accordance with embodiments of the present invention, may provide the following benefits to the user. Improvement on the combined cycle efficiency and an increase in the power output. This may result from reducing the exhaust dilution losses and reducing the parasitic load by requiring fewer air circulation devices. The present invention may also benefit the user by reducing the installation and start-up costs of the cooling system by requiring fewer air circulation devices and integrating the cooling systems. The present invention may circulate a cooling fluid through an integrated cooling circuit, which may be in fluid communication with each compartment of the multiple compartment of the turbomachine.
|COOLED TURBINE BLADE FOR A GAS TURBINE AND USE OF SUCH A TURBINE BLADE - An aspect of the invention is a turbine blade for a gas turbine, comprising a blade root, adjoining which one after the other are a platform region having a transversely running platform and then a blade profile curved in the longitudinal direction, comprising at least one cavity which is open on the root side and through which a coolant can flow and which extends through the blade root and the platform region into the blade profile. The cavity is surrounded by an inner wall, on the surface of which structural elements influencing the coolant are provided. In order to prolong the service life of such a turbine blade, the invention proposes that a section, lying at least in the blade profile and adjoining the platform region, of the surface of the inner wall be free of structural elements. Such a turbine blade can preferably be used in a stationary gas turbine
|HEAT TRANSFER PASSAGE - This invention relates to heat transfer passage (
|PUMP HAVING HEAT-DISSIPATING MECHANISM - A pump includes a DC motor (
|COMBINED FEATHERSEAL SLOT AND LIGHTENING POCKET - A segmented engine component has multiple segments which are connected to each other via a featherseal arrangement. Each of the components has a combined featherseal slot and lightening pocket.
|TURBINE SHROUD SUPPORT THERMAL SHIELD - A turbine shroud assembly includes an annular thermal shield around an annular shroud support. A honeycomb layer is attached to the shroud support along an inner side of the honeycomb layer and a heat shield is attached to an outer side of the honeycomb layer. The honeycomb layer may be brazed to the shroud support and the heat shield may be brazed to the honeycomb layer. A lip may depend inwardly from a forward end of the heat shield and an axial extension may extend beyond an aft end of the honeycomb layer. The thermal shield may be segmented. The shroud assembly may include axially spaced apart first and second stage thermal shields circumferentially disposed around an annular shroud support and may be incorporated in a high pressure turbine including first and second stage shrouds coupled to shroud hangers that are inwardly supported by hooks of the shroud support.
|FAN SHAFT SEAT STRUCTURE - A fan shaft seat structure including a shaft bushing and a heat dissipation member. The shaft bushing has an open end, a closed end and a, connection section. A receiving space is defined between the open end and the closed end. The connection section extends from the closed end in a direction reverse to the receiving space. The heat dissipation member has a first face and a second face. The first face is flush with a first end of the connection section in contact with the closed end of the shaft bushing. The second face is flush with a second end of the connection section. The shaft bushing is integrally connected with the heat dissipation member to increase heat dissipation area and save working time and manufacturing cost as well as achieve better heat dissipation effect.
|SEGMENTED TURBINE RING FOR A TURBOMACHINE, AND TURBOMACHINE FITTED WITH SUCH A RING - The segmented ring has the gaseous hot flow of the turbomachine passing through it and comprises:
|HEAT SHIELD FOR SEALING A FLOW CHANNEL OF A TURBINE ENGINE - A heat shield arrangement for local separation of a flow channel within a turbine engine, with respect to a stator housing radially surrounding the flow channel is provided. The heat shield includes two axially opposite joining contours which are each engageable with two components which are axially adjacent along the flow channel. Each provides a complementary reception contour for the joining contours. At least one of the reception contours has an axial clearance, in which the associated joining contour is axially displaceably mounted. At least one seal is provided between the axially displaceable joining contour and the reception contour. The seal is mounted movably within the reception contour or the joining contour in such a way that the seal is deflectable against a surface region of the reception contour or of the joining contour.
|Coated turbine component and method of coating a turbine component - Turbine components with different types of coatings on different parts thereof are described. The coatings are chosen such that they are especially adapted to the thermal and corrosive conditions being present on the parts of the component during use. A method to coat a turbine component is also described.
|AIR COOLED BUCKET FOR A TURBINE - A bucket for a turbine is described. The bucket includes a dovetail portion configured to couple the bucket to a turbine wheel, the dovetail portion having a lower surface. The bucket also includes a shank portion that extends from the dovetail portion and an airfoil having a root and a tip portion, an airfoil shape, and a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in Table I. The bucket also includes a plurality of cooling passages. The plurality includes no more than five cooling passages that extend between the root and the tip portion of the airfoil. Each of the cooling passages exits the airfoil at the tip portion, the plurality of cooling passages are positioned in a camber line pattern.
|Turbine Airfoil with an Internal Cooling System Having Enhanced Vortex Forming Turbulators - A turbine airfoil usable in a turbine engine and having at least one cooling system. At least a portion of the cooling system may include one or more cooling channels having a plurality of turbulators protruding from an inner surface and positioned generally nonorthogonal and nonparallel to a longitudinal axis of the airfoil cooling channel. The cooling channel may also include a plurality of vortex enhancers protruding from an inner surface forming the cooling channel and positioned nonparallel to the turbulators. In one embodiment, the vortex enhancers may be positioned generally orthogonal to the turbulators. The configuration of turbulators and vortex enhancers creates a higher internal convective cooling potential for the blade cooling passage, thereby generating a high rate of internal convective heat transfer and attendant improvement in overall cooling performance. This translates into a reduction in cooling fluid demand and better turbine performance.
|TURBOMACHINE - A turbomachine is provided. The turbomachine includes a rotor, a stator and a plurality of blade discs mounted on the rotor. The rotor includes a turbulator cylinder where a plurality of turbulators are provided on a curved surface of the turbulator cylinder and the stator includes an annular shroud extending around the turbulator cylinder. The plurality of turbulators increase a heat transfer to a coolant flowing between the adjacent opposed surfaces of the turbulator cylinder and the annular shroud.
|Cooled Turbine Airfoil Fabricated From Sheet Material - A turbine airfoil (
|ANNULAR GAS TURBINE HOUSING COMPONENT AND A GAS TURBINE COMPRISING THE COMPONENT - The invention relates to an annular gas turbine housing component (
|Turbine Vane for a Gas Turbine Engine - A turbine vane for a gas turbine engine having an outer wall of nonuniform thickness. The turbine vane may be formed from a generally elongated airfoil formed from an outer wall having a leading edge, a trailing edge, a pressure side, a suction side, a first endwall at a first end, a second endwall at a second end opposite the first end, and an internal cooling system positioned internally of the outer wall. The outer wall may be formed of a non-uniform thickness such that aspects of the outer wall positioned between an outboardmost portion of the outer wall and an inboardmost portion of the outer wall are thinner than the outboardmost and inboardmost portions of the outer wall.
|HEAT TRANSFER DEVICE IN A ROTATING STRUCTURE - A cooling system includes a moving rotor system which in turn includes: a rotating disk on which a plurality of heat conducting structures are distributed, the heat conducting structures including an inner arrangement of spiral blades; an air flow generating fan element; and an outer arrangement of heat transfer pins distributed along a perimeter of the rotating disk, the heat transfer pins having a high aspect ratio that maximizes a surface area to footprint area; wherein the spiral blades generate a mass fluid flow of ambient fluid toward the heat transfer pins such that the heat transfer pins are persistently cooled.
|Turbine Engine Components with Near Surface Cooling Channels and Methods of Making the Same - A turbine airfoil has an airfoil-shaped core and a skin extending about the outer peripheral surface of the core. The core and/or the skin are configured such that a plurality of cooling channels is formed between them. In one embodiment, the cooling channels are formed by a plurality of radially extending channels in the core. In another embodiment, the cooling channels are formed by providing a wave-shaped skin such that, when the skin is attached to the outer peripheral surface of the core, the cooling channels can be formed in the space between the outer peripheral surface of the core and each wave of the skin. Such airfoil constructions can allow the inclusion of different materials in the airfoil. Further, such constructions can allow greater flexibility in the formation of cooling channels. Moreover, such constructions can help to achieve thinner outer walls and near surface cooling of the airfoil.
|EXTENDED IMPINGEMENT COOLING DEVICE AND METHOD - An extended impingement cooling structure to cool outside an air supply plenum comprises an inner wall; an impingement sheet; a series of supports to maintain the inner wall in spaced relation to the impingement sheet, and a baffle supported between the inner wall and the impingement sheet. The baffle has a collector plenum area that receives impingement cooling air from the air supply plenum and a channel in fluid communication with the collector plenum and extending outside the air supply plenum with openings to allow impingement cooling air to pass therethrough and having a series of lands extending into the channel wherein the lands are located in proximity to impingement cooling air outlets in the inner wall.
|STRUCTURALLY DIVERSE THERMAL BARRIER COATINGS - A coated article includes an article having at least one surface and a thermal barrier coating system disposed upon the at least one surface. The thermal barrier coating system has at least two layers, with each layer having a different microstructure. The microstructure of each layer may be any one of the following: columnar, amorphous, randomized, and splat-like. The thermal barrier coating system typically exhibits a thermal conductivity of no more than 16 BTU in/hr ft
|Processes for the formation of positive features on shroud components, and related articles - A process for the formation of positive features on the surface of a turbine shroud component is described. The process involves applying a feature-forming material to a selected portion of the component surface with a laser consolidation apparatus, according to a pre-selected shape and size for the positive features. A gas turbine engine, comprising a shroud component which contains positive features formed according to embodiments of this process, represents another embodiment of this invention. Methods for modifying the shape of at least one positive feature on a surface of a shroud component are also described.
|DEAD ENDED BULBED RIB GEOMETRY FOR A GAS TURBINE ENGINE - A component within a gas turbine engine includes a dead ended rib which at least partially defines an internal cooling circuit flow path, the dead ended rib defines a bulbed rib profile.
|Apparatus and Method for Reducing the Pressure on a Joint Between at Least Two Delimiting Parts - An apparatus, especially a steam turbine, including a first delimiting part and a second delimiting part is provided. The delimiting parts are attached to one another forming a joint and enclosing at least a part of a first pressure chamber. A shielding element is also provided on the sides of the delimiting parts facing towards the first pressure chamber and is arranged to form a seal completely covering the joint, so that a cavity is formed between the delimiting parts and the shielding element. A line is routed in the cavity connecting the cavity to a second pressure chamber. In addition, a method for decreasing the force acting on a joint, which is formed by the joining together of a first delimiting part and a second delimiting part of an apparatus, especially a steam turbine, and for reducing the attachment forces acting on the joint is provided.
|MIXING FAN - The invention relates to a fan comprising a housing and a fan wheel arranged on a motor shaft and being drivable by a motor. According to the invention, the fan is designed as a mixing fan for transporting and mixing a combustible medium with air, wherein at least the fan wheel is designed in an insulating manner.
|CORE RUNOUT CEILING FOR TURBINE COMPONENTS - A method of closing off a mold plug opening in a turbine component includes the steps of inserting a weld member into an opening to be closed, and to abut a necked portion within a passage leading from the opening. Heat is applied to the weld member, such that a surface of the weld member in contact with the necked portion liquefies, and such that the weld member adheres to the necked portion, closing off the opening. The weld member and application of heat are selected such that the entirety of the weld member does not liquefy, but remains in the opening, without ever having liquefied. A turbine component formed by the method is also disclosed.
|THERMAL CONTROL SYSTEM FOR TURBINES - A thermal control system for a turbine casing (
|GAS TURBINE ENGINE WITH IMPROVED THERMAL ISOLATION - A gas turbine engine includes a housing with a duct wall that defines a generally annular and axially elongated hot gas flow path for passage of combustion gas. The engine further includes a contoured shroud mounted within the internal engine cavity and defining a hot gas recirculation pocket for receiving hot gas ingested from the hot gas flow path through the annular space and for recirculating the ingested hot gas back through the annular space to the hot gas flow path. The contoured shroud includes a base wall extending radially inwardly from the duct wall, an inboard wall extending from the base wall in an axial direction toward the rotor, and an end wall extending from the inboard wall in a radially outward direction. The end wall terminates in a circumferentially extending free edge disposed in proximity to the annular space. The end wall defines an opening.
|HYDRODYNAMISCHE MASCHINE, INSBESONDERE HYDRODYNAMISCHE KUPPLUNG EINES TURBOCOMPOUNDSYSTEMS - A hydrodynamic machine, and especially a hydrodynamic coupling, for a turbine compound system includes (a) a bladed primary wheel and a bladed secondary wheel which together form an operating space which is filled or can be filled with operating medium, and (b) a housing which encloses the primary wheel and the secondary wheel and which is manufactured from sheet metal. The housing is manufactured from at least two separate sheet metal components which are placed on the primary wheel and/or the secondary wheel, are aligned with each other at a joint abutment location and are welded together. In the area of the welded joint abutment, a relief which is open toward the joint abutment is provided and which extends along the joint abutment in the surface of the primary wheel and/or the secondary wheel.
|METHOD AND APPARATUS FOR TURBINE ENGINES - A method for sealing a gas turbine engine includes coupling a turbine bucket to a rotor wheel and forming an interface region therebetween. A cooling air passage is defined in a portion of the rotor wheel and a cooling air manifold is defined in a portion of the turbine bucket. The method also includes inserting a seal tube within at least a portion of the cooling air passage. The method further includes coupling the cooling air passage, the seal tube, and the cooling air manifold in flow communication to at least partially define a turbine bucket cooling system. The method also includes operating the gas turbine engine such that the rotor wheel and the turbine bucket are rotated, thereby inducing a pressure on the seal tube to substantially decrease air flow discharged from the turbine bucket cooling system through the interface region.
|Compressor Clearance Control System Using Bearing Oil Waste Heat - The present application provides a compressor clearance control system for a gas turbine engine having an oil recirculation system with a flow of oil therein and a compressor with a casing and a number of rotor blades. The compressor clearance control system may include a casing heat exchanger positioned about the casing of the compressor and a conduit in communication with the casing heat exchanger and the oil recirculation system so as to heat the casing of the compressor with the flow of oil from the oil recirculation system.
|FILM COOLING STRUCTURE - A film cooling structure
|SYSTEM AND METHOD TO INSULATE TURBINES AND ASSOCIATED PIPING - An insulation system includes at least one turbine insulation compartment configured to enclose at least a portion of a turbine; an insulation storage compartment configured to store a supply of insulation; a plurality of first pipes that connect to the turbine insulation compartment and the insulation storage compartment; and a blower configured to generate a flow of air in at least one first pipe to pneumatically convey insulation between the insulation storage compartment and the at least one turbine insulation compartment. A method of insulating at least a portion of a turbine includes enclosing at least a portion of the turbine in a compartment; and conveying insulation into the compartment.
|PLASMA ENHANCED COMPRESSOR DUCT - A compression system is disclosed, comprising a first compressor having a first flowpath, a second compressor having a second flowpath located axially aft from the first compressor, and a transition duct capable of flowing an airfow from the first compressor to the second compressor, the transition duct having at least one plasma actuator mounted in the transition duct.
|METHOD AND APPARATUS FOR COOLING A TRANSITION PIECE - Disclosed is a compressor discharge can including a transition piece and a flow redirector located about the transition piece, defining an airflow space therebetween, the flow redirector configured to reduce recirculation of flow in the airflow space.
|COOLING STRUCTURE FOR OUTER SURFACE OF A GAS TURBINE CASE - A gas turbine case is provided including an outer case surface, and a channel portion formed as a recessed area extending radially inwardly into the outer case surface. The channel portion extends about a circumference of the case. An outer flow jacket is attached to the outer case surface and extends over the channel portion to define an enclosed cooling passage along the outer case surface. At least one inlet passage and at least one outlet passage are provided in fluid communication with the enclosed cooling passage to convey air to and from the cooling passage.
|VENTILATION OF A DOWNSTREAM CAVITY OF AN IMPELLER OF A CENTRIFUGAL COMPRESSOR - A system for ventilating a downstream cavity of an impeller of a centrifugal compressor in a turbomachine, this cavity being delimited by the downstream face of the impeller and by an annular end-piece of a diffuser and being ventilated by taking air from the outlet of the compressor, the system comprising at least one annular deflector mounted in this cavity in order to oppose the rise of hot air along the downstream face of the impeller and in order to cause the diverted hot air to be driven by the air taken from the outlet of the compressor.
|Method for applying a NiA1 based coating by an electroplating technique - The present invention provides a coated article made using a plating process, either electroless or electrolytic, whereby nickel is plated on the article using a solution that includes a suspension of powders or containing one or more of the following elements: Ni, Cr, Al, Zr, Hf, Ti, Ta, Si, Ca, Fe, Y and Ga. Optionally, the coating is then heat treated at a temperature above about 1600.degree. F. for an effective amount of time to allow to homogenize the coating by allowing effective interdiffusion between the species. The level of aluminum may be altered to produce a coating of the predominantly beta phase of the NiAl alloy composition. Optionally, a TBC layer is applied over the predominantly beta phase NiAl alloy composition metallic bond coat.
|FASTBACK TURBULATOR STRUCTURE AND TURBINE NOZZLE INCORPORATING SAME - A heat transfer apparatus, includes a member defining a wall exposed to fluid flow in a predetermined direction of flow; and a plurality of turbulators disposed on the wall. Each turbulator includes an upright front face which generally faces the direction of flow, and a back face which defines a ramp-like shape tapering from the front face to the wall.
|GAS TURBINE ENGINE HAVING A COOLING-AIR NACELLE-COWL DUCT INTEGRAL WITH A NACELLE COWL - A gas turbine engine includes an engine core extending along a core axis, a cooling-air delivery duct on the engine core, and a removable nacelle cowl overlying the engine core. A cooling-air nacelle-cowl duct delivers cooling air to the cooling-air delivery duct. At least a portion of the length of the cooling-air nacelle-cowl duct is integral with the nacelle cowl and not directly supported on the engine core.
|ZONED DISCONTINUOUS COATING FOR HIGH PRESSURE TURBINE COMPONENT - A turbine component has an airfoil extending between a leading edge and a trailing edge, and has an outer surface. A coating includes at least two discontinuous areas that are spaced from each other such that there is an area of uncoated surface between the discontinuous areas of coating. In addition, a method of providing such a coating is disclosed.
|TURBOMACHINE - A turbomachine comprises a housing (
|HEAT DISSIPATION DEVICE AND CENTRIFUGAL FAN THEREOF - An exemplary heat dissipation device includes a centrifugal fan and a fin assembly. The centrifugal fan includes a fan frame and an impeller mounted in the fan frame. The fan frame includes a base plate, a cover plate and a side wall extending between the base plate and the cover plate. An air outlet is defined in the side wall.
|WIND TURBINE WITH A REFRIGERATION SYSTEM AND A METHOD OF PROVIDING COOLING OF A HEAT GENERATING COMPONENT IN A NACELLE FOR A WIND TURBINE - The invention provides a wind turbine wind turbine with two vessels, each being interchangeably in thermal communication with a heating medium which transfers heat from a heat generating structure to the vessel, and with a cooling medium which transfers heat from the vessel to an ambient space. The vessels form a compression structure which form part of a refrigerating circuit which can circulate a working fluid between the compression structure, a condenser and an evaporator. At the evaporator, cooling effect is obtained based on evaporation of a working fluid, and the cooling can be utilized for cooling a heat generating component in the wind turbine.
|AIRFOIL HEAT SHIELD - Exemplary embodiments include a multi-layer, modular and replaceable heat shield for gas turbines. The heat shield apparatus can include a base layer adjacent the airfoil and a thermal layer coupled to the base layer, wherein the base layer and the thermal layer match a contour of the airfoil.
|Fan with heat dissipating outlet guide vanes - A method for designing a fan having a motor which drives an impeller comprises providing an outlet guide vane assembly which includes a hub and a plurality of guide vanes that extend radially outwardly from the hub, attaching the hub to the motor, determining an approximate amount of heat which is generated by the motor during operation of the fan, determining an approximate surface area which is required to dissipate the heat into a surrounding air stream, and configuring the guide vanes to comprise a total surface area which is approximately equal to the required surface area. In this manner, the heat generated by the motor during operation of the fan can be dissipated by the guide vanes.
|HIGH REFLECTIVITY INFRARED COATING APPLICATIONS FOR USE IN HIRSS APPLICATIONS - The present invention is a hover infrared suppression system for a gas turbine engine comprising a hover infrared suppression system having an upstream first stage, a second stage downstream of the first stage and a third stage downstream of the second stage, the engine operating at a temperature sufficient to cause the hover infrared suppression system to emit infrared radiation. The present invention further comprises a high reflectivity coating applied over a preselected area of at least one of the stages of the hover infrared suppression system to reduce the infrared radiation emitted from the engine, the high reflectivity coating being fired after application.
|RAM AIR FAN MOTOR COOLING - A ram air fan assembly includes a ram air fan disposed at a fan inlet and a ram air fan motor operably connected to the ram air fan. A blower is operably connected to the ram air fan and is configured to redirect a cooling flow across the ram air fan motor from a substantially axially directed flow to a substantially radially directed flow thereby increasing the cooling flow across the ram air fan motor. A method of cooling a ram air fan assembly includes urging a cooling flow toward the ram air fan motor and is directed across the ram air fan motor thus removing thermal energy from the ram air fan motor. The cooling flow proceeds across a blower operably connected to the ram air fan motor, thus directing the cooling flow substantially radially outwardly toward the fan inlet.
|AIR CYCLE MACHINE COMPOSITE INSULATOR PLATE - An air cycle machine including a housing with a compressor housing portion and a turbine housing portion secured to one another by fasteners. The compressor and turbine housing portions each provide a surface. An insulator plate is provided between and engages the surfaces. The fasteners extend through circumferentially arranged holes in the insulator plate. The insulator plate has an axial width, an inner diameter and an outer diameter. The outer diameter to the inner diameter provides a first ratio of 1.19-1.21, and the inner diameter to the width provides a second ratio of 53-59. In one example, the insulator plate is a composite structure constructed from 9-12 carbon fiber laminations with each layer having directional carbon fibers oriented transversely relative to the carbon fibers of an adjacent layer.
|COMPRESSION SYSTEM FOR TURBOMACHINE HEAT EXCHANGER - An example turbomachine cooling arrangement includes a pump configured to pressurize a first turbomachine fluid that is then communicated through a heat exchanger assembly to remove thermal energy from a second turbomachine fluid. A portion of the pump is configured to be housed within a gearbox housing of a turbomachine.
|INLET AIR CONDITIONING SYSTEM - An embodiment of the present invention provides an air conditioning system located upstream of the inlet system for a gas turbine. The air conditioning system may comprise at least one conditioning module for adjusting the temperature of the airstream. The at least one conditioning module may have a plurality of forms including at least one of the following systems: a chiller, an evaporative cooler; a spray cooler, or combinations thereof. The specific form of the at least one conditioning module may be determined in part the configuration of the gas turbine.
|Sealing System for Centrifugal Pumps - A centrifugal pump for delivering hot fluids, having a contacting shaft seal, a seal housing (
|Use of a Tungsten Bronze Structured Material and Turbine Component with s Thermal Barrier Coating - A tungsten bronze structured ceramic material as a thermal barrier coating is described wherein the tungsten bronze structured ceramic coating material has the formula AO—B
|PROTECTION OF THERMAL BARRIER COATING BY A SACRIFICIAL COATING - According to an embodiment of the invention, an article of manufacture for use in a gas turbine engine is disclosed. The article comprises a part having a surface covered with a ceramic thermal barrier coating. The thermal barrier coating has an outer surface covered with a sacrificial phosphate coating, wherein the sacrificial phosphate coating reacts with contaminant compositions to prevent contaminant infiltration into the thermal barrier coating.
|Heating pump - A heating pump includes an electric motor, a pump housing fixed to the motor, an impeller driven by the motor, and a ring heater with an inner hole for heating fluid in the pump housing. The pump housing has a pump chamber and a pump inlet and a pump outlet which are in fluid communication with the pump chamber. The impeller is received in the pump housing and having an impeller inlet and a plurality of impeller outlets. The ring heater is disposed inside the pump chamber and between the pump inlet and the impeller. The impeller inlet is in fluid communication with the pump inlet via the inner hole.
|FAN AND FAN ASSEMBLY - An assembly includes a fan and a heat sink for detachably fixing the fan. The fan includes a pair of first and a pair of second sidewalls, with two pair of rims respectively extending from the first and second sidewalls. Ends of the rims of the first sidewalls, which are directed toward and are adjacent to a same one of the second sidewalls, each have a latch flange. Ends of the rims of the second sidewalls, which are directed toward and are adjacent to a same one of the first sidewalls, each have a latch flange. The heat sink includes a channel for slidably receiving one pair of rims of the first or second sidewalls, a blocking member disposed at one end of the channel to block a corresponding sidewall of the fan, and a latch member disposed at the other end of the channel to latch the corresponding latch flanges.
|SIMPLIFIED HOUSING FOR A FUEL CELL COMPRESSOR - A compressor includes a shaft assembly including a thrust disk disposed on a main shaft and a housing having a first portion and a second portion, the first and second portions adapted to receive the shaft assembly and enclose the shaft assembly therebetween, wherein the shaft assembly is rotatably disposed within the housing, and wherein at least one of the first portion and the second portion includes a shaft assembly retention feature for receiving the thrust disk to regulate a motion of the shaft assembly.
|TURBINE ROTOR WHEEL - A rotor wheel is provided and includes a body having first and second opposing faces and portions recessed from a plane of the first face to define therein an annular groove and a plurality of tributary grooves, the annular groove being receptive of fluid from an external source and formed to direct the fluid to flow along an annular flow path, and the plurality of tributary grooves being receptive of the fluid from the annular groove and respectively formed to direct the fluid to flow sequentially along radial and axial tributary flow paths while preventing inter-tributary groove fluid communication.
|IMPINGEMENT COOLING ARRANGEMENT FOR A GAS TURBINE ENGINE - There is disclosed an impingement cooling arrangement for a gas turbine engine (
|DIVOTED AIRFOIL BAFFLE HAVING AIMED COOLING HOLES - A baffle insert for an internally cooled airfoil comprises a liner, a divoted segment and a plurality of cooling holes. The liner has a continuous perimeter formed to shape a hollow body having a first end and a second end. The divoted segment of the hollow body is positioned between the first end and the second end. The plurality of cooling holes is positioned on the divoted segment to aim cooling air exiting the baffle insert at a common location.
|TURBOMACHINE INLET HEATING SYSTEM - A turbomachine system includes a compressor having a compressor intake and a compressor extraction outlet, and an inlet system fluidly connected to the compressor intake and the compressor extraction outlet. The inlet system includes a plenum having a first end portion that extends to a second end portion through an intermediate portion. The inlet system also includes a heating system having a plurality of conduits extending horizontally through the intermediate portion of the plenum and arranged in a vertical relationship. Heated air from the compressor extraction outlet passes through the plurality of conduits and raises a temperature of ambient air passing through the plenum and into the compressor intake.
|METHOD AND APPARATUS FOR GAS TURBINE ENGINE TEMPERATURE MANAGEMENT - A turbine engine has a compressor for delivery of compressed air to a combustor. The combustor delivers hot combustion gas through an outlet to a turbine. The turbine includes a nozzle assembly, downstream turbine blades, and shroud assemblies adjacent radially distal ends of turbine rotor blades. The nozzle and shroud assemblies include internal cooling passages for receiving compressed air from the compressor and, cooling air apertures opening through walls of the vanes and shrouds into the hot gas path to release film cooling air. The number of apertures, the aperture area, and the aperture pattern are varied in relation to the circumferential temperature profile of the combustion gas with a higher aperture area and/or higher number of apertures in high temperature regions and a lower aperture area and/or lower number of apertures in low temperature regions.
|GAS TURBINE ENGINE COMPRESSOR COMPONENTS COMPRISING THERMAL BARRIERS, THERMAL BARRIER SYSTEMS, AND METHODS OF USING THE SAME - Gas turbine engine compressor disks having a hot flowpath side; a shaft having a first surface positioned in the hot flowpath side; and a thermal barrier applied to at least the first surface of the shaft where the thermal barrier is operable to maintain the temperature of the shaft below about 700° C. (1300° F.) when the hot flowpath side experiences a service operating temperature of from about 700° C. (1300° F.) to about 788° C. (1450° F.).
|Gas-Turbine Aircraft Engine With Structural Surface Cooler - The present invention relates to a gas-turbine aircraft engine with a core engine surrounded by a bypass duct, with a substantially annular cooling element being provided in the area of a radially inner wall of the bypass duct downstream of stator vanes of the bypass duct.
|HEAT INSULATING STRUCTURE FOR EXPANSION TURBINE, AND METHOD OF MANUFACTURING THE SAME - A heat insulating structure for an expansion turbine includes an adiabatic expansion device including an expander body that includes an outlet passage for refrigerant fluid at a central portion thereof and an introduction chamber for refrigerant fluid communicating with an inlet of the outlet passage on an outer peripheral portion thereof, and a turbine impeller that is rotatably provided at the inlet and braked by a braking device. The adiabatic expansion device adiabatically expands refrigerant fluid by rotating the turbine impeller with refrigerant fluid that flows from the introduction chamber to the outlet passage side. A heat-insulating layer, which surrounds the entire periphery of the outlet passage over the entire length of the introduction chamber, is formed between the introduction chamber and the outlet passage. Accordingly, it is possible to improve turbine efficiency by reducing transfer of heat of refrigerant fluid from the introduction chamber to the outlet passage.
|TURBOCHARGER ASSEMBLY HAVING HEAT SHIELD-CENTERING ARRANGEMENTS - A turbocharger for internal combustion engines, having a heat shield disposed between a turbine housing and center housing of the turbocharger for shielding the center housing from exhaust gases passing through the turbine. The heat shield in one embodiment is centered on a generally conical surface of the center housing, by engagement between the conical surface and a centering portion of the heat shield. In another embodiment, the heat shield has a generally conical portion that is non-axisymmetric, having a plurality of radially enlarged lobes that engage a radially inwardly facing surface of the turbine housing for centering the heat shield.
|INSULATOR, AND STATOR AND MOTOR PROVIDED WITH SAME - An insulator includes a main body, a latching portion, and a slot. The main body covers a portion of a stator core around which a coil is wound to insulate the stator core from the coil. The latching portion is disposed at an end of a portion of the main body around which the coil is wound to latch the coil onto the main body. The slot is formed so as to expose the coil at a portion of the latching portion on a side where cooling oil for cooling the coil is supplied to the coil.
|INLET BLEED HEAT SYSTEM - An embodiment of the present invention takes the form of an IBH system that has a single conduit, which is positioned close to a downstream end of a silencer section. This arrangement may reduce the overall pressure drop associated with the inlet system. This arrangement may also promote a substantially uniform mixing between the cooler ambient air and the warmer heated air.
|OIL MANAGEMENT SYSTEM FOR A COMPRESSOR - The invention relates to an oil management system for a compressor in a refrigeration system comprising: an oil temperature sensor; a heater arranged to heat oil in a crank case of the compressor; and a controller operatively associated with the temperature sensor and the heater, the controller arranged to control operation of the heater on the basis of ambient air temperature and oil temperature to maintain the oil temperature within a range Tmax≧R≧Tmin where Tmax>Tmin.
|INLET BLEED HEAT SYSTEM - An embodiment of the present invention takes the form of an IBH system that has two conduits, which are positioned close to a downstream end of a silencer section. This arrangement may reduce the overall pressure drop associated with the inlet system. This arrangement may also promote a substantially uniform mixing between the cooler ambient air and the warmer heated air.
|EXHAUST GAS HOUSING FOR A GAS TURBINE AND GAS TURBINE HAVING AN EXHAUST GAS HOUSING - An exhaust gas housing for a gas turbine, in which an annular gas passage, through which exhaust gas discharges from the gas turbine to the outside, is formed by a concentric inner casing and an outer casing which concentrically encompasses the inner casing at a distance, wherein the inner casing and the outer casing are interconnected by a plurality of radial struts which extend through the gas passage and have in each case a leading edge and a trailing edge with regard to the exhaust gas flowing through the gas passage, and wherein the struts, the outer casing and the inner casing are equipped in each case with a heat-resistant lining towards the gas passage, wherein the lining of the struts is at least partially mechanically decoupled from the lining of the inner casing and/or of the outer casing for reducing thermal stresses on the periphery of the struts.
|SEGMENTED THERMALLY INSULATING COATING - A gas turbine article includes a substrate and a thermally insulating topcoat disposed on a surface of the substrate. The surface of the substrate includes a surface pattern defining first surface regions and second surface regions. The first surface regions include incubation sites that are favorable for deposition of the thermally insulating topcoat and the second surface regions are less favorable for deposition of the topcoat. The topcoat includes segmented portions that are separated by faults extending through the topcoat from the second regions.
|COMPRESSOR HOUSING RESISTANT TO TITANIUM FIRE, HIGH-PRESSURE COMPRESSOR INCLUDING SUCH A HOUSING AND AIRCRAFT ENGINE FITTED WITH SUCH A COMPRESSOR - A compressor housing resistant to a titanium fire (burning titanium). A mixed housing is constructed, in which a structure holding stator blades includes a single-cast part made from titanium or titanium alloy, and at least one element forming a shield made from refractory alloy(s), and which is incombustible in presence of burning titanium, where each shield is secured to the single-cast part by fasteners. The fasteners are positioned with each shield so as to define jointly an inner wall demarcating an outer contour of the compressor airstream.
|EXHAUST-GAS TURBOCHARGER - An exhaust-gas turbocharger includes a bearing flange for securement of the exhaust-gas turbocharger to a bearing housing of a turbine wheel. The bearing flange is provided with an outer circumferential fin having a base portion which terminates in a free end. The base portion is defined by a width which is greater than a width of the free end. An outer housing is welded to the outer circumferential fin of the bearing flange, and accommodates an impeller housing.
|GAS TURBINE ENGINE WITH OUTER CASE AMBIENT EXTERNAL COOLING SYSTEM - A thermal barrier/cooling system for controlling a temperature of an outer case of a gas turbine engine. The thermal barrier/cooling system includes an internal insulating layer supported on an inner case surface, the internal insulating layer extending circumferentially along the inner case surface and providing a thermal resistance to radiated energy from structure located radially inwardly from the outer case. The thermal barrier/cooling system further includes a convective cooling channel defined by a panel structure located in radially spaced relation to an outer case surface of the outer case and extending around the circumference of the outer case surface. The convective cooling channel forms a flow path for an ambient air flow cooling the outer case surface.
|THERMAL INSULATION STRUCTURE FOR STRUCTURAL MEMBER, AND SCROLL STRUCTURE - To provide a thermal insulation structure for a structural member and a scroll structure which can be easily used even in integrally constructed structural members and which can ensure reliability and thermal insulation properties. Provided are securing portions (
|TURBO COMPRESSOR - A turbo compressor is provided that has first, second and third stage compressor blades rotated by a large gear shaft via an acceleration device, and includes a cast integral casing (
|TURBINE EXHAUST DIFFUSER SYSTEM MANWAYS - A turbine exhaust diffuser system includes a plurality of manways. The plurality of manways each extend between an outer wall of the turbine exhaust diffuser system and an interior access tunnel of the turbine exhaust diffuser system. The plurality of manways extend between the outer wall and the access tunnel at an angle that is not perpendicular to a central axis of the turbine exhaust diffuser system.
|Turbine Shell Having A Plate Frame Heat Exchanger - A turbine shell is provided, and includes a body portion and at least one plate. The body portion has a forward portion and an aft portion. The plate is located between the forward portion and the aft portion. The plate is part of a plate frame heat exchanger, which is part of the body portion of the turbine shell.
|WIND TURBINE NACELLE WITH COOLER TOP - The present invention relates to a wind turbine nacelle having a first face with a longitudinal extension in a wind direction, comprising a cooling device having a cooling area and extending from the first face of the nacelle, and a cover having at least one inner face, the cooling device being enclosed by the first face of the nacelle and the inner face of the cover. A first distance between at least one of the faces and the cooling area is at least 30 mm.
Patent applications in class INCLUDING HEAT INSULATION OR EXCHANGE MEANS (E.G., FINS, LAGGING, ETC.)
Patent applications in all subclasses INCLUDING HEAT INSULATION OR EXCHANGE MEANS (E.G., FINS, LAGGING, ETC.)


text:
India's frontrunner for prime minister Narendra Modi has pledged to speed up corruption-hit defense procurement if he comes to power to ensure the country's military is better prepared for battle.
As the nation's general election enters its final stretch, Modi said timely, cost-effective and corruption-free purchase of defense weapons and other equipment was critical for the military.
"The last 10 years has seen our defense preparedness becoming weak on account of several procurement procedures mired by long delays leading to shortage of arms and equipment," Modi told the Times of India in an interview published Tuesday.
"In the past, we have had a paradoxical situation where there was hardly any procurement happening in time and still serious questions of transparency have been raised."
"The ideal situation is an efficient procurement system leading to timely and cost-effective procurement of quality defense equipment, done in a transparent manner," he said.
Modi, a Hindu nationalist hardliner, and his opposition Bharatiya Janata Party (BJP) are expected to vault to power over the ruling Congress party after a decade in power when results are announced on May 16.
India has faced a long list of failed defense deals over the years as a result of corruption allegation scandals that have left the military short of crucial equipment.
In January, India cancelled a deal with the Italian-owned AgustaWestland to buy 12 luxury helicopters amid allegations the company paid bribes to win the 556-million-euro ($753 million) contract.
The scuppered deals come at the same time as India's military needs are growing, with tensions on its border with Pakistan, an increasingly assertive China and growing ambitions for India's role in world affairs.
In the longer term, Modi said India must reduce its reliance on other defense suppliers — traditionally Russia but now also including the United States, Israel and France.
"We should involve Indian corporates in PPPs (public-private partnerships) for defense manufacturing. We have the scientific and technical know-how but the arms lobby has prevented indigenization of military hardware."
"This must change, making India more self-reliant and also saving foreign exchange," he said.
In the interview, Modi also said ties with arch rival Pakistan could not improve unless the country worked hard to stop militants from carrying out attacks on Indian soil.
"The first step in building any meaningful relationship with Pakistan has to be Pakistan taking effective and demonstrable action against the terror networks that operate from its soil."
"Once that happens, there will an increased trust between the two neighbors which will enable us to pursue a policy of dialogue to solve all the issues."
Related Articles
Related Topic Tags
Related Defense, Military & Aerospace Forum Discussions
- ADF General discussion thread
- Iraqi Air Force and Air Defense
- Iraq war/unrest/fighting
- Russian Air Force News & Discussion
- Royal New Zealand Air Force
- RussianLand Forces Thread
- Russian Navy Discussions and Updates
- Royal Australian Navy Discussions and Updates
- Brazilian Naval Strength
- The Royal Navy Discussions and Updates
- Mexico's military defense
- Ukranian Crisis
- Russia tests new missiles
- Australian Army Discussions and Updates
- Royal Air Force [RAF] discussions and updates


text:
This page contains Cheats for Shinobi 3: Return Of The Ninja Master organized by sections for Genesis. Shinobi 3: Return Of The Ninja Master is a Action Platformer 2D game, made by Megasoft (Japan), released on Jul 22, 1993 and published by Sega. If you can't find a hint or secret in our list, then please check this page periodically for the latest updates.
- Developer:
Shinobi 3: Return Of The Ninja Master Genesis CheatsMegasoft (Japan)
- Publisher: Sega
- Genre: Action Platformer 2D
- Release Date: Jul 22, 1993
- ESRB: Not Set
Set the amout of shurikens to 0 on the options menu, Set the sounds effects option to Shuriken. Highlight the shurikens option and keep it there and the 0 will change into the symbol for infinity....From: pradeeprk4
Choose BMG selection on the options menu, then, press B to select the following songs in order. He runs, Japonesque, shinboi walk, sakura, getufu...From: smartestforyou
Some ninjustu spots are in Level 1, Section 2. When you get to the first hangover rope, there are 2 boxes there, one has the ninjustu. (Not new ninjustus, just another to use.) Next, is one in Level 2, section 2. It's hard to tell exactly, but keep jumping high, (Maybe use the Fushin ninjustu)there ...From: Hyper Ty 7
Stuck on this game? Set a specific, clearly defined question and let others answer your question or view answers to previously asked questions. If you think you are an Shinobi 3: Return Of The Ninja Master expert then please try to help others with their questions.
I'm stuck on round 2, when you have to go up the elevator, is there anyway to skip this level?...
Posted on: 09-13-2012
Shinobi 3: Return Of The Ninja Master - Gameplay
- May 28, 2014, Views: 133
Shinobi 3: Return Of The Ninja Master - Intro
- May 28, 2014, Views: 116
Shinobi 3: Return Of The Ninja Master - Ending + Credits
- May 28, 2014, Views: 92
- Teenage Mutant Ninja Turtles - Review Trailer, (Genesis)
- Terminator 2: The Arcade Game - Review Trailer, (Genesis)
- Streets Of Rage 3 - Gameplay, (Genesis)
- Streets Of Rage - (wii virtual console version) sega segenesis/megadrive Blaze gameplay, (Genesis)
- Outrun 2019 - Gameplay Video 1, (Genesis)
- Wonder Boy In Monster World - JP Review Trailer, (Genesis)
- Fire Shark - Gameplay Video 1, (Genesis)
- Jurassic Park - Review Trailer, (Genesis)
- Kim Kardashian: Hollywood - Gameplay, (iPhone-iPod)
- Episode: Choose Your Story - Gameplay, (iPhone-iPod)
- How To Train Your Dragon 2 - Ready To Fly Trailer, (Wii)
- The Settlers - Kingdoms Of Anteria - Announcement Trailer, (PC)
- Entwined - Quick Look Trailer, (PS3)
- Blue Estate - Official Launch Trailer, (PS4)
- Goat Commando 3D Simulator - Gameplay, (iPhone-iPod)
- Munin - Official Launch Trailer, (iPad)


text:
Body-Solid Functional Training CenterModel GDCC210Define the motions that are right for you and your individual workout goals with the Body Solid GDCC210 Functional Training Center. This dual independent weight stack system provides dedicated resistance with true isolateral movements.Core stability training can lead to improved balance, coordination and stability. By efficiently working your body's stabilizer muscles though a limitless number of exercises, the GDCCC210 Functional Training Center offers strength-building results to users of all sizes. The Body Solid GDCC210 features ergonomically designed adjustments and interchangeable cable handles engineered to put hundreds of strength-building exercises within your grasp.With a space-saving footprint, dual independent weight stacks, user-friendly ergonomics and adjustability and precision-fitted components, the GDCC210 Functional Training Center isolates an unbeatable value in today's advanced fitness market.From cable crossovers and shoulder presses to pull-ups, leg kickbacks and everything in between, make a motion to improve your core, build your strength and increase your endurance with the Body Solid GDCC210
This page cannot be copied in whole or in part without the written consent of Bayou Fitness.Copyright 2007, Bayou Fitness Products
Don't miss special offers and updates:
totaltrainer.comCheck out our Total Trainer info page.
Copyright 2011 BayouFitness. Customer Service: 1-800-847-3988
All Training Equipment:
Total Trainer
, Dumbbells
, Home Gyms
, E Series
, DVDs
, Benches
, Boxing MMA
, Commercial Rated
, Crossfit
, Elliptical Trainers
, Gravity Resistance Systems
, Kettlebells
, Mats
, Pilates Equipment
, Plate Weight Bars Storage
, Power Towers
, Racks
, Rebounders
, Rowers
, Sale & Clearance
, Smith Machines
, Strength
All Fitness Brands:
Bayou Fitness
, Best Fitness
, Body Solid
, Proform
, Valor Fitness
, XMark Fitness
, Yukon Fitness
Excellent customer service and competitive pricing are what makes Bayou Fitness® stand out from others. Our focus has always been on selling quality products at wholesale pricing. Having trouble deciding on which product to order? The Bayou sales staff can help you make an informed decision based on your needs plus answer any questions that you may have.


text: Congratulations, does this mean we might see you in the summer? I start my masters in Jan, will be odd to be back in school. Good luck in finishing up, Susan Rostislav <rostislav at cox.net> wrote: EEEeeeeeeeeerrrrrrrrrrkkkkk. . The door opens slowly and I peek around the corner. Hi Lordses and Ladieses. I haven't forgotten you just been toooooo busy with homework. Holdin a 4.0 for 4 semesters now and one to go. I'll get a break for summer then back at it for a Masters in the fall. Miss you all. Ros. _______________________________________________ Namron mailing list Namron at ansteorra.org http://www.ansteorra.org/mailman/listinfo/namron --------------------------------- Do you Yahoo!? Protect your identity with Yahoo! Mail AddressGuard -------------- next part -------------- An HTML attachment was scrubbed... URL: /pipermail/namron-ansteorra.org/attachments/20031108/ab4a6923/attachment.html


text:
Advanced Writing Skills for Lawyers
Course Number:704
The purpose of this course is to improve legal writing and analysis skills. To accomplish that goal, students will draft pleadings, pretrial motions, office memoranda, other documents and a brief in support of summary judgment. In-class editing exercises reinforce the instruction in effective writing and analysis. The course, in several ways, will mimic the law firm clerking experience. In order to facilitate feedback and personal instruction, the course will be limited to 10 students.
Page last updated: Tue, 06/26/2012 - 09:32


text:
15" X 22" Gouache and watercolor on Strathmore Illustration Board.
...So Beautiful...nice work...:Aug 23rd, 2011 Reply Subscriber
Thank you for the lovely comment on Tropical Birds. They are very much appreciated!Aug 24th, 2011 Reply
Thanks for sharing your beautiful work! It's an inspiration to all of us artists and has been featured in the Daily Inspiration #168 , congratulations!
Magnificient!Aug 21st, 2011 Reply
this is absolutely fantastic and brilliant and the details are tremendousAug 21st, 2011 Reply Subscriber
So many cute birds. I like this. I love macaws and humming birds. I'd love to have a hyacinth. And Major Mitchel's cockatoos are so pretty.Aug 20th, 2011 Reply
I love just about all birds, but I own a Blue and Gold Macaw. Most are too expensive to buy!Aug 20th, 2011 Reply


text:
Poor Kelly just cannot win, can she?
After her much-bigger-in-the-UK-than-the-US popularity landed her a spot as a judge on X-Factor UK, people are saying she's the main reason no one fawks with the show anymore.
Simon Cowell has reportedly expressed his anger at The X Factor producers after the show lost more than two million viewers.
"The figures are hugely disappointing for The X Factor because the whole point of the live shows is that they are supposed to build momentum."
The source added: "Last year there were nearly 14million watching the second live show. Where have all those viewers gone? It's no wonder Cowell has gone ballistic. Losing viewers is the last thing he wanted to happen."
Kelly Rowland is being blamed for causing trouble on the show, with The Sun claiming she's been "bossing about" fellow panelist Tulisa Contostavlos and telling Louis Walsh's acts to scrap his ideas.
The insider revealed: "Kelly is trying to turn this into The Kelly Show with her meddling — and it's really putting people's noses out of joint. The contestants love it as they're in awe of her but the judges hate it."
"Tulisa has properly fallen out with her after Kelly went to speak to her about the styling and songs and vocals for Rhythmix."
They explained: "Tulisa just ignored her and was fuming that she was poking her nose in. Kelly walked off muttering something about, 'Tulisa not wanting her advice, even though she has sold millions of records and was in the biggest girl group ever'.
Wow. Kelly's feeling herself THAT much? AND her behind the scenes shenanigans are seeping out into the show's popularity? It has nothing to do with the fact that Simon bounced and left lackluster replacements for his UK audience, right?
More On Bossip!
Australia, Get Your Girl: More Of The Funniest Iggy Azalea Slander
New Couple: Which NBA Baller Is Chopping Coach Doc Rivers Banger Daughter Callie's Cakes To Smithereens Now?
Funniest, Messiest & Shadiest Comments Left On Blac Chyna's Instagram Pics
The Complete 2014 Hater's Guide To Kim Kardashian
'Charlamagne Tha Auntie:' Twitter Goes In On Charlamagne Tha God's Shea Buttery Selfie


text:
Newsweek and Daily Beast Merge
NEW YORK ( TheStreet) -- Newsweek magazine and The Daily Beast, have merged to become the Newsweek Daily Beast company.
The joint venture will be equally owned by Newsweek owner Sidney Harman and Barry Diller, CEO of The Daily Beast's parent company IAC/InterActive (IAC).
"In an admittedly challenging time, this merger provides the ideal combination of established journalism authority and bright, bristling Web site savvy," Harman said
Newsweek magazine was founded in 1933, and was purchased by the Washington Post (WPO) in 1961.In its 2009 annual report, the Washington Post reported the struggling financial state of the magazine. Advertising revenue was down 37%, which followed a 14% decline in 2008. In efforts to reduce costs, the company reduced the magazine's domestic circulation rate base from 3.1 million to 2.6 million in 2008. Then in January 2010, it lowered domestic circulation to 1.5 million. In August, the Washington Post sold the magazine for $1 to Harman, the founder of audio and video equipment company Harman International (HAR). The Beast's president Stephen Colvin will become CEO of the new company and Harman will be an executive chairman. Tina Brown, co-founder and editor in chief of The Daily Beast will also become editor in chief at Newsweek magazine.
Select the service that is right for you!COMPARE ALL SERVICES
Action Alerts PLUSTry it NOW
Jim Cramer and Stephanie Link actively manage a real portfolio and reveal their money management tactics while giving advanced notice before every trade.
Product Features:
- $2.5+ million portfolio
- Large-cap and dividend focus
- Intraday trade alerts from Cramer
- Weekly roundups
TheStreet Quant RatingsTry it NOW
Only $49.95/yr
Access the tool that DOMINATES the Russell 2000 and the S&P 500.
Product Features:
- Buy, hold, or sell recommendations for over 4,300 stocks
- Unlimited research reports on your favorite stocks
- A custom stock screener
- Upgrade/downgrade alerts
Stocks Under $10Try it NOW
David Peltier, uncovers low dollar stocks with extraordinary upside potential that are flying under Wall Street's radar.
Product Features:
- Model portfolio
- Stocks trading below $10
- Intraday trade alerts
- Weekly roundups
Dividend Stock AdvisorTry it NOW
Jim Cramer's protege, David Peltier, identifies the best of breed dividend stocks that will pay a reliable AND significant income stream.
Product Features:
- Diversified model portfolio of dividend stocks
- Alerts when market news affect the portfolio
- Bi-weekly updates with exact steps to take - BUY, HOLD, SELL
Real Money ProTry it NOW
All of Real Money, plus 15 more of Wall Street's sharpest minds delivering actionable trading ideas, a comprehensive look at the market, and fundamental and technical analysis.
Product Features:
- Real Money + Doug Kass Plus 15 more Wall Street Pros
- Intraday commentary & news
- Ultra-actionable trading ideas
Options ProfitsTry it NOW
Our options trading pros provide daily market commentary and over 100 monthly option trading ideas and strategies to help you become a well-seasoned trader.
Product Features:
- 100+ monthly options trading ideas
- Actionable options commentary & news
- Real-time trading community
- Options TV


text:
Columbia-Brazoria ISD Employment
Cyndy Pullen - Director of Human Resources
CBISD is accepting applications for the following:
♦Carpenter/General Maintenance
To view current employment opportunities with Columbia-Brazoria ISD or to complete/submit an online application, please click here.
*All applicants for instructional positions must meet requirements for Highly Qualified as defined by the No Child Left Behind Act.
2013-2014 CBISD Substitute Handbook
2013-14 Salary Compensation Schedule
For more information about employment with Columbia-Brazoria, please contact Human Resources by completing the form below.
Friday, December 19, 2014


text:
Troy D. Thompson, MD
Ratings based on 6 reviews
Write a review
Are you a patient of Troy D. Thompson, MD?
Reviews (6)
34 Years Old. 5'4. 142 lbs. Mother of Three. Need a Little Lift. - Round Rock, TX
He takes a long time to talk to you on your first visit. He is a character. You might not feel comfortable with him, because he has his opinion, but it takes a few minutes for him to process what you want to do ;-). And I love that!! But he is always willing to understand what you really want. And be prepared. He wants to make you dangerous ;-) ha ha He meant SEXY!!
5 out of 5 stars Breast Augmentation
Love my New Maracas! - Round Rock, TX
5 out of 5 stars Breast Implants
Rock N Roll Tatas - Round Rock, TX
5 out of 5 stars
Couldn't Be Happier! - Round Rock, TX
5 out of 5 stars Tummy Tuck
WELL Worth the Money and the Minor Pain! -3 months PO in Round Rock, TX
I was referred to this doctor by another specialist. And when I got to the hospital for the pre-op appointment all of the nurses told me that Dr. Thompson is the only doctor they'd use for this type of surgery. He's awesome!