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A multistage centrifugal impeller in which each blade row is individually matched to optimum efficiency characteristics in a manner which minimizes blade lean. Each blade row is composed of twisted blades which substantially equalize working fluid diffusion from blade root to blade tip while restraining blade lean to less than 15°.
1. A centrifugal compressor for compressing a fluid comprising:
(a) an annular flow path, substantially parallel to an axis of rotation at an inlet and substantially perpendicular to the axis of rotation at an outlet, the outer surface of which is formed by a stationary shroud, and the inner surface of which is formed by a rotatable impeller hub; and
(b) an impeller comprising at least two rows of blades positioned upon a rotatable impeller hub, including:
(i) a first, inlet blade row comprising a plurality of blades extending from said hub at said inlet, each blade including a root and a tip and leading and trailing edges and being twisted from said root to said tip for obtaining blade lean for being matched to different substantially optimum generally axially extending curvilinear airstream lines at both the root and the tip for the purpose of producing a generally constant, pressure flow at the exit of said first blade row from said roots to said tips; and
(ii) a second blade row comprising a plurality of blades extending from said hub at said outlet, said second blade row being axially spaced from said first blade row and each blade including a root and a tip and leading and trailing edges and being twisted from said root to said tip for obtaining blade lean for being matched to substantially different optimum generally radially extending curvilinear airstream lines at both the root and the tip for the purpose of producing a generally constant pressure flow at the exit of said second blade row from said roots to said tips.
2. A multistage centrifugal compressor according to claim 1 wherein:
said blade rows are comprised of differing numbers of rotating blades.
3. A centrifugal compressor for compressing a fluid comprising:
(a) an inlet, generally axial flow, stage comprising a plurality of blades, each blade including a root and a tip and leading and trailing edges and being twisted from said root to said tip for obtaining blade lean which substantially equalizes the diffusion of the fluid at the root and tip of the blade; and
(b) a second, generally radial flow, stage comprising a plurality of blades, each blade including a root and a tip and leading and trailing edges and being twisted from said root to said tip for obtaining blade rake which substantially equalizes the diffusion of the fluid at the root and tip of the blade.
4. A multistage centrifugal compressor as claimed in claim 1 or 2 further characterized by:
(a) said inlet blade row being shaped as a twisted sheet wherein the blade tip profile differs from the blade root profile in order that both the blade tip and blade root apply a substantially equalized rate of diffusion to the working fluid, and
(b) said second blade row comprising an exit blade row so shaped as to produce a primarily centrifugal flow wherein the blade root and blade tip profiles are substantially the same at the fluid exit.
5. A multistage centrifugal compressor as claimed in claim 1, 2, or 3 further characterized by:
the blade rows axial length determined so as to minimize blade tip lean, while providing a substantially equalized rate of fluid diffusion for production of uniform fluid compression along the blade height from root to tip.
6. A multistage centrifugal compressor as claimed in claim 1, 2, or 3 further characterized by:
said blade rows being axially displaced from each other in order to allow the succeeding blade rows to re-initialize flow according to optimized blade angles for each flow region of the impeller.
7. A multistage centrifugal compressor as claimed in claim 2 or 3 further characterized by:
the blade rows being shaped to generate a substantially constant pressure airflow at blade row exits.
8. A multistage centrifugal compressor as claimed in claim 1, 2 or 3 further characterized by:
variation of blade number in rotating blade rows in order to maintain controlled rate of diffusion from impeller inlet to exit.
9. A multistage centrifugal compressor comprising:
a stationary shroud surrounding a centrifugal impeller, wherein the shroud in conjunction with the impeller defines an annular flow region for a compressor working fluid, in which fluid flow in a working fluid inlet is essentially parallel to an axis of impeller rotation and fluid flow in a working fluid exit is essentially perpendicular to the axis of rotor rotation, and in which the centrifugal impeller is comprised of at least two blade rows wherein:
(a) the centrifugal impeller rotates as one unit having no stationary blades situated between rotating blade rows,
(b) the successive rotating blade rows comprise increasing numbers of blades,
(c) each blade row is separated from every other blade row, and
(d) each blade of said impeller includes a root and a tip and leading and trailing edges, each blade being twisted from said root to said tip for obtaining blade lean effective for producing a generally constant pressure profile from said root to said tip at said trailing edge of each of said blades, and for obtaining a curvilinear flow path through said impeller blade rows.
10. A multistage supersonic centrifugal compressor comprising:
(a) a uniformly rotatable bladed rotor impeller having at least three blade rows wherein:
(i) each of the blade rows is of a separate and discontinuous mechanical form,
(ii) the number of blades in each blade row is determined by the circumferential volume of flow area and impeller rotational speed so as to produce a controlled rate of fluid diffusion throughout compressor,
(iii) each of the blade rows is axially removed from every other row,
(iv) each blade of said impeller includes a root and a tip and leading and trailing edges, each blade being twisted from said root to said tip for obtaining blade lean effective for producing a generally constant pressure profile from said root to said tip at said trailing edge of each of said blades, and for obtaining a curvilinear flow path through said impeller blade rows,
(b) a stationary shroud surrounding the rotor wherein:
(i) said shroud in conjunction with the rotor defines the annular flow region of a compressor working fluid,
(ii) said shroud in conjunction with the rotor defines the working fluid inlet and exit,
(c) a flow inlet in which the fluid flow is essentially parallel to the axis of rotor rotation, and
(d) a flow exit in which the fluid flow is essentially perpendicular to the axis of rotor rotation.
11. A multistage centrifugal compressor as claimed in claim 10 wherein said three blade rows further comprise:
(a) an inlet blade row shaped as a twisted sheet for producing an optimized primarily axial flow with substantially equalized rates of airflow diffusion at both blade hub and tip,
(b) a second row of blades so shaped as to produce a mixed axial and centrifugal flow, with substantially equalized rates of airflow diffusion at both blade tip and hub, and
(c) an exit blade row so shaped as to produce a primarily centrifugal flow.
12. A multistage centrifugal compressor as claimed in claim 10 further characterized by:
the blade rows being individually shaped and mechanically separate so as to reduce the required blade tip lean to less than 15°, while maintaining generally equalized rates of diffusion along the height of each blade.
13. A multistage centrifugal compressor as claimed in claim 11, further characterized by:
the trailing edge of the exit blade row being parallel to the axis of rotation, having virtually no rake and producing a primarily centrifugal fluid flow at the impeller fluid exit.
14. A multistage centrifugal compressor as claimed in claim 10 further characterized by:
an increase in blade numbers in successive blade rows designed to produce a controlled rate of diffusion of fluid flow as the fluid proceeds through the centrifugal compressor.
15. A multistage supersonic centrifugal impeller comprising:
at least two flow regions of blade rows where said blade rows are circumferentially displaced, including an inducer region for channeling primarily axial fluid flow, and an exducer region for exiting primarily centrifugal fluid flow and differing numbers of blades in each blade row and wherein each blade of said impeller includes a root and a tip and leading and trailing edges, each blade being twisted from said root to said tip for obtaining blade lean effective for producing a generally constant pressure profile from said root to said tip at said trailing edge of each of said blades, and for obtaining a curvilinear flow path through said impeller blade rows.
16. An impeller as claimed in claim 1, 10 or 15 further comprising:
an inlet blade row designed primarily for fluid supersonic relative velocities consistent with temperature corrected impeller blade tip speeds in excess of 1,200 ft/sec and having twisted blades in which the blade angle at the tip differs from the blade angle at the root.
17. An impeller as claimed in claim 1, 2 or 15 wherein:
the impeller is assembled from multiple pieces.
18. An impeller for a centrifugal compressor comprising:
(a) an annular hub having a radially outer surface including a first portion disposed substantially parallel to an axis of rotation of said hub, a second portion disposed substantially perpendicular to said axis of rotation, and a third portion joining said first and second portions;
(b) a first row of inducer blades extending radially outwardly from said first hub portion and being effective for channeling airflow in a substantially axial direction;
(c) a second row of exducer blades extending substantially axially outwardly from said second hub portion and being effective for receiving airflow from said first blade row and channeling said airflow in a substantially radially outward direction; and
(d) each blade of said impeller including a root and a tip and leading edges and trailing edges and each blade being twisted from said root to said tip for obtaining blade lean effective for producing a generally constant pressure profile from said root to said tip at said trailing edge of each of said blades, and for obtaining a curvilinear flow path through said impeller blade rows.
19. An impeller according to claim 18 further including a third row of blades extending outwardly from said third hub portion and being effective for receiving airflow in a generally axial direction from said first blade row and channeling said airflow in a generally radial direction to said second blade row.
20. An impeller according to claim 19 wherein said third blade row is axially spaced from said first and second blade rows to define gaps therebetween for allowing reinitialization of flow between said blade rows.
21. An impeller according to claim 19 wherein said first and third blade rows have lean at both said leading and trailing edges, and said second blade row has lean at said leading edge, said trailing edge thereof being disposed substantially perpendicular to said second hub portion.
This invention relates to centrifugal impellers and, in particular, concerns centrifugal impellers used as final compressor stages in aircraft gas turbine engines.
Gas turbine engines have become the standard propulsion source for all types of aircraft but the very smallest. The aircraft gas turbine engine operates as an open Brayton cycle system whose work output is either in the form of a high energy exhaust or a mechanical shaft rotation. In gas turbine engines that produce a high energy exhaust stream, turbofan or turbojet engines, the compressors are generally of the axial type. Axial compressors are made up of a series of rotating stages of axial blades which compress inlet air prior to combustion. In gas turbine engines of the rotating shaft type, turboshaft or turboprop engines, axial-centrifugal compressors have been found to be more suited in many applications. The axial-centrifugal compressors have a series of axial stages similar to pure axial compressors prior to a final centrifugal stage situated just upstream of a gas diffuser and a combustor. The centrifugal stage provides a high level of compression in a minimum of length.
The centrifugal impellers used in the axial-centrifugal compressors have been found lacking in several respects in comparison with axial stages.
In recent years the centrifugal impellers devised have not been able to achieve the efficiency of axial stages. This shortcoming in efficiency has limited centrifugal impeller use in turbojet engines and hindered axial-centrifugal compressor efficiency in turboshaft type engines.
The invention comprises a multistage centrifugal compressor in which there is an annular flow path substantially parallel to the axis of rotation at the inlet and substantially perpendicular to the axis of rotation at the outlet. The outer surface of the flow path is determined by a stationary shroud, while the inner surface is formed by a rotating impeller hub. The impeller comprises at least two rows of blades positioned upon the hub. Preferably, the blade rows have different numbers of rotating blades.
In the first blade row or inducer, at the inlet of the centrifugal compressor, each blade is made to match different substantially optimum air stream lines from the root to the tip of the blade. This allows for a generally constant pressure flow at the exit of the blade row.
The inlet blade row may be designed for fluid supersonic Mach numbers, consistent with temperature corrected impeller tip speeds in excess of 1,200 ft/sec.
There is also a second blade row comprising a transitional stage, in which a plurality of blades are axially spaced from the first blade row. In the second blade row, each blade is also made to match substantially different airstream lines at the root and the tip of the blade so as to allow a generally constant pressure flow at the exit of the blade row.
In a preferred embodiment a third stage, or exducer, is separated from the second stage of the impeller. The third stage is optimized according to the flow characteristics of the impeller exit. The exducer blades have little or no rake relative to the impeller hub at the airflow exit.
In the preferred embodiments, the blade rows stage are comprised of a plurality of blades, each blade having a profile incorporating lean, which substantially equalizes the diffusion of the fluid at the blade root and the blade tip. Blade row axial length is sufficiently short in each stage to minimize blade tip lean. Blade lean is thus restricted to less than 12°-15° at any place along any of the rows of blades.
A characteristic of the preferred embodiments is that the blade rows are axially displaced from each other in order to optimize flow according to optimized blade angles for each flow region of the impeller. It is further noted that a substantially constant rate of diffusion of the fluid being compressed is maintained throughout the centrifugal compressor by variation in blade number, or solidity, in the rotating blade rows.
A further characteristic of the preferred embodiment is that there are no stationary blade rows situated between the rotating blade rows. Furthermore, the centrifugal impeller is an integral unit that all blade rows rotate together, at the same speed and do not change in relative position from each other. It should be noted, however, that the impeller may be assembled from separate pieces.
FIG. 1 is a cross section of a conventional gas turbine engine. It is marked "Prior Art."
FIG. 2 is a perspective view of a conventional centrifugal impeller. It is marked "Prior Art."
FIG. 3 is a cross section of a centrifugal impeller incorporating this invention.
FIG. 4 is a perspective view of a centrifugal impeller incorporating this invention.
FIG. 5 is a representation of the aerodynamic stream lines of the gas flow on a centrifugal impeller.
FIG. 6 is a cross sectional representation of a radial impeller blade and a non-radial impeller blade in phantom.
FIG. 7 is a plan view of a compressor blade designed as a twisted sheet.
FIG. 8 is a perspective view of a singly highly leaned blade following optimal streamlines on an impeller hub.
FIG. 9 is a perspective view of a single conventional blade on an impeller hub.
FIG. 10 is a perspective view of a blade set incorporating this invention on an impeller hub.
FIG. 11 is a perspective view of several radial impeller blades.
FIG. 12 is a perspective view of several highly leaned impeller blades.
FIG. 1 shows the gas flow path through the central part of a gas turbine engine with a conventional axial-centrifugal compressor 20. Air from the inlet 21 travels through a series of axial stages of rotating blades 24 and static stators 22. These rotating axial stages drive the air forward and thereby compress the air in an efficient manner. After the air passes through the axial section of the compressor 20, the centrifugal impeller 26 drives the air outward and further compresses the air prior to its entry into the diffuser 28 and the combustion area 30. At the centrifugal impeller 26, the air volume is contained by the impeller itself and the impeller shroud 23. The compressed air is heated in the combustion area and travels through the turbine nozzle 32 and the rotating turbine rotor 34 where work is recovered from the high temperature highly compressed gas.
FIG. 2 is a perspective drawing of a conventional centrifugal impeller 26 as shown in cross-section drawing FIG. 1. Rotating integral blades 38 can be described as twisted sheets designed to compress air in a centrifugal gravitational field. Splitter blades 40, which are partial versions of the larger continuous blades 38, prevent excessive diffusion of gas flow as the air channels increase in size with the increasing impeller circumference from the air inlet 42 to the exit 44. It should be noted that modern impellers are generally machined in one piece.
Air enters the centrifugal impeller 26 in the axial inlet area 42. The air entering at the inlet has been compressed by the axial compressor stages upstream of the centrifugal impeller. The air, at the inlet, is therefore moving in a direction parallel to the axis of rotation and is already highly compressed. The inner flow path of the air in the impeller is formed by the impeller hub 27. The air itself is driven forward and compressed by the impeller blades 38 in all areas of the blade from blade root 29 to blade tip 31. As the air proceeds through the centrifugal impeller, the flow direction changes from parallel to the axis of rotation to perpendicular to it in all directions. The air, by the time it reaches the exit 44, is moving primarily outwardly from the axis of rotation and no longer moving along that axis. The flow field at that point may be described as a centrifugal flow field, in that the primary direction of the air at the centrifugal impeller exit 44 is tangential Impellers of the conventional type as here shown have several restrictions placed upon them which limit their efficiency. These will be more graphically described below, but reference to FIG. 2 is encouraged.
FIG. 3 is a cross section of a centrifugal impeller 36 incorporating this invention which may be installed in the compressor of FIG. 1 in place of the conventional impeller 26. As in the compressor of FIG. 1, air enters at the compressor inlet 21 and passes through a series of rotating axial blade stages 24 and non-rotating stators 22. The centrifugal impeller 36, however, is divided into three novel flow regions which will be more particularly described below. Upon passing through the rotating centrifugal impeller, the air travels through a diffuser 28, a combustion section 30, a turbine nozzle 32, and a turbine rotor 34. Work is taken from the high temperature highly compressed gas by the turbine as in a conventional compressor. An advantage of the invention is the ability of the novel impeller 36 to be substituted in the compressor 20 for a conventional impeller 26 without the additional cost of engine redesign.
FIG. 4 shows a perspective view of the centrifugal impeller of FIG. 3 embodying this invention. This centrifugal impeller 36 is made up of three blade rows 46, 48, and 50. The air enters through inlet 42 and exits through exit 44.
The creation of the three individual flow regions allows for optimization of centrifugal flow characteristics for efficient flow. The first region is an independent blade row 46 called the inducer having mostly axial characteristics. The second blade row 48 is a transitional or mixed flow region which has progressively less axial and more centrifugal characteristics as the radius of the impeller hub 27 expands. The hub 27 is defined as the impeller surface at the roots 29 of the blades. Flow region 50 is a primarily rotating radial flow region, or exducer, in which the air flow is directed primarily outward from the axis of rotation rather than along the axis of rotation as it is in an axial row.
The significance and benefits of the design may not be intuitively apparent from this drawing. They will be understood, however, after discussion of the basis of the design parameters below. By dividing up the centrifugal impeller into three regions of differing blade numbers, a maximum possible efficiency is reached, and the efficiency greatly elevated above that possible in the conventional centrifugal impellers.
Compressors are designed to produce a specific pressure ratio from air inlet to air exit. In turbine engine final stages where centrifugal impellers are used, it is most efficient to force the airflow to diffuse at a generally constant rate. This means that the flow speed decreases and air pressure increases at a generally constant rate from blade inlet to exit. If the diffusion rate is too high, the impeller will not pump efficiently and air flow will separate near the hub resulting in increased losses.
FIG. 5 is a representation of aerodynamic streamlines of optimum air flow patterns within the flow volume of a centrifugal compressor. The air flow patterns have been circumferentially unwrapped and simplified as an aid for clarity of understanding. This view should be considered as a two dimensional representation of a three dimensional flow. The streamlines have been optimized for a particular pressure ratio impeller, but the manner of the optimization as described below is generally applicable to centrifugal impellers. The streamlines have been optimized to produce a closely matched rate of diffusion at blade root and tip and for production of an evenly increasing pressure ratio. flow. These factors provide for an efficient flow.
Lines 52 represent the optimum air flow pattern at the tips of the impeller blades. The tip is that portion of the impeller blade farthest away from the impeller hub. Lines 54 represent the optimum air flow pattern at the root of the impeller blades. The air flow along the impeller is represented by these lines, and, since the flow is continuous around the circumference of the impeller, an infinite number of lines may be drawn.
Conventional impellers are not able to follow the optimum streamlines required to produce a most efficient flow. In modern conventional centrifugal impellers, each impeller blade constitutes an individual twisted sheet of metal that runs from the forward gas inlet end of the impeller to its aft end or gas exit. Blade 38 (FIG. 2) is generally radial, at least at the inlet, in that it is made to follow a radial line from the blade's center of rotation to the tip or outermost edge of the blade. In conventional centrifugal impellers, air tends to diffuse at a much higher rate near the impeller hub 27 than at the tip 31 of the blade in the inlet and central portions of the flow path.
Diffusion is defined as a decrease in fluid velocity and an increase in fluid pressure. The amount of diffusion done by an airfoil upon air is proportional to its velocity relative to that of the airstream and to its blade turning. Blade turning is the change in flow angle of the flow passage formed by two adjacent blades.
More diffusion occurs at the hub than at the tip of a radial impeller blade. The reason for this is that the speed of rotation of a rotating object increases from the center of rotation to its outermost point. Therefore, the blade tip 31 is at a higher velocity and centripetal acceleration than the blade root 29. The gas, therefore, travels at a higher velocity near the blade tip 31 than at the root hub 29 of a generally radial blade.
To compress a gas efficiently in a flow field, one needs to compress the gas at a relatively constant rate from blade root to blade tip as the gas passes through the compressor. It is inefficient to allow diffusion to occur at an inconstant rate as this tends to increase turbulence and decrease the effective pressure ratio of the compressor. Furthermore, a high rate of diffusion near the hub results in airflow stagnation and stall.
As shown in FIG. 5, the optimum aerodynamic profiles of impeller blade root and tip air flows differ if one attempts to maintain relatively equal rates of diffusion at the root and tip. The reason that the optimal profiles differ is because the airfoil forces applied by the blade differ. As stated above, the absolute velocity of the blade tip is increased over the blade root as dictated by the radial length of the blade from the center of rotation. This is because in each individual rotation, the circumference of the circle drawn out by the blade tip is larger than the circumference at the blade root. This difference in circumference decreases as the impeller becomes more centrifugally shpaed. At the air outlet 44 there is no difference in circumference since the entire blade is at the same radius from the center of rotation. For most of the blade length, however, the blade tip travels a longer distance during each rotation, and therefore is travelling at a faster velocity than the blade root.
The blade 61 depicted in solid cross section in FIG. 6 is a radial blade. The tip 31 is found to be directly over the root 29 in a constant cross sectional plane. As a result, blade tip speed across the airstream is substantially greater than the blade root speed. It is evident that a radial blade, with a uniform blade angle, will not produce a uniformly pressurized flow during rotation because of the effects of the blade tip speed being elevated above the blade root speed.
In order to vary the work done upon a fluid independent of airfoil velocity, the blade angle, in respect to the fluid flow must be changed. As the blade angle in the flow changes, the amount of work done upon that flow is also changed. It has been deduced that, if the blade root is made to do less work upon the fluid flow than the work done by the tip, the effects of the higher tip speed may be offset and relatively equal rates of diffusion may be established both at the hub and at the tip.
Application of the principle of independent design of blade root and blade tip results in the manufacture of blades such as the blade shown in FIG. 7. This blade may be described as a twisted sheet. Such blades have multiple independent profiles resulting from a twisting of the blade tip relative to the blade root. The resulting blade has profiles which are changed continuously from the blade tip to the blade root. In this way, a continuous blade form is maintained. The result of this design characteristic is that the blade tip is positioned a distance away circumferentially from the blade root and is said to lean.
Therefore, in order to compensate for the difference in diffusion between the hub 27 and the blade tip 31, conventional impeller blades are designed to `lean` from hub to tip off the radial line from the axis of rotation. Lean is defined as the amount that a blade tip diverges from a radial line drawn from the axis of rotation at a constant axial distance. This is shown by blade 63 in FIG. 6. Conventional impellers cannot, for reasons discussed below, utilize lean to its fullest potential in order to provide a more controlled rate of air diffusion from blade root to blade tip.
Return now to FIG. 5 which displays optimum air stream profiles at the tip and root of a centrifugal impeller blade. Matching impeller blade angles to any pair of profiles from each of the groups of tip and root profiles produces a continuous impeller blade 51 with theoretically equalized diffusion for a more uniformly pressurized flow. At the inlet portion of the compressor, which is at the top of the figure, there is a large diversion in the angles of the root and tip streamlines. As a result of the streamline diversion, the inlet of blade 51, as can be seen in perspective in FIG. 8, shows a very large lean of the tip over the root. This lean decreases as the blade progresses along the airstream and the profiles cross. However, after crossing of the profiles, the lean begins increasing once more. Although the streamline profiles in the centrifugal portion of the impeller become very similar forms, the upstream air profiles require a large lean, which is carried through to the impeller exit. A blade like this could theoretically produce a controlled diffusion flow path. However, a blade formed in such a manner is nearly impossible to produce, and if produced, would be inefficient in actual usage and extremely fragile.
To manufacture a highly polished continuous surface, as required for any thin aerodynamically sound airfoil, precise machining is required. In FIG. 12 can be seen partial sections of a series of several highly leaned blades 51 upon an unwrapped rotor hub. To machine the passage 66, it is difficult to get any sort of machine tool down to the base of the blade to properly form it without destroying the adjacent blade. The combination of blade lean and blade twist along the hub serves to make the underside of the blade roots inaccessible. This is not true with radial or nearly radial blades 60, as shown in the comparison FIG. 11. Tools may be more easily let down betweem the blades to machine the surfaces. This manufacturing difficulty has restricted blade lean to less than about 15°.
Manufacture would not, however, be the sole problem with the highly leaned blade 51 (FIGS. 5 and 8). In modern compressors, centrifugal impellers rotate at speeds up to 90,000 rpm and accept inlet air at supersonic relative velocities. FIG. 6 is a blow-up cross section of impeller blades at an impeller inlet. A fully radial blade 61 is shown in solid line. The center of the blade 61 follows a radial line from axis of rotation. A non-radial blade 63 can be seen in dotted lines with lean such as has been discussed. The leaning blade 63 is subject to centripetal acceleration which acts upon the blade to create a force which would tend to straighten that blade into a radial blade. This force is a major stress upon leaning rotating blades.
The centripetal acceleration produces a high stress in the leaned blade 63 at the root near the hub. In practice, the stress in centrifugal impeller blades restricts lean to less than about 12°-15°.
As an explanatory observation, a pencil spun on a string tends to remain straight out from the axis of rotation. Such would also be true of the blade tips of an impeller. Therefore, a radial blade such as 61 would have very little bending stress brought on the root; the blade would be in tension and would maintain the straight, outward rotational position. However, with a highly leaning blade 51, the forces acting on the blade would tend to straighten it, and therefore, at the hinge point which occurs at the root, the blade would be in bending as well as in tension. A leaned blade therefore has a higher maximum stress load than a radial blade rotating at the same speed.
A further disadvantage of large blade lean as in blade 51 is found only in modern transonic compressors as used for the most efficient aircraft gas turbines currently produced. In such compressors, airspeed near the impeller inlet is at supersonic velocities. The rotating blades are therefore subject to supersonic shock waves. These supersonic shocks in combination with blade lean greatly complicate efficient design of flow passages for supersonic relative velocities. Therefore, the large blade required in current impellers make efficient supersonic design very difficult.
As has been previously discussed, blade speed increases as one moves radially away from the center of rotation. The flow at the centrifugal exit, however, is completely different. Air flow is directed centrifugally outward from the axis of rotation. Therefore, both the blade tip and the blade hub are rotating at the same velocity since they are at the same radial distance from the axis of rotation. In order to produce efficient flow, blades at the centrifugal exit should be virtually perpendicular to the hub. Therefore, connecting the optimized air flow profiles for blade 51 with a continuous blade with reasonable lean at the inlet results in an inefficient exit 58. Such an exit would result in a greatly distorted and turbulent flow leaving the impeller exit. Air leaving the impeller exit leaves the centrifugal flow field created by the impeller and goes to a stationary diffuser. Turbulent exit air is very difficult for a diffuser to handle efficiently.
Returning now to FIGS. 5 and 8, it has been shown that the non-radial continuous blade 51, is inefficient. Such a blade could not easily be constructed, and if it were constructed, would be severely limited as to possible rotation speed because of bending stress.
Conventional impellers are therefore a compromise, as shown by conventional blade 38 in FIG. 9. Blade 38 does not follow the optimum profile at either the blade tip or root. Therefore, the rate of diffusion of the fluid will be somewhat uneven, both from the hub to the tip and axially along the length of the blade. This compromise allows for the construction of an adequate blade, with some lean and a proper centrifugal outlet. The flow pattern of the air leaving at the air exit has turbulence and secondary flow because of the uneven work done and a high rate of diffusion.
A further problem with conventional centrifugal impellers is that as the hub radius increases from inlet to exit, the blades diverge. This divergence results in wider air passages between the blades and greater air diffusion. The air not being effectively worked on by the blades tends to slow down, or diffuse, this decreased velocity results in greatly increased pressure. The pumping action of the compressor is made less efficient by a rapid increase in diffusion.
Conventional impellers have tried to limit this excess diffusion through the use of splitter blades 40, FIG. 2. Splitter blades 40 are foreshortened versions of the conventional continuous blades 38 that go from impeller inlet to exit. The splitter blades begin downstream of the inlet and end at the gas exit where the continuous blades end. Such foreshortened blades which work on the fluid in the channels between the continuous blades, allow for an increase in efficiency. However, since splitter blades must be directed in concordance with the continuous blades and are best placed in the middle of the flow passage formed by the continuous blades, design compromises are made which limit their efficiency. Specifically, splitter blades cannot be completely matched to the gas flow in order to entirely control excess diffusion.
An attribute of the conventional blade is, therefore, that air tends to diffuse too quickly near the hub. Although blade 38 is an improvement over a purely radial blade, it is still not as efficient in producing a uniformly pressurized flow as the theoretically possible continuous centrifugal blade. The conventional blade is a forced compromise due to the factors listed above. A conventional continuous blade, therefore, is limited to less than 15° lean which is insufficient to prevent excess diffusion at the hub.
To the right of FIG. 5, are three blades, 46, 48, and 50, which provide for a greatly improved airflow of high efficiency and follow more closely the optimum blade profiles. All three blades are machineable and mechanically stable as shown in perspective in FIG. 10.
An advantage of the invention is found in its use of several blades in place of the single centrifugal blade. The several blades allow for re-initialization of flow profile combinations along several portions of the airstream. This allows blade angle to be more efficiently matched to the optimum theoretical flow profiles.
The flow shown in FIG. 5 can be considered a continuous flow that can be divided into infinite streamlines. Therefore, by re-initializing the flow profile combination, one allows the blade angles to be matched to different streamlines in an optimum manner. A continuous blade is incapable of reinitializing flow profile combinations since it is relegated to following only one set of streamlines for the entire flowpath of the impeller.
The use of multiple blade rows allows for greater control of air flow, much as if a single continuous blade could be leaned beyond the 15° limit that has been discussed above. Effectively, a continuous blade following the same air flow characteristics would have much greater lean.
The first blade row, or inducer, 46 is a leaned blade row having mostly axial characteristics. In order to achieve high efficiency, two major design principles have been followed in addition to those generally used in designing a compressor blade row.
The inducer stage has been so designed as to follow the optimum streamlines shown in FIG. 5. The inducer blade row is thereby designed to produce a particular pressure ratio flow and to minimize the difference in the rates of diffusion at the blade tip and the blade root. This is done by following different blade angle profiles at the root and tip. By following the optimum streamlines, the impeller hub and blade root area have been unloaded aerodynamically in relation to the tip. If the hub was not unloaded relative to the tip, unwanted pressure rise and airflow stagnation inefficiencies would occur, because of the small flow area and the slow absolute velocity of the blade at the root. The rate of diffusion at the blade root and the blade tip is substantially equalized, that is, more nearly equal, if the inducer stage is designed according to the optimum streamlines. The axial length of the blade, however, has been foreshortened so that lean, which has been used to equalize the rate of diffusion, is restricted to within allowable geometric and aerodynamic limits.
In a further aid to efficiency, the air pressure leaving the blade row of the inducer 46 is equalized. This means that air pressure from impeller hub to shroud leaving the blade at its trailing edge is relatively constant.
The inducer stage, therefore, has been optimized for the inlet area of the impeller. Following the inducer stage, there is a short axial gap 47 (FIG. 10) where the airflow is not further compressed by the impeller. This axial gap allows the airflow to mix and makes possible the change in geometry of the following blade row. A transitional stage 48 is designed according to the optimum flow characteristics of the central portion of the impeller flow path.
The transitional stage 48 takes the flow from the more axial forward portion of the impeller to the more centrifugal area approaching the exit stage. This blade row 48 also follows the optimum streamlines shown in FIG. 5. The blade row is leaned radially to allow for a relatively constant, controlled rate of diffusion from blade root to blade tip. As with the inducer stage, the blade root follows a different blade angle profile than the blade tip, thereby allowing the blade to compensate for the difference in rotational speed between the root and the tip and the inefficiencies that would be caused by rotational effects. At the blade row exit, the air pressure is held relatively constant by this design.
The use of diverging blade angle profiles, or optimum streamlines, results in blade lean. As with the inducer stage blade, axial length is determined so as to restrict lean within tolerable limits. By following the above criteria, a much more efficient transitional region is created. In a continuous blade, the transitional region must be compromised to suit the aerodynamic and mechanical structure requirements of the air inlet 42 and exit 44.
As with the inducer blade row, there is a short axial gap 49 following the transitional row 48. This axial gap 49 makes possible the change in geometry of the exit row 50 and air flow mixing in between rows.
The constant pressure airflow that leaves the transitional stage, enters the exit stage 50, or exducer. As with the transitional stage, the exit stage can be wholly optimized for that area of the impeller. Since the airflow follows a centrifugal flow path for most of the length of the exit blades 50, an efficient exit allows the air to be centrifugally thrown outward from the impeller into the stationary diffuser. An efficient way of doing this is by having the blades placed perpendicular to the hub at the outlet. Since these blades at the exit are at the same radial distance from the center axis of rotation, any lack of perpendicularity is referred to as rake rather than lean to avoid confusion. What lean here occurs is described in the relationship of the blade's exit position to the upstream blade position. The lean limitation problems discussed above are less important in the exit blade row since, in relation to centripetal acceleration, the blade is firmly held along its side and is more resistant to bending loads. Therefore, stress is a less important factor in the exit blade row than in the preceding blade rows.
The exit blades 50 must still have some lean in order to follow the optimal flow profiles as shown in FIG. 5. As with the prior two blade rows, diffusion of the fluid is maintained at a controlled and relatively constant rate from blade root to blade tip. In addition, upon exiting the impeller, the fluid pressure is relatively constant throughout the exit area.
It is therefore shown that the lean at both the leading and trailing edges of the stages of the multi-bladed impeller is much reduced from that which would be required of the conventional impeller blade designed to achieve the same or similar controlled rate of diffusion across the blade height. The improvement thus shown allows for the optimization of blade flow profile with acceptable lean.
Efficiency requirements are thereby met in each of the three blade rows so that the flow produced by the multistage impeller is at a much higher level of efficiency than that of a conventional impeller A continuous blade type impeller cannot cope with either the geometric or the aerodynamic problems in as efficient a manner.
There are, however, additional improvements that stem from use of the multistage impeller. Since there are three distinct blade rows, the number of blades in each blade row may be varied to match the volume of the flow area, the rotational speed, and the pressure ratio required of each stage. The separate blade rows may be adjusted circumferentially with respect to each other for maximum efficiency. Further, they may be manufactured so as to allow the leading edges of trailing blade rows to begin upstream of the preceeding blade row's trailing edges.
In each blade row, the blades acting upon the fluid are matched to the flow area in which the blade row is also varied in order to produce a controlled rate of diffusion as the air passes through the impeller. The matching of both blade number and blade shape to optimum flow characteristics greatly aids efficiency. As discussed above, conventional blades cannot achieve as high a level of efficiency since the only change in blade number, or solidity, may be made by the addition of splitter blades which can only follow the compromise flow path of the continuous blades.
It must be additionally noted that all three blade rows are easily machineable. The impeller itself may be manufactured as a single piece or as multiple pieces to be assembled. A further advantage of this design approach is to allow different materials for the front and rear blade rows which can be machined separately and which can optimize the material selection for the stress and temperature levels of that location. In the preferred embodiment of the invention (FIG. 3), each blade row (46, 48, 50) is machined as a separate piece.
In summary, by allowing blade number to vary between blade rows and by individually optimizing the blade rows according to the different flow areas of the impeller, the inefficiencies that have previously plagued centrifugal impellers may be largely corrected. It has been shown that the aerodynamic and geometric constraints upon the conventional impeller are overcome through the use of the multiple blade row impeller shown.
Theoretical calculation and experimental results show that minimizing the rate of diffusion from blade tip to blade root and producing relatively constant pressures between each blade row as discussed above offer a significant improvement in impeller efficiency. Depending on the pressure ratio required in the engine for which a centrifugal impeller is to be used, the number of blade rows on the centrifugally shaped hub may be varied. For smaller impellers only two rows may be necessary, while for larger impellers pumping a higher pressure ratio, more than three blade rows may in fact be required.
Described above is a centrifugal impeller which significantly increases the possible aerodynamic efficiency that may be achieved by centrifugal impellers. Centrifugal impellers embodying this invention may now be more universally used in gas turbine engines.
Centrifugal impellers of the type embodying this invention may be used as highly efficient final compression stages in virtually any gas turbine application and allow for reduction in total engine length by elimination of axial stages and their accompanying stator portions. This allows for a significant reduction in weight in gas turbine engines and a concurrent increase in the thrust per weight ratio of said engines. Such increases result in increased efficiency and decreased fuel consumption.
While the invention has been particularly shown and described with reference to the preferred embodiments thereof, it will be understood by those skilled in the art that various changes in form and detail may be made therein without departing from the spirit and scope of the invention as defined by the appended claims. The text of the application has described a design procedure which has been followed by the inventors and is thought superior to previous design procedures both in its method of use and the product of its application. Various similar centrifugal impellers for both gas turbine and non-gas turbine uses may be designed and constructed embodying the invention disclosed.
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help replacing drawer pull with shank
I have some old brass drawer pulls to replace in my kitchen. My problem is that they have an extension that goes into the drilled hole and therefore the hole is larger than tthe standard screw size. Please see photo.
My questions: Does anyone know what the term is for this kind of pull or where I could find a replacement? If I cannot find a suitable replacement I am considering spray painting them.
I had this issue with an old dresser I refinished. I ended up finding pulls that covered the existing holes, so I had to drill new holes for the new screws. You can see in the pic how the flat pieces on the ends cover the old holes. I never see the inside of the drawers, so no big deal. A cabinet door may be different since you would see the old holes. You could maybe fill them with something.

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Federal And State Officials Are Trying To Protect Ash Trees From Emerald Ash Borer Beetles
Federal and state agriculture officials are setting 568 traps across Kansas to detect and prevent the spread of the emerald ash borer.
The beetle has killed millions of ash trees since it was first discovered in North America in 2002.
In Kansas, it was found in Wyandotte County in 2012 and Johnson County in 2013.
Kansas is participating in a U.S. Department of Agriculture survey to monitor known infestations and detect unknown beetle populations.
The state plans to set up 80 traps in Barton, Bourbon, Douglas, Ellsworth, Leavenworth, Marion and Osage.
The USDA is also putting some up. Traps are coated with a nontoxic glue.
Kansas has implemented an intrastate quarantine for firewood, nursery plants and mulch for affected counties to prevent further spread of the pest.
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Awareness and Free Will (for AI)
In Part 5 I described how it is theoretically possible to model intelligence by observing its emergence from within a digitally-simulated universe. The cybernetic model thus produced would eventually accumulate a near-infinite number of logic steps, which would produce an empirical model of consciousness (if-then logic) that would most likely bear some resemblance to the Constructal Pattern.
Yet, there is more to consciousness than binary logic. An AI with enough logic steps and decision-making ability might have enough information to become self-aware, but it wouldn't necessarily have the will or the inclination to do so.
A logic-based AI could never make independent decisions, raise questions, or demonstrate spontaneous behavior. It would have no motivation to ask questions like, "What is the nature of my own existence?", without receiving explicit instruction to do so. If logic-based intelligence is not issued a definite command, then it has nothing to act on — null input produces null output… Which isn't "life". Dreams and other sometimes illogical things have a way of keeping us sane; without them, we wouldn't be human. So if we really want to reach the Singularity and build Strong AI (i.e. replicate human consciousness In Silico), then we need to account for not only the straight lines of logic, but also for the meandering flows of feeling, chance, and intuition.
Binary Refined
Creating virtual intelligence is not something we want to mess up, nor is it something we can do overnight. So, rather than creating some form of intelligence that lacks emotion and is rooted in binary decision-making ability only, let's get it right the first time — let's create something like us. That should be the only goal of advanced AI research – to understand and replicate human consciousness – not merely to reduce it to numerical logic.
So we can't create Strong AI from the bottom-up with logic alone; we also need to let unattended forces of entropy do their work. For this, we could present AI with a constant stream of 'random' input to increase its variance – basically, to 'let its mind wander' by providing it with permutations of its own 'thoughts', essentially granting it a subconscious.
More variance could be added to the system letting the AI choose between a number of possible outputs for any given input, and selecting the most 'optimal' outcome. The ensuing spontaneity would create the functional equivalent of free will.[1] Also, to add some extra structure to what otherwise might be random variance of little consequence, what if these 'random' decisions were directly influenced by the input stream in the form of coordinated environmental feedback? What I'm essentially trying to describe is like an echo chamber of thought; a digital environment for the mind that builds itself in reaction to observation. I would argue that the mind needs this to grow. In any case, given enough 'random' inputs and feedback loops, the machine's logic could 'never' be predicted – it would have free will.[2] Thus, spontaneous behavior (i.e. free will) can be written as binary instruction; the only requirements are an extensive ruleset (logic) and a constant stream of random inputs[3]. The logic would come from the AI research discussed in Part 5. The input stream, or randomized environmental feedback, might be generated using cellular automata or genetic algorithms.[4] Still, this is a markedly different way of achieving consciousness. Creating life from pure logic may turn out to be an impossible (or at least very difficult) task.
Before this series concludes with Part 7, you might also want to check out this forum thread, where I discuss Earth's humanitarian responsibilities leading up to the Singularity. I think people tend to get distracted by abstract notions of the Singularity and machine intelligence and forget about real-world problems in the process… To quote myself, "We don't want to invest in such distant futures that we forget about the present." As important as exponential change is, we also need to keep it in perspective.
Next entry: Universal Duality
Table of Contents
- Six Blind Men and an Elephant – "All religions, arts and sciences are branches of the same tree."
- The Physics of Consciousness – Consciousness explained in terms of electromagnetism and information.
- The Holographic Universe – The behavior of photons may indicate that we live in a holographic universe.
- Simulation Theory – How to emulate consciousness on a computer by allowing it to evolve from scratch.
- Artificial Intelligence – How to create self-aware, free-willing artificial intelligence.
- Awareness and Free Will – How free will can arise from binary decision-making (i.e. pure logic).
- Unified Field Theory – Living systems balance entropy and negative entropy by employing a unique mode of parallel processing.
- If the AI had an innumerable number of choices – so many that any given input corresponded to a near-infinite number of probabilistic outcomes, then its behavior would indeed appear to be completely random.↵
- This is similar to how Stephen Wolfram describes free will in his book A New Kind of Science.↵
- "Entropy generation"↵
- Of course, the balance between random inputs and logic would need to be carefully controlled. Consciousness ultimately consists of the process of balancing extremes: Logic and spontaneity, 'Yin' and 'Yang'. Too much in either direction and the system becomes unstable.↵
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Article | May 31, 1995
Magnetic particle controls
Sofstep® magnetic particle clutches and brakes from Magnetic Power Systems, Inc. (Fenton, MO) provide smooth, controllable torque for power transmission and tension control applications.
Available in a range of sizes with torque ratings from 2 to 240 lb-in they are compatible with all of the company's tension control systems.
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Real Mom Stories
Early Favorites
09.09.10 3 weeks old
My Birth Story
09.01.10 2 weeks old
Real Life Stories: Pregnancy Complications
Three mothers share the hurdles they faced along the way.
It's A Boy!
08.21.10 Welcome Baby Tucker
Family History Week
08.12.10 Week 39
Exploring Cloth Diapers
08.05.10 Week 38
Baby Shower
07.29.10 Week 37
Looking Back
7.27.10 The end of the road
Deferring My Entry
The right decision for the right reasons.
Midsummer brain-dump
07.16.10 Week 35
Time, Time, Time
7.15.10 See what's become of my life…
Cue up the (travel) Cribs
07.08.10 Week 34
The Bookworm's Dilemma
7.1.10 Week 33
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Motel Metro
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Bonjour from Canada...
... Mario Kart in the living area. We played, and I won, and then we headed out for food.
The immediate impression I got of Montreal was that there was not a great deal to be there, and was grateful for having booked just two nights. After speaking to a few people in the hostel however, everyone spoke extremely highly of the city. That evening, we headed out as a hostel to climb a large hill in the park that rewarded climbers with a fantastic view of the city skyline. At ...
Last day in Montreal
Terry's birthday, so we went out to brunch. Halfway across town, deep in the suburbs, to a great restaurant. I don't know how he finds these places. It had an extensive French influenced menu, but he only wanted pancakes with a side order of potatoes, and a bowl of hot chocolate.
Then we caught the train into the Old Town, and and spent a couple of hours at the Montreal History Museum.
We are catching the train to Washington DC ...
Walking tour of old Montreal
... and grab on your car to steal them and we would be lost without our Jill. Anyway Richard keyed in the address for the Information Centre in old Montreal so we can see where to book a walking tour of old Montreal. I followed the map down Rue Peel to Dorchester Square (Richard also found it with Jill) and we just missed the 11am tour of old Montreal East section. This was booked out and we have to pay for the tours as there are no free ones. Young chap behind ...
Montreal Fun!!
... the Pantheon in Rome with its immense colonnaded edifice and domed ceiling. Since it was the weekend we were unable to take a peek inside but apparently the interior has 32 marble columns and coffered 20m ceiling in Italian renaissance style. The grandeur of this building means it could very easily be mistaken for a city hall or another notable government building rather than a bank. It is very impressive. On the southern edge of the square there were a few tacky tourist ...
The End of Part 2: Post-Trip Reflection
... and influences this summer as well as describe the main events of my trip.
Logistics Reflection
Pre-Departure Prior to leaving for South America, I was working full time in New York. Our flight actually left only a day after my internship ended. It was good that I had done the exercise of planning the major parts of my trip and booking flights back while I was at Babson before work began. One issue with the pre-departure however came ...


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Slashdot videos: Now with more Slashdot!
We've improved Slashdot's video section; now you can view our video interviews, product close-ups and site visits with all the usual Slashdot options to comment, share, etc. No more walled garden! It's a work in progress -- we hope you'll check it out (Learn more about the recent updates).
Comment: Re:DeLorian problems (Score 1) 436
Why don't the British make computers?
I'll have you know a Brit, Charles Babbage, designed the first computer. Now, he may have never actually managed to get the thing built so it worked, but...oh never mind...
Comment: Re:for all the founding fathers did right (Score 4, Informative) 601
RIAA May Be Violating a Court Order In California 339
from the play-nice-now dept.
Comment: Re:Won't work, even with all the good faith... (Score 1) 179
Supreme Court Won't Hear ACLU Wiretap Case 323
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Stay Lifted, Novell Vs. SCO Can Go Forward 161
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UK Government Loses 15 Million Private Records 339
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Italian Judge Tells HP To Refund Pre-Installed XP 225
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RIAA Trying To Avoid a Jury Trial 183
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Explore the personal stories of Syrian refugees in Lebanon
Everyday lives in conflict-ridden Aleppo
Inside Story | 27 Mar 2014 19:38 GMT
It is blamed for wars and discrimination, yet also embraced as a means of resolution and integration.
Religion is the source of many arguments, while some studies suggest it is on the decline.
A conference in Qatar is promoting a message of interfaith dialogue, of religion as a means of global co-existence.
"This is very helpful in terms of breaking misconceptions, all the challenges we have in the peace-building process, the barriers to achieving peace, it is very important that we search for common ground," Rohaniza Sumndad Usman, founder of the Teach Peace, Build Peace Movement told Al Jazeera.
Blaming religion as the cause of conflict is an easy generalisation to make.
Fighting in Central African Republic is between Muslims and Christians; Buddhists and Rohingya Muslims are involved in the violence in Myanmar; the conflict in Northern Ireland had its roots in religion; and the Palestinian-Israeli conflict is seen as having a religious dimension.
But in all these examples, there are more fundamental driving forces - be it land, power or nationalism.
So is religion at the heart of conflicts around the world? And do different faiths have the will to work together for a common good?
Presenter: Mike Hanna
Guests: Professor Ibrahim Saleh al-Naimi - Chairman of Doha International Center for Interfaith Dialogue.
Archbishop Makarios Mavrogiannakis - Head of the Greek Orthodox Church in Doha.
Rabbi David Rosen - International Director of Interreligious Affairs for the Global Jewish Advocacy.
Source: Al Jazeera
Scientist and atheist Richard Dawkins is challenged on whether religion is a force for good or evil in the world.
Arts & Culture, Middle East, Religion
Will potential new legislation end Haredi Jews' special privileges or brew up a political firestorm?
Politics, Israel
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More than 800 people were killed and 65,000 displaced in religion-based election violence in 2011 in the central city.
Nigeria Decides, Nigeria, Goodluck Jonathan
More than 100 people were gunned down in Maidan Square a year ago, but investigations have failed to bring prosecutions.
Human Rights, Politics, War & Conflict
Religious practice involves ceremonial dancing, singing and body piercing - which are not allowed in mainstream Islam.
Religion, Europe, Albania
US announces it will slow American forces drawdown in Afghanistan amid increasing fears of Taliban-led civil war.
War & Conflict, Politics, Asia
It is a source of sustenance but also of tension and new political realities are now increasing uncertainty.
Egypt, Sudan, Middle East
A media post-mortem into the UK's surveillance report. Plus, why five years on in Argentina the media looks so familiar.
Media, Edward Snowden, Security
The untold story of how the Lebanese community overcame the odds and found their place in multicultural Australia.
Asia Pacific, Australia, Lebanon
How to keep a telenovela profitable and demanding sponsors happy while inspiring the production team to stay passionate.
Arts & Culture, Mexico, Latin America


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Flash Furniture Chiavari Chair Cushion for Wood and Resin Chiavari Chairs
Flash Furniture Chiavari Chair Cushion for Wood and Resin Chiavari Chairs
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|Product Type: Seat Cushion
|Country of Manufacture: China
|Assembly Required: Yes
About the ManufacturerFlash Furniture: Quality office furniture - at the speed of light. Flash Furniture takes pride in offering the highest quality office chairs and furniture at the best price that you will find anywhere. They proudly present an extensive selection of quality furniture for the commercial and home office. Flash Furniture offers a wide selection of office, hospitality, and restaurant furniture, available to ship within forty-eight hours – so you can get the support you need, right on time.
Flash Furniture Chiavari Chair Cushion for Wood and Resin Chiavari Chairs
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OUR SKU # FFC1120Chiavari Chair Cushion for Wood and Resin Chiavari Chairs is also sometimes listed under the following manufacturer numbers: LELCBLACK, LELCWHITE


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Dodge refreshed both of its retro-cool performance beasts, the Charger and the Challenger, for 2015. The Challenger, seen here, gets the choice of three engine options: a 3.6-liter, 305-hp V-6; a 5.7-liter, 375-hp Hemi V-8; and a monstrous 6.4-liter Hemi V-8 making 485 horses.
Dodge Packs Up to 485 Horses in the 2015 Challenger
The redesigned Challenger comes with three engine options for 2015.
This is McLaren's New Entry-Level Sports Car
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I Owned the Last Beautiful Lincoln
It's been 44 years since Lincoln built a beautiful car. I owned the last one, and I hope like hell the brand can pull off an honest...
Hybrid Big Rig Doubles the Mileage of Today's Trucks
The Freightliner SuperTruck improves fuel economy by 115 percent and cools the cargo compartment with solar power
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text: So things might start to get blurry. It's been more than a week since I actually was in Osaka. The only thing we really did this day was go to Osaka Castle and ride the Ferris Wheel. So we headed out on the Osaka subway line, which compared to Kyoto's subway, was a breeze to navigate. The subway to Osaka castle, exits directly to Osaka Castle Park. Cool fountain and slide at the front of the park View of the castle from beyond the outer and inner moat. We really need more moats in the United States. View from the 8th floor of Osaka castle. It really was a lovely park, so that was a really nice bonus as well https://fbcdn-sphotos-b-a.akamaihd...._=1431178066_b9f3acd7d1f2a08a7263ef48dbe29496 We then headed for a restaurant near Osaka Aquarium for lunch. Nearby there was a huge ferris wheel. Japan loves their ferris wheels. I saw at least 6 during the trip to Fu kuoka on the bullet train and two were in pretty small towns. The Ferris Wheel was pretty awesome and gave you great views of the bay and of the city. The worst part was that as we approached the top, it started raining and hailing so it was really loud in there and nerve-racking We then headed to America Town to do some shopping - mainly at record stores for my friend, but I also got to go to the Disney store for vinylmation. The area had quite a few interesting shops, including this gem which I'm pretty sure was not officially licensed. Sweet manhole cover. After that I mainly waited for Andy to finish record store shopping, and we went to dinner at Nataraj, an Indian restaurant with vegan options. On our way to dinner, we actually got lost, but fortunately found it in time. The japanese address system is ridiculous! Also some random thoughts about Japan. - The Japan address system is crazy. It's good Andy has a phone here or we would be lost all the time for sure. - No Diet Pepsi or Diet Coke. Boo! - Lots of Kawaii stuff here. Next up: ***uoka and Sumo!


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Steven M. Gillon is the resident historian of The History Channel and host of HistoryCENTER. Having taught at both Oxford and Yale, he is currently a professor at the University of Oklahoma.
Given the updated release of Steve Mariotti's classic The Young Entrepreneur's Guide to Starting and Running a Business on Tuesday, we decided...... READ MORE
Written by Doris Kearns Goodwin
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The game going from E1L7 to the title is a remnant from the hardcoded game code. The game uses E1L7 as the "user map" slot, and automatically thinks it's the last map of the game (resulting the game going to the title screen after finishing a user map).
It would sound like you're either running an older or otherwise erroneous version of EDuke32. Care to share any more details? Unless the posts above are yours as well.


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Originally written on Buffalo Wins | Last updated 11/10/14
DETROIT - SEPTEMBER 02: Buffalo Bills head coach Chan Gailey watches the action during the fouth quarter of the preseason game at Ford Field on September 2, 2010 in Detroit, Michigan. The Lions defeated the Bills 28-23. (Photo by Leon Halip/Getty Images)
If you were to pick the apex for Chan Gailey's tenure in Buffalo..what would it be? You'd probably pick the Pats win last year, wouldn't you? God, that seems so long ago. A dream...that we thought would springboard us into contention. Alas, it was nothing more than a trick. However, I think of that game being Fitz's best moment, so, I'll save it for when I write my obituary for him in March. To me, Gailey's Gatorade dousing moment came at last year's Redskins game. I wrote how it was just ironic how the Bills were sitting pretty at 4-2 and were facing the coach who pretty much used them to get a better offer from the Redskins. Washington was a disaster entering the game. They had John Beck as the QB and were only a year removed from the McNabb disaster. It just felt like poetic justice. Kind of like the nerd going to his high school reunion with a model chick and a high paying job and then seeing the hot girl -who dissed him all throughout high school- where now she ...
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Publisher's Description+
It's easy to make color sketch for photo. It also convert your photo to Oil Painting. You can adjust the hue, saturation, lighting, exposure for the photo, and also make artistic picture, such as realism, pop art, abstract. Certainly, it also can make black and white sketch for photos. The usage is very easy. Professional functions for photo sketch or color sketch, More specially, More powerfully! Make perfect work with a few clicks.
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text: I want to offer further discussion on the Dept. of Highways proposed closure of the left turn lane from Cat Creek Road on to Hwy 441. The recent information meeting at Franklin City Hall was attended lightly by property owners in the Holly Springs area. Those that did attend were unanimous in their disapproval of this ridiculous proposal. Not only was it ill thought out but would result in an even more dangerous result than what the DOT's bean counters have come up with. For those who did not attend the meeting let me point out the flaws in the existing proposal.


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Joel Heffner
Writer | Speaker
Home | Contact | Articles | Speaking | The Story Starter
Joel Heffner is a writer and speaker. His articles have appeared in such diverse publications as the New York Time and the American Kennel Club's magazine. He is the author of the Amphoto Guide to Wedding Photography. He frequently writes and speaks about photography.
Joel is the creator of The Story Starter where
you can find 3,423,651,840 (yes, he counted them) ideas for writing a
story. It was named as one of the 101 Best Websites for Writers by
Writer's Digest Magazine for 2008, 2012 and 2014.
He has spoken to numerous organizations, including:
Tech-to-Go Conference


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EI-LO offers designers, manufacturers, and apparel brands the perfect T-shirt at the perfect price point. We combine quality blank knit apparel with easy ordering, no minimums and immediate delivery. As a completely vertical manufacturer, we control every aspect of the process to ensure the highest quality products. Using 100% USA Cotton & Ring-spun Yarn our fabrics are softer, more stable and are USDA and NAFTA Certified. For more info please visit
I'm an avid reader of Shop-Eat-Surf because it's really the only online newsletter that I have found that is not only industry related, but also because it's not so "guy-centric." I find that a lot of the information I read on the site pertains to my business (as a swimwear designer) and keeps me up to date on what other companies and other women in the industry in general are doing which is not only inspiring but also helps me gauge the future direction of my business as well.
I feel privileged to read the Executive Edition because I know I am getting insider industry information before it hits the mainstream media channels. And it's always good to know what my friends are up to in the industry.- By Monica Wise, Founder, L*Space
It is common knowledge in our industry that there is one undisputed leader in reporting on the topics, businesses and trends that impact all of us the most, and it is shop-eat-surf.com. Their access to those who make our industry happen is second to none, and we value not only the content of their reporting but the editorial thought on what it all means both in the present as well as the future. If we were asked to give a rating, it would be five out of five stars.- By Craig Levra, CEO, Sport Chalet
MOSS ADAMS CAPITAL: Apparel and foowear market monitor highlights notable deals, stock prices and results.
Details on Industry Insight.
Press Release:
Volcom's third annual spring fashion show took place last Thursday at Volcom Headquarters VIP space. Volcom partnered with ELLE Magazine to present us with this amazingly fun event. The show featured 16 models showcasing both Volcom's Spring 2012 swim collection and a limited edition collaboration capsule with Volcomunity ambassadors, Posso.
Volcom's Spring 2012 swim collection holds several distinct looks, a color palette of brights as well as softer morphed tones, coupled with new silhouette shapes that accent dramatic highs and lows.
"The essence of our collection for Spring '12 comes from many places in the past, present and future," say Suzanne Vallely, Volcom Swim designer. "This SP2012 collection can and will take her as far as she wants to go."
The models walked the runway to the sounds fueled by Posso, who premiered brand new songs produced exclusively for the event. Their newest track, "Gypsy Love" started the night off with the runway show, followed up by a Posse DJ set that kept the energetic crowd captivated until the wee hours of the night.
POSSO (meaning: "I can") is an out-of-this world collaboration between best friends Marylouise Pels and Vanessa Giovacchini. Their collection embodies the true spirit of their day to night dressing: easygoing, slightly rebellious effortless California style, which was a perfect match for Volcom and their spring line.
Make sure you check out Volcom's Spring 2012 Swim and Posso collaboration, available at Volcom retailers in November. Special thanks to Bertenzen for providing amazing drinks to take us through the night – Rolf Binder, Tohu, Weihenstephaner, Birra Moretti & Prosecco Tiziano… Needless to say we had plenty of fuel for the party.
Check out some pictures from the event above.
Volcom is a modern lifestyle brand that embodies the creative spirit of youth culture. The company was founded on liberation, innovation and experimentation while remaining dedicated to the breakdown of established traditions. Volcom's avant-garde approach to clothing and branding has set it apart in the action sports industry and beyond. Please visit Volcom for more information.


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Days Inn And Suites York
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The Big Plane Ride
It was Jordan and Rachel's first time flying today. The flights on United left Harrisburg at 8
with a layover in Washington Dulles and arriving in Orlando at 12:30am. It was a late night but the kids LOVED flying
including Rachel who had several complete ...
Post-visit: The Indian School Cemetery
... war were not achieved." I think it's the closest I've ever heard the military or the US government come to admitting that we lost that war. Of course, there's not much mention of atrocities committed by the US military. And one display that is notably absent is any mention of the wars with the Native Americans and massacres committed by the US armed forces during that time. There are displays of the military activities during the "peaceful years" between ...
Post-visit : Back to my old home
... very ugly streets with metal hardware shops etc that look like they were built in 2 days. There is a little Middle Eastern store run by an Egyptian guy that looks interesting--but it's not very well stocked... I'd never visited the Mechanicsburg Museum, so I guess I'd better do it now. It's basically a one room old railway station, honoring the importance that the Cumberland railway played in the development of ...
York Fair
... back "home". Back after a year around the world and five years in Washington before that. But except for family ties and a few favorite places, I don't feel like I bear any special relationship to this place, or to any of the local culture. I feel like I'm on one long, tedious, sometimes gratifying, sometimes nostalgic, often yummy, mostly unwanted, yet also necessary and unavoidable, extended vacation in my hometown. ...
20,000 Women? "Wilt Hit on Everything That Moved"
... on our 2011 Harley Hillbilly Holiday, passing through coal towns whose better days were also in the past.
Ray us a good source for learning about coal mining; he grew up in an Eastern Kentucky coal camp and had a bachelors degree in mining engineering. If you ask Ray about bituminous coal, be prepared for a thorough explanation.
As we approach Hershey, Pennsylvania, the weather gradually clears. The sun even comes out and ...


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Hotel California
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Baja California - beautiful but a bit brrrrr!
... it was too. Run by Bonnie, Mexican by birth but with strong links to the US and speaking perfect English we felt immediately at home there, sheltered under her huge trees and on nice green grass. Bonnie's place is one of the fincas owned originally by her parents and features a sort of time share hotel in one corner, her house in another and lots of open farmland around the site. After a hiccup with the gas (which resulted in Bonnie giving us a Strelitzia cutting as a ...
But The Solar Panel is OK
... positive terminals, stopping the batteries from burning themselves up (and possibly the rest of the boat).
The lower wire is the culprit, the larger wire over it is the radar cable. The is where the wires go through the cockpit lazarette through that burned out hole into the ...
New Year's Day Winter Swimming
... at around 2:30 PM'ish and asked if we could use the machines, only our 2nd self-service laundromat in almost a year(!) :-) The immediate answer was "no!" as they were closing early, 3:30 instead of 7, fair enough on New Year's Eve. I managed to negotiate using just the washer and taking the clothes home wet. We chatted a little with the lady and she said she would be going to a "fiesta" to bring in the New Year (can't believe it's almost 2012!). Then, most surprisingly, at 3 ...
Opera in Ensenada Grande
... angle highlighting all the marine life. Encircling us is an incredibly huge swarm of millions of tiny guppy-sized fish resembling a swirling wide bridal veil. At one point we are completely enveloped inside the veil; when we gently swim through, the veil opens up and closes behind us again. AMAZING! Some larger fish actually follow us around. We don't want to leave Ensenada Grande!
Camping Day1: the night we slept in a bar.
... like bath water, I couldn't shake the feeling that I was walking though people's pee. There were some really awesome rick formations, and I guess we were at the place where a lot of pictures for post cards are taken.
When we finally got to the beach we were staying at, we ended up getting a truck+ trailer really stuck in sand, and spent the next hour digging/pushing it out! My job was to ...


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The Bohemian Hotel Savannah Riverfront, the latest boutique hotel by The Kessler Collection in Orlando, Fla., will officially open in Savannah on July 24, with a ceremonial ribbon-cutting will take place July 28 at 6 p.m.
ATLANTA - The Georgia Department of Labor (GDOL) reported today that the preliminary unadjusted unemployment rate in the metro Savannah area rose to 8.0 percent in May, up four-tenths of a percentage point from a revised 7.6 percent in April.
The Georgia Ports Authority's Board of Directors unanimously re-elected Stephen S. Green of Savannah to serve an additional one-year term as chairman for fiscal year 2010 and approved capital improvement projects that will increase capacity and efficiency.
Summer is here. And for many people, summer is synonymous with "vacation." If you have children or grandchildren, they're most likely on vacation from school, and if you've got the time and motivation, you may take a family vacation over the next few months. But there's one part of your life that should never go on vacation - and that's your investment portfolio.
ATLANTA - The Georgia Department of Labor (GDOL) reported today that the state's seasonally adjusted unemployment rate jumped to 9.7 percent in May, the highest rate ever recorded in Georgia. The jobless rate was up five-tenths of a percentage point from a revised 9.2 percent in April.
SAVANNAH - Savannah Technical College's Effingham Campus and EFACEC will host "Getting a manufacturing job with EFACEC" on June 24 at 5:30 p.m. at the Effingham Campus.
ATLANTA - The Georgia Department of Labor announced that 75,436 laid-off workers filed first-time claims for state unemployment insurance benefits in May, an increase of 68.7 percent from May 2008.
The author of an authoritative tome on the life of John Adam Treutlen was honored with the award named after the state's first constitutional governor Thursday night.
Joe Doyle, administrator of the Governor's Office of Consumer Affairs, has announced that the agency has entered into settlements with three different companies who allegedly held going-out-of-business sales that were not in compliance with Georgia law.
General Motors' bankruptcy won't have any impact on the local Chevrolet dealership, Fuller Chevrolet General Manager Tommy Arden said.
Two workshops entitled "Starting A Business" will be held during the month of June.
Business after hours was recently held at Microtel.
The Coastal Bank will present a free real estate tax credit seminar in Rincon on June 2.
ATLANTA - The Georgia Department of Labor reported that the unadjusted unemployment rate in the metro Savannah area was a preliminary 7.7 percent in April, up from a revised 7.5 percent in March.
After 43 years with Morris Multimedia, Karen Tanksley won't be starting her work day holding a cup of coffee in her Rincon office.
STATESBORO - The Georgia Southern University Museum recognized longtime supporter Planters Telephone Cooperative recently during the annual Georgia Association of Museums and Galleries Conference at the Nessmith-Lane Conference Center.
The Georgia Department of Labor announced that Effingham County's unemployment rate for December 2014 fell to 5.4 percent, down from 5.5 percent in November 2014.
ATLANTA - The Georgia Department of Labor announced the state's seasonally adjusted unemployment rate for December was 6.9 percent, down three-tenths of a percentage point from 7.2 percent in November. The rate in December 2013 was 7.4 percent.
The Georgia Ports Authority ended 2014 with growth in all cargo sectors, including a 10.2 percent increase in 20-foot equivalent container units (TEUs) and a 7.4 percent increase in total tonnage.
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See our store section for gifts by different stores
See our top gift ideas section for most popular items.
Create your own personal gift registry. Register for any item, from any store, for any occasion. Find the gift registries of your family and friends.
Ever find the perfect gift idea for someone, but their birthday was months away? We make it easy to remember your gift ideas.
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Your Spirit Personalized Confirmation Valet Box
Engravable Confirmed in Christ Dove Memory Box
Got Spirit? Confirmation Mug
Grace of the Lord Confirmation Cross
Personalized Confirmed in Christ Wood Frame with Dove
Confirmation Medal with Dove and Golden Inlay
Confirmation Prayer Jerusalem Stone Plaque
Personalized Confirmation Black And Gold Metal Frame
Confirmation Photo Frame
Bronze Finish Confirmation Memory Box
Personalized Dove Confirmation Cross
Pewter Confirmed in Christ Cross
Stained Glass Cross with Dove
Personalized Got Spirit Frame
Come Holy Spirit Photo Frame
Personalized Confirmation Prayer Glass Plaque
Sterling Silver Cross and Dove Name Disc Necklace
Trinity Metal Wall Cross
Sterling Silver Confirmation Dove Disc Pendant
Men's Cross of Peace Sterling Silver Necklace


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Paul in OK
its a oil filterRead All Reviews
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Can't beat OEM for fit and function. Great price to boot from RMATV, thanks!Read All Reviews
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I needed to replace my clutch and simply opted for the OEM clutch kit. I realize there are many options but OEM works just fine for me.Read All Reviews
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Lets face it when you do a motor rebuild its hard to keep track of what gaskets you need, this is a must for anyone rebuilding a motor. You are guaranteed to have every gasket needed, and will not be stuck waiting because you forgot to order one gasket!Read All Reviews
BRANDON in KS
works great way better than factory clutchRead All Reviews


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