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A diverging rocket engine nozzle has a system to allow ambient gases to flow from the outside to the inside of the nozzle's chamber. The system includes a plurality of coolant conduits adjacent the inside surface of the nozzle. The conduits are spaced apart to provide a plurality of vent openings which extends from the inside to the outside of the nozzle's chamber. A plurality of valves controls gas flow through the vent passages when the pressure outside of the nozzle is greater than the pressure directly adjacent the inside surface of the nozzle. The coolant conduits cool and shield the valves at their points of attachment to the outside of the nozzle.
1. A rocket nozzle structure for a rocket engine which has a flowpath for rocket gases extending axially through the nozzle, the nozzle structure including a casing having an exterior and having an interior which bounds the flowpath, the casing having a throat and a divergent region extending downstream from the throat, the divergent region having a high expansion ratio, and which comprises:
a casing having a divergent region, the casing including
an inner wall having a plurality of conduits for coolant which bound the flowpath for rocket gases, at least two of the conduits being spaced apart leaving an opening therebetween,
a plurality of vent passages extending from the exterior of the casing to the interior of the casing each vent passage extending through an associated opening between a pair of conduits;
an outer member attached to the inner wall which is adapted to support a seal element, the outer member being spaced by the conduits from the flowpath for rocket gases,
a plurality of seal elements, each of which is adjacent to at least one vent passage, the seal element extending axially from outer member of the casing and having a first end attached to the outer member and a second end movable between an open position which permits flow through the vent passage from the exterior to the interior and a closed position which blocks flow through the passage from the interior to the exterior, the seal element having a first side facing the exterior of the nozzle and a second side facing the interior of the nozzle;
wherein each seal element is movable to the open position to permit flow through the passage under operative conditions having separated flow adjacent the casing at which the pressure in the exterior is greater than the pressure on the interior to stabilize the location of the separated flow and is movable to the closed position to block flow through the passage under operative conditions having full flow adjacent the casing at which the pressure adjacent the casing on the interior is greater than the pressure on the exterior and wherein each seal element at its point of attachment to the outer member is shielded by the coolant conduits from the rocket gases and is cooled by the coolant passing through the coolant conduits.
2. The rocket nozzle structure of claim 1 wherein the outer member is an outer wall, the casing has
an inner wall which includes,
at least one of said pair of conduits for coolant which are adjacent, which extend substantially parallel to each other and which are spaced apart leaving a gap therebetween,
at least one spacer disposed in the gap which extends laterally and axially between each pair of conduits to form a unitary structure, the spacer having at least one hole extending through the spacer;
a manifold extending outwardly of the inner wall which includes,
the outer wall, the outer wall being spaced outwardly from the inner wall the outer wall extending axially and laterally with respect to the inner wall, the outer wall having an opening extending through the wall;
a pair of manifold walls spaced axially one from the other and extending outwardly between the inner wall and the outer wall to form the manifold;
wherein each vent passage extends through an associated opening in the spacer, through the manifold and through an associated opening in the outer wall; and
wherein the seal element has a first end attached to the outer wall and extends inwardly of the outer wall within the manifold, the seal element being responsive under operative conditions to the difference in static pressure between the exterior and the interior of the engine by being responsive to the difference in static pressure between the manifold inwardly of the seal member and the exterior of the engine.
3. The rocket nozzle structure of claim 2 wherein the seal element is in the closed position against the outer wall in the non-operative condition of the engine.
4. The rocket nozzle structure of claim 2 wherein the seal element is rigidly attached at the first axial end to the outer wall and has a radial flexibility characteristic which permits deflection of the seal element away from the outer wall in response to operative static pressure exerting a force on the first side and second side of the seal member.
5. The rocket nozzle structure of claim 2 which further includes a source of pressurized gas and wherein the vent passage through the exterior of the casing is in flow communication with the source of pressurized gas.
6. The rocket nozzle of claim 5 wherein the rocket engine consumes fuel and the pressurized gas is the same gas as the rocket fuel.
7. The rocket nozzle of claim 1 wherein the seal element has a first end, the outer member is a stiffening member attached to the conduits of the inner wall, wherein the inner wall bounding the flowpath rotatably supports each seal element at the first end and the structure further includes a spring means on the exterior of the casing extending between the stiffening member and the seal element to urge the wall element toward the open position.
8. The rocket nozzle structure of claim 7 wherein the seal element is a carbon-carbon composite.
9. A method of operating a rocket engine nozzle having a high expansion ratio and which has passages which extend from the exterior of the engine, which includes the steps of:
operating the engine with a pressure ratio and at an area ratio of the nozzle which results in a separated flow zone and a full flow zone;
opening the vent passages in flow communication with the separated flow zone;
closing the vent passages in flow communication with the full flow zone;
wherein the step of opening and closing the passages includes the steps of disposing seal elements in said engine to block the flow or unblock the flow of ventilation gas through the vent passage, the seal elements being responsive to the static pressure adjacent the wall region of the nozzle and ambient pressure.
This invention was made under a Government contract and the Government has rights herein.
This invention relates to rocket engines which have a rocket nozzle for expanding hot, highly pressurized rocket gases and more particularly, to a high expansion ratio nozzle for such an engine.
One example of a rocket engine is the RL10 rocket engine manufactured by the Pratt & Whitney Group of the assignee of this application. Three major components of this engine are a turbopump, a combustion chamber and a rocket nozzle.
During operation of the rocket engine, the turbopump is used to supply a fuel and oxidant, such as liquid hydrogen and liquid oxygen, to the combustion chamber. The liquid oxygen and liquid hydrogen are expanded in the combustion chamber and burned to produce hot, pressurized rocket gases. The hot, pressurized gases are flowed at high velocities to the exhaust nozzle. The exhaust nozzle allows further expansion of the gases to increase the velocity of the gases before the gases exit the engine, thereby increasing the thrust of the rocket engine.
The exhaust nozzle is fabricated from thin walled tubes that are tapered and shaped to form the required nozzle contour. Liquid hydrogen fuel is flowed through these tubes to provide convective cooling to the tubes and regenerative heating to the hydrogen fuel. The convective cooling ensures that the temperature of the tubes is consistent with the temperature limits required for structural integrity of the nozzle.
Two important parameters of an exhaust nozzle are the expansion ratio of the nozzle at the exit and the pressure ratio of the nozzle under operative conditions. The pressure ratio is the total pressure Pc (i.e., combustion chamber pressure) of the exhaust nozzle divided by the total pressure Pa of the ambient environment to which the rocket gases are discharged. The expansion ratio is the area ratio at the exit of the nozzle. The expansion ratio at any location of the nozzle is the area of the nozzle at the location divided by the area of the throat of the nozzle.
The exhaust nozzle will flow "full" without separation of the boundary layer of the gases from wall of the nozzle if the pressure ratio is high enough. However, if the pressure ratio is too low for the required amount of expansion, then the flow will separate from the nozzle wall or casing which bounds the flowpath for the rocket gases. Aerodynamic losses will result.
This is caused in part by the static pressure in the wall region dropping well below ambient as the flow expands through a supersonic, overexpanded nozzle. As shown in FIG. 1, the boundary layer thickness increases with area ratio and the boundary layer has a portion which is subsonic. Ambient pressure is transmitted upstream through the subsonic portion of the boundary layer. Under the influence of this adverse pressure gradient, the subsonic portion of the boundary layer slows and thickens. Then the flow separates from the nozzle wall and induces the formation of shock waves which cause the primary overexpanded supersonic flow to adjust to the pressure of the inflowing ambient air.
For three-dimensional flow nozzles, the flow separation begins at a point on the nozzle wall rather than at a single area ratio plane normal to the centerline. This is because the pressure in the boundary layer for any one area ratio is subject to the random fluctuations that are characteristic of turbulent flow.
The ambient pressure of the inflowing air varies with altitude. At sea level, the pressure on the exterior of the nozzle and of the inflowing air is about fourteen and seven tenths pounds per square inch (14.7 psia). The total pressure on the interior of the nozzle, for example at a downstream location, might approach fifteen hundred pounds per square inch (1500 psi) with a static pressure of about fifteen pounds per square inch (15 psia). The pressure Pb in the boundary layer might be in the order of two or three (2-3) pounds per square inch. The pressure differential may impose large side loads on the wall casing of the nozzle which surrounds the gas flow path.
Separation such as occurs when using a high area ratio exhaust nozzle at low pressure ratios may cause unstable flow separation, that is, the separation location may oscillate fore and aft, and side to side with high frequency. This results in large fluctuating side loads. The fluctuating side loads are particularly troublesome in rockets because of the effect the side loads have on the trajectory of the rocket and because the side loads can cause destructive vibrations in the exhaust nozzle.
As the rocket driven vehicle travels from sea level to a high altitude above the earth's surface, (for example, 200,000 feet) the rocket nozzle will operate at pressure ratios (Pc /Pa) which vary dramatically from low pressure ratios at sea level to high pressure ratios at altitude. This results from the large variation in ambient pressure which decreases from about fourteen pounds per square inch (14.7 psia) at sea level to pressures as low as one-tenth of a pound per square inch (0.1 psia) at one hundred thousand feet (100,000 ft.) of altitude. Thus, it is difficult to avoid separation of flow in a typical fixed-geometry rocket nozzle.
FIG. 2 is an exemplary curve showing the relationship of the separation area ratio Ar for a nozzle as a function of the pressure ratio at which the nozzle is operated. For a given pressure ratio of the rocket nozzle, separated flow will occur in the chamber at area ratios above the separation area ratio. For example, at a pressure ratio of two hundred the exhaust nozzle will flow "full" at an area ratio less than about 68:1 and will flow separated at an area ratio greater than 68.1 with overexpansion of the flow and unstable separation occurring at an axial location corresponding to about the area ratio of 68:1 of the nozzle. If separation were the only concern, the ideal nozzle would have an area ratio at the exit which is equal to the area ratio at which separation occurs.
One solution, then, is to employ an exhaust nozzle having a maximum area ratio which, for the operative pressure ratios, causes the nozzle to flow full from take-off until the rocket reaches its final altitude. However, this reduces the efficiency of the rocket at high altitudes because of the low velocities of the exiting flow. These low velocities are associated with the small, gradual expansion of area used to avoid separation at low pressure ratios which occur at sea level take-off.
Creating a vehicle having several stages is another approach to tailoring the nozzle area ratio and pressure ratio to avoid separation. Each stage has a nozzle having area ratios designed for a limited range of pressure ratios. The nozzle would have a first stage having a low area ratio at sea level launch and another stage having a high area ratio at high altitude orbit. Multi-stage rocket engines are more complex than single stage rocket engines and increase the complexity of operation. However, such a rocket has the advantage of increased thrust as the rocket reaches orbit.
The above art notwithstanding, scientists and engineers have been working under the direction of Applicants' assignee to develop a rocket engine having an exhaust nozzle which would eliminate the requirement for staging, and, have a high expansion ratio (that is, greater than 150:1) for good thrust at altitude while not having unacceptably large unstable separation.
This invention is predicated in part on the recognition that flow from the exterior to the interior of the exhaust nozzle through the casing into a zone having separated flow is capable of stabilizing the location of separation and reducing the internal drag associated with such separation.
According to the present invention, a rocket nozzle having a high expansion chamber includes a plurality of vent passages extending from the exterior to the interior of the chamber for stabilizing the location of separation under operative conditions that have a low pressure ratio and includes a device responsive to the pressure ratio of the nozzle for closing the passages as the pressure ratio increases.
In accordance with one embodiment of the present invention, a plurality of seal elements which extend axially from the casing, are in response to the direction of differential pressure across the seal element, movable between 1. an open position which permits in flow through the vent passage, and, to, 2. to a closed position which blocks outflow through the vent passage.
According to the present invention, a method of operating a rocket engine includes 1. the step of operating the engine with a pressure ratio and at an area ratio of the nozzle which results in a separated flow zone and a full flow zone within the rocket chamber and 2. the step of opening vent passages in the casing of the nozzle to place the separation zone in flow communication with ambient atmosphere to stabilize flow separation in the rocket chamber. In still another embodiment, gas is provided to the separation zone at a pressure which is greater than the ambient pressure.
A primary feature of the present invention is a rocket nozzle having a high expansion area ratio, which is operable at low pressure ratios at low altitudes and at high pressure ratios at high altitudes. Another feature is a casing for the nozzle which surrounds the divergent section (expansion chamber) of the nozzle. A portion of the casing has a plurality of vent passages which extend through the casing to place the interior in flow communication with the exterior. In one embodiment, at least one manifold extends about the casing and has a valve means for interrupting flow from the interior to the exterior at high pressures in the wall region and for permitting flow from the exterior to the interior at low pressures in the wall region. In one embodiment, the device for interrupting a flow is a check valve. In another embodiment, the device for interrupting flow is a door which is positively positioned by an actuator in response to a pressure signal or altitude signal from a control means. In another embodiment, the doors are thin, relatively flexible members or seal elements which are movable from an open position to a closed position in response to pressure forces acting the seal element.
A primary advantage of the present invention is the efficiency and simplicity of a rocket engine having a single nozzle which provides a high expansion ratio with stable separation under operative low pressure ratios of the rocket engine. Another advantage is the internal drag which results from pressurizing the separation zone of the rocket chamber. Still another advantage in one embodiment is the simplicity of the venting scheme which relies on the difference in pressure between the exterior and the interior to supply the force to allow or interrupt flow between the exterior and in the interior of the chamber.
The foregoing features and advantages of the present invention will become more apparent in light of the following detailed description of the best mode of carrying out the invention and the accompanying drawings.
FIG. 1 is a schematic illustration of a nozzle wall showing separation of the boundary layer and accompanying pressures.
FIG. 2 is an exemplary curve showing the relationship for a particular nozzle of separation area ratio (Ar) as a function of pressure ratio Pr of the nozzle.
FIG. 3 is a schematic representation of a portion of a rocket engine with portions of the nozzle and cooling system broken away for clarity.
FIG. 4 is a schematic representation of a side elevation view of the rocket engine shown in FIG. 3.
FIG. 5 is a view taken along the line 5--5 of FIG. 4.
FIG. 6 is an alternate embodiment of the configuration shown in FIG. 4.
FIG. 7 is a view taken along the line 7--7 of FIG. 6.
FIG. 8 is an alternate embodiment of the construction shown in FIG. 4.
FIG. 9 is a view taken along the line 9--9 of FIG. 8.
FIG. 10 is a side elevation view of a portion of the divergent region of an exhaust nozzle of the type shown in FIG. 3.
FIG. 11 is an enlarged view from above of a portion of the divergent region of the nozzle shown in FIG. 10.
FIG. 12 is a view taken along the line 12--12 of FIG. 11.
FIG. 13 is a view taken along the line 13--13 of FIG. 12.
FIG. 14 is an alternate of the exhaust nozzle shown in FIG. 10.
FIG. 15 is an enlarged view of a portion of the casing shown in FIG. 14.
FIG. 16 is an enlarged view taken along the line 16--16 of FIG. 15.
FIG. 17 is an alternate embodiment of the construction shown in FIG. 8.
FIG. 18 is a graphical representation of wall temperature versus axial location for a water cooled extension.
FIG. 3 is a schematic representation of a portion of a rocket engine 8 with a portion of the cooling system broken away for clarity. The rocket engine includes a combustion or thrust chamber 10 and an exhaust nozzle 12. The exhaust nozzle has a convergent region 14, a throat 16, a divergent region 17 and an exit 18. The throat has a diameter D1 and the exit has a diameter D2. The ratio of the area of the nozzle at any axial location to the area of the throat is the area ratio of the nozzle at that location.
The exhaust nozzle 12 has a casing 22 which extends about the axis A of the nozzle. The casing bounds the thrust chamber 10, the convergent region 14 and the divergent region 17. An exhaust chamber 24 is disposed on the interior of the casing in the divergent region of the nozzle.
The divergent region of the casing is divided into three sections. A first section 24 extends from the throat 16 of the nozzle out to an area ratio of about 40 to 1. The first section is formed of a plurality of axially extending tubes 25 for coolant (not shown in detail) which are joined together to form the contour of the casing. The second section 26 is a continuation of the tubes. The tubes in the second section are spaced apart to allow for ventilation ports (not shown).
A third section 28 extends from the second section to the exit 18 of the nozzle. The third section is a fixed extension which is integrally attached to the second section of the nozzle. The third section of the nozzle does not have axially extending cooling tubes.
Coolant manifolds 32 and 34 are used to flow hydrogen to the cooling tubes 25 extending through the second section of the nozzle and to supply hydrogen to the thrust chamber. The hydrogen is regeneratively heated as the tubes are cooled. Coolant manifolds (not shown) are also used to supply coolant to the tubes in the first section of the exhaust nozzle.
The thrust chamber includes an inlet manifold 36 for the regeneratively heated liquid hydrogen fuel; and, an inlet manifold 38 for the liquid oxygen oxidant. The fuel and oxidant are flowed into the thrust chamber via an injector (not shown). An igniter (not shown) is also disposed in the thrust chamber.
FIG. 4 is a schematic representation of a side elevation view of the rocket engine shown in FIG. 3, partly in full and partly broken away. The casing 22 has an outer wall 42 and an inner wall 44. A flow path 46 for working medium gases extends axially through the chamber 24 of the exhaust nozzle. A plurality of vent passages for venting the interior of the exhaust nozzle, as represented by the flow paths 48, 52, 54, and 56, extend inwardly through the casing 22 to the interior or chamber 24 of the exhaust nozzle.
The inner wall 44 of the casing 22 has a plurality of openings as represented by the openings 58, 62, 64 and 66 which extend through the first or inner wall of the casing. The outer casing 42 has a plurality of openings, as represented by the openings 68, 72, 74, and 76 which extend through the second or outer wall 42. Radial walls 77, 78, 82, 84 interrupt the cavity leaving manifolds 88, 92, 94, and 96 therebetween. The inner wall and the outer wall are joined at 86 to bound the manifold 96. The manifolds and associated openings provide the vent passage for each of the flow paths, as for example, the vent passage 48 for a flowpath formed by the openings 58 in the inner wall, the manifold 88, and the openings 68 in the outer wall.
A plurality of check valves at each opening in the outer wall, as represented by the check valves 98, 102, 104 and 106, are representative of means for placing the vent passage in flow communication with the exterior of the nozzle and with the interior of the nozzle. Each check valve could be located at any location that permits flow inwardly through the associated passage at operative conditions under which the exterior pressure exceeds the interior pressure adjacent the inner wall. The check valve blocks the flow of gases from the interior of the nozzle under operative engine conditions at which the chamber pressure adjacent the wall exceeds the pressure on the exterior of the nozzle. Accordingly, the check valves are means responsive to the pressure ratio between the exterior of the exhaust nozzle and the interior of the exhaust nozzle at a location adjacent to the wall in the wall region of the exhaust nozzle.
FIG. 5 is a view taken along the lines 5--5 of FIG. 4 showing the relationship of the openings 58, 62, 64 and 66 to the circumference of the nozzle. As can be seen, the slots have a high aspect ratio with respect to the axial direction, that is, the circumferential length of each slot is greater than the axial length of each slot. The area of the slots is approximately equal to twenty percent of the area of the nozzle exit.
FIG. 6 is an alternate embodiment of the configuration shown in FIG. 4 having a plurality of axially extending openings 108. The openings 108 have a low aspect ratio with respect to the axial direction of the exhaust nozzle, that is, the slots 108 each have an axial length which several times greater than the axial width of each slot.
A single manifold 88a extends circumferentially about the inner wall 44a and inwardly of the outer wall 42a. A check valve 98A performs the same function as does the check valve 98 shown in FIG. 4.
FIG. 7 is a view of the exhaust nozzle shown in FIG. 6 taken along the line 7--7 of FIG. 6 to show the relationship of the axial slots 108 and to the throat of the exhaust nozzle.
FIG. 8 is alternate embodiment of the construction shown in FIG. 4. having a plurality of holes 110 through the inner wall 44b of the nozzle. In this particular embodiment, the seal elements or valves 98b, 102b, 104b and 106b are responsive to a control means 112 such as the on board computer for the rocket engine. The control means generates a control signal to the valves 98b, 102b, 104b and 106b to turn the valves on and off.
The control means 112 compares the total pressure of the chamber to the ambient pressure on the exterior of the rocket and generates a pressure ratio signal from which the separation area ratio can be determined. The control means sends a signal to the valves 98b, 102b, 104b and 106b opening the valve associated with the separation area ratio and closing valves upstream of that point. Thus, the flow through the valves 98b, 102b, 104b and 106b will be from the exterior of the rocket engine to the interior wall region under operative conditions at which separation is expected to have occurred adjacent to the wall region.
FIG. 9 is a view taken along the lines 9--9 of FIG. 8 showing the relationship of the holes 110 to the throat of the exhaust nozzle.
FIG. 10 is a side elevation view partially in section and partially broken away to show in more detail portions of the divergent region 17 of a rocket engine having the type of exhaust nozzle shown in FIG. 3. A plurality of tubes, as represented by the tubes 25, extends axially over a portion of the first section 24 from the coolant exit manifold 34. The plurality of tubes may be formed of three-hundred and sixty (360) individual tubes having a tapering diameter, for example, tapering from a diameter of about a quarter of an inch to a diameter of about four-tenths of an inch at the end of the second section 26. The tubes may be formed of any suitable material having resistance to hydrogen embrittlement, high strength and ductility, weldability and brazeability without requiring a heat treat stress relief cycle. One example of a material for the nozzle tubes in the inlet and exit manifolds is Haynes 230 nickel alloy material. The tubes are joined together with a gold nickel braze.
The second section 26 of the nozzle extends from an area ratio of approximately forty to one (40:1) to an area ratio of about one hundred and forty-four to one (144:1) at which location the coolant inlet manifold 32 is located. The second section of the nozzle has an outer wall 42c and an inner wall 44c. A plurality of openings 58c, 62c 64c and 66c as represented by the opening 58c, extend through the inner wall. The openings in the outer wall and the inner wall are enlarged many times for clarity.
The outer wall 42c is spaced outwardly from the inner wall. The outer wall extends axially and laterally with respect to the inner wall. The outer wall, has openings as represented by the openings 68c, 72c, 74c and 76c. The outer wall may be formed of an aluminum alloy such as AMS (Aerospace Material Specification) 4027 aluminum alloy.
The third section 28 of the divergent region 17 of the exhaust nozzle is a fixed, radiation--cooled extension that establishes the remaining contour of the divergent section of the exhaust nozzle. The extension of the third section extends from an area ratio of about 144:1 to an area ratio of 250:1. The location of the regenerative tube cooling-radiation cooling interface between the second region 26 and the third region 28 is established by the requirements for adequate film cooling. The cooling tubes are modified in ways discussed below which cause the cooling fluid to cool the tubes to a temperature which is less than half the temperature to which the tubes are cooled for structural reasons. This increased cooling causes water condensate to form in the boundary layer of the regenerative nozzle region of the divergent section and to further cool the downstream, radiation-cooled extension.
Integral stiffening bands 114 extend circumferentially about the exterior of the fixed extension to increase the structural rigidity of the fixed extension. The fixed extension may be made of any suitable alloy such as AMS 7852 columbium alloy.
In the second section of the divergent region, stiffening bands or bulkheads 116 extend circumferentially about the exterior of the second section. These bulkheads form a plurality of manifolds between the inner wall and the outer wall as represented by the manifolds 88c, 92c, 94c, and 96c.
FIG. 11 is an enlarged view from above showing the transition from the first section 24 and the beginning of the second section 26 of the divergent region of the exhaust nozzle. As shown at area ratio Ar of approximately 38:1, the inner wall has pairs of tubes 25 for coolant which are adjacent and which extend substantially parallel to each other. The tubes are spaced apart leaving a gap G therebetween. An axially extending spacer is disposed between each pair of tubes, as represented by the spacer 118. Fore and aft bulkheads, as represented by the bulkhead 78c, extend circumferentially about the nozzle to form, in cooperation with the outer wall 42c, the manifold 88c.
FIG. 12 is a view taken along the line 12--12 of FIG. 11 showing in more detail the tubes 25 and the adjoining spacer 118. The spacer may be formed of a material having a comparable coefficient of a thermal expansion to the material of the tubes which are formed of Haynes 230 alloy. Oxygen-free copper (AMS 4501) was selected and the entire assembly is gold-nickel brazed which allows field repair of brazed joints without removing the engine/nozzle from the vehicle. The spacer 118 has a standoff 122 which extends locally and radially outwardly from the spacer beneath the bulkhead or manifold wall 78c. The standoff is a local projection from the spacer and the length between standoffs is open and in flow communication with the openings 58c.
FIG. 13 is a view taken along the line 13--13 of FIG. 12 showing in more detail the relationship of the inner wall 44c, the outer wall 42c, and the radially extending bulkheads 77c and 78c. The inner wall is formed of the spacers 118 and the adjacent tubes 25 which extend beyond the spacer in the hole region 58c of the spacer. Thus, the hole opening 58c, the manifold 88c, and the opening 68c in the outer wall define the vent passage 48 along which the associated vent flow path extends.
The outer wall includes means 48 for placing the vent passage 48c in flow communication with the exterior and with the interior of the chamber which is responsive to pressure on the exterior of the exhaust nozzle and on the interior of the nozzle in the wall region 107. As shown in FIG. 13, the means is a plurality of seal elements as represented by the single reed valve 98', which extends axially from the casing 22. The reed valve is formed of a thin, flexible sheet or strip, having a thickness of about, for example, twenty-thousandths (0.020) of an inch, a length of about six and one half inches and width of about five inches. The length to thickness ratio of the reed valve is greater than 200. A suitable material is Inconel X-150 (AMS 5598) and the outer wall is an aluminum AMS 4027 alloy.
The reed valve is movable between an open position, shown in full, and a closed position shown in phantom. In the closed position, the reed valve blocks flow through the passage from the interior to the exterior. In the open position, the reed valve permits flow through the vent passage 48c from the exterior to the interior. A plurality of openings (not shown) in the end 124 of the reed valve permit flow through the end of the reed valve. The other end 126 of the reed valve is attached to the outer wall by any appropriate method such as bonding or, preferably, riveting.
The reed valve has a first side 128 facing the ambient exterior of the nozzle. The reed valve has a second side 132 facing the interior of the nozzle. In a non-operative condition of the engine, the reed valve is in the closed position against the outer wall of the casing 22.
FIG. 14 is an alternate embodiment of the exhaust nozzle shown in FIG. 10. A portion of the first section 24 of the nozzle has 720 tubes 25 formed of Haynes 230 nickel alloy material with a diameter of approximately one quarter of an inch which extend axially through the first section of the divergent region 17 of the exhaust nozzle 12.
The second section 26 of the nozzle extends from an area ratio of approximately forty to one (40:1) to an area ratio of approximately two-hundred to one (200:1). In the second section, the casing 22 is formed of the axially extending tubes 25 and twelve (12) equally spaced, tapered axial slots which provide the openings 58d, 62d, 64d, and 66d. This establishes passages for ventilation flow to provide pressure ratio or altitude compensation at area ratios of approximately 40:1, 80:1, 120:1, and 160:1.
A carbon-carbon composite door at each slot, as represented by the doors 98d, 102d, 104d, and 106d (hereinafter 98") represent means for placing each vent passage in flow communication with the exterior and interior of the nozzle. Each door has a forward end 136 and a hinge 138 which extends from the casing to the door or seal element. The hinge is a spring and spring loads the doors open to the non-operative position shown in FIG. 14. Each door has first side 142 facing the interior of the exhaust nozzle and a second side 144 facing the exterior of the nozzle.
FIG. 15 is an enlarged view of a portion of the casing showing one of the doors of 98" and the hinge 138 at the upstream end 136 of the door. A stiffening band 146 having projections 148 extends circumferentially about the door and beneath the hinge to reinforce the tube construction at the door location. A housing 152 for the door extends rearwardly and inwardly and is joined to the stiffening band and to the tubes 25 to provide a seat for the door. To form the door opening a plurality of axially extending tubes 25 bound the flowpaths for coolant shown by the directional arrows C. The tubes extend axially along the side of the upstream door, extend circumferentially for a short distance between the upstream and downstream doors. The tubes extend axially along the side of the door until they reach the next door at which point they extend circumferentially for a short distance.
FIG. 16 is an enlarged view taken along the line 16--16 of FIG. 15 to show in greater detail the relationship of the stiffening band 146, the spring 138 and the circumferentially extending portion of the tubes 25 (such as ten tubes of which several are broken away). The downstream door 98" is shown in the open position which is the non-operative position of the door. The housing 152 at its upstream end has an axially extending flange 158 at the upstream end of the door 136 which engages a groove 162 in the door to pivotally trap the door at the upstream end. The spring 138 is attached to the door by bolts 156 which engage a carbon-carbon projection on the blow-in door.
The slots or door openings 58d, 62d, 64d or 66d are circumferentially indexed to allow the routing of coolant tubes as described above this permits the coolant tubes 25 to specially cool the hinges and prevent local hot spots. The doors located at area ratios of 40:1 and 80:1 require additional cooling to prevent carbon-carbon abrasion during engine operation. This may be accomplished by bleeding hydrogen into the gas path via holes 164 in one of more of the adjacent upstream cooling tubes. Alternatively, the cooling tube might be contoured by a reduction 166 in the tube flow area by swaging or increasing the tube wall thickness to increase the flow velocity through the tube and thus the convective heat transfer coefficient of the tube. Internal devices for increasing heat transfer area and turbulence, such as internal fins 168, swirlers (not shown) and trip strips or other devices to roughen the surface of the tube will increase both the heat transfer area and turbulence and locally increase velocity. The trip strips 170 may be combined with mini swirler vanes 172 angled with respect to the approaching flow to reduce the flow area, roughen the surface, and to trip and direct the flow with a swirling motion.
FIG. 17 is an alternate embodiment of the construction shown in FIG. 8 where the means for interrupting the vent passage 48e is a seal element, such as a vent door 176, positively pivoted at its upstream end 178 by a hydraulic or gas actuator 180. The hydraulic actuator is responsive to control means such as the control means 112 which generates a signal causing the actuator to positively move the door to the open position. The actuator might be disposed in a manifold 88e which extends between the outer wall 42e and the inner wall 44e. This would allow the ventilation flow to be pressurized, for example by placing the flow in communication with a source of pressurized gas such as a small amount of coolant flowed through the adjacent tubes which form the inner wall 44e. The flow from these tubes might also be positively controlled by a valve in flow communication with the opening 58e, with or without the doors 176.
During operation of the rocket engine shown in FIG. 3 with an exhaust nozzle as shown in FIG. 6, fuel and oxidant are flowed into the combustion or thrust chamber 10. The fuel and oxidant, in this case hydrogen and oxygen, are burned to produce water vapor and hot, high pressure gases. The total pressure of the gases may, for example, approach three thousand (3000) pounds per square inch at the throat and remains constant at any axial location of the nozzle. The static pressure is a constant at any axial location as long as the flow is full, that is, unseparated.
The gases are flowed from the combustion chamber into the exhaust nozzle 12 through the convergent region 14 of the nozzle to the throat 16. The gases are expanded from the throat to the exit 18 where the gases develop the propulsive thrust for the vehicle to which the rocket engine 8 is attached.
As the gases expand, the over expansion and separation of the flowing gases from the wall 44a will result in a low pressure region in a wall region 107 adjacent the inner wall 44a. The low pressure region and the higher ambient pressure results in a pressure differential which causes the inflow of ambient air along the vent passage 48a through the means 98a, the manifold 88a and the openings 108 in the inner wall 44a to the interior chamber 24 of the engine. The flow, although separated, is stabilized by the inflow of ambient air at a relatively low pressure (that is equal to or less than 14.7 pounds per square inch absolute) into the interior of the nozzle. The flow area available for the incoming flow in the inner wall is approximately twenty per cent of the exit area of the nozzle to ensure that a large volume of the low pressure flow enters. This has the effect of stabilizing the separation point and avoids the separation location moving axially up and down the rocket nozzle with a deleterious effect on rocket stability. In addition, there is a gain in engine efficiency as a result of the decrease in internal drag which results from increasing the pressure force in the wall region to oppose the external ambient pressure force.
As the altitude of the vehicle increases, the ambient pressure drops and the pressure ratio increases, causing the separation area ratio to move to an axial location which is past the openings 108. The flow is full to the new axial location, and as a result, the pressure in the wall region exceeds ambient pressure causing the seal element or check valve 98a to close and the separation point moves to a location downstream of the openings 108. For a nozzle having a separation area ratio curve as shown in FIG. 2, it is possible to take into account the pressure ratio and locate the openings 108 so that the location of the separation area ratio stays within the region of the openings 108 of the nozzle.
The operation of the multi-manifolded construction shown in FIG. 4 is similar to the operation of the single manifold construction shown in FIG. 6. It is expected that the stabilized separation point will leap from a location in one manifold to a location in the adjacent manifold as the pressure ratio increases with an increase in vehicle altitude and a concomitant decrease in ambient pressure. It is possible under some conditions that the separated flow might oscillate axially a small amount in the manifold region of one of the manifolds. In this case, the benefit of the invention is the dimunition in the magnitude of axial oscillation. Such oscillations are positively diminished by inflow downstream of the separation location that enters through the adjacent downstream manifolds.
As shown in FIG. 8, the seal elements or check valves 98b, 102b, 104b and 106b are controlled by the engine control means 112. The on board computer received either a predicted chamber pressure and ambient pressure signal or actual signals to generate a pressure ratio signal Pr. The actual signals may be direct pressure readings through pressure transducers or analogous signals from which pressure may be determined. For example, an analogous signal for ambient pressure would be an altitude signal for which a correlation exists to ambient pressure.
The pressure ratio signal Pr is fed to a lookup table as represented by the graph Ar v. Pr and the appropriate area ratio Ar is selected so that manifolds axially located upstream of the axial location of the separation area ratio are closed and manifolds at and downstream of the separation area ratio location are open.
As was shown in FIG. 4 and FIG. 6, the perforated nozzle shown in FIG. 10 uses ventilation flow at ambient pressure into the flow path 46 to force and control flow separation at preselected points along the contour of the divergent section of the nozzle. As noted, the ventilation zone extends from an area ratio of 40:1 to an area ratio of 144:1. The perforation zone is limited to the axial locations associated with these area ratios because studies have shown that altitude compensation is more efficient and beneficial at lower altitudes of the vehicle (which are associated with lower area ratios) than at high altitudes which are associated with the high area ratios used for thrust.
The reed elements 98' are closed when the engine is non-operative, but spring open under the pressure differential of approximately one (1) pound per square inch of pressure or greater which is produced between the ambient pressure and the static wall pressure inside the nozzle in the wall region. As the altitude of the vehicle is increased, the ambient pressure decreases and the pressure differential relative to a specific reed valve location decreases, unloading the valve and allowing the valve to close. At a pre-selected altitude, having an associated ambient pressure, all valves would close to form a high area ratio nozzle contour thus allowing the nozzle to compensate for a change in altitude of the vehicle.
The divergent region 17 of the nozzle shown in FIG. 14 will operate in similar fashion to the nozzle shown in FIG. 10, providing altitude compensation by relying on ambient flow ventilation to force and control flow separation. The ventilation is required throughout a wider range of area ratios because the circumferential locations of the ambient vent passages 48,52,54,56 are not as evenly distributed as in the FIG. 10 embodiment. Accordingly, ventilation is required throughout a wider range of area ratios, from area ratio 40:1 to an area ratio of 200:1, to accomplish the same effect as in the FIG. 10 construction.
The vent passages are blocked by the carbon-carbon composite doors 98" each hinged with a spring 138 at the forward end 136. The doors are actuated by the relative differential pressure at the location of the doors and close as the vehicle gains altitude. As mentioned, the doors located at area ratios of 40:1 and 80:1 receive additional cooling, either by injecting small amounts of hydrogen into the flowpath via holes 164 or by condensing water vapor which is formed as a product of combustion.
As shown in FIG. 17, it is possible to supply large quantities of pressurized ventilation gases via the manifold 88e in conjunction with a computer operated vent door 176. It is expected that the large volume of gases will be supplied at a slightly increased pressure which is lower than twenty (20) pounds per square inch. One source of the pressurized gas is the liquid hydrogen fuel which could be expanded into the exhaust nozzle. This will have a slight adverse impact on engine efficiency because the hydrogen is not used in the combustion chamber.
In both the FIG. 10 and FIG. 14 constructions, the cooling tubes are specially contoured to cool the regenerative tubes to a temperature which is less than fifty per cent of the temperature required for structural stability. Sub-cooling the tubes cools gases in the flow path which contain water vapor well below the saturation temperature characteristic (that is, the temperature at which water condenses at the local pressure) of the gases. This causes water to condense in the boundary layer of the regenerative by cooled portion of the nozzle. The water condensate provides additional cooling to the downstream radiation cooled extension in the divergent portion of the nozzle. For example, well over two-tenths of a pound of water per second can be generated at the end of the extension over an axial wall temperature gradient from about 300� R to about 550� R.
Because the primary exhaust gas of a hydrogen oxygen combustion chamber is essentially high temperature steam, this film coolant, water, is internally generated within the nozzle. Generally speaking, the water will be generated when the surface temperature of the wall is cooled below approximately five hundred and sixty degrees Rankine (560� R.). One of the major advantages of this technique is its relative simplicity.
FIG. 18 illustrates the reduction in downstream wall temperature that this mechanism can produce. Location A corresponds to a point slightly upstream of the interface between the second section 26 and the third section 28. Location B is immediately adjacent the second section and the third section, and location C is the end of the nozzle extension. The temperature is normalized by dividing the surface temperature of the extension by the maximum temperature of the extension. The length is normalized by dividing the axial location by the overall length of the secondary nozzle.
As will be realized, the nozzle can be operated within temperature limits which provide for specialized cooling at specialized locations; and, with a high area ratio bell nozzle over a wide range of pressure ratios even at low pressure ratios which cause separation, by avoiding the large fluctuating side loads due to unstable flow separation. As a result, improvements in thrust both at low altitudes and high altitudes are obtained from a single large area ratio nozzle which is tolerant of pressure ratio ranges much larger than heretofore used for a single nozzle. This provides for adequate thrust at liftoff and for efficient thrust production at high altitudes.
Although the invention has been shown and described with respect to detailed embodiments thereof, it should be understood by those skilled in the art that various changes in form and detail thereof may be made without departing from the spirit and scope of the claimed invention.
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|By Marketwired .
Article Rating:
|November 5, 2012 12:01 AM EST
SUNNYVALE, CA -- (Marketwire) -- 11/05/12 -- AMD (NYSE: AMD) today unveiled its new AMD Opteron 6300 Series server processors based on its next-generation "Piledriver" core architecture. The new AMD Opteron processors deliver superior performance and scalability for virtualized server platforms that are central to private and public cloud deployments, big data systems and high-performance computing (HPC) clusters. The AMD Opteron 6300 Series processors strike the ultimate balance between performance, scalability and cost effectiveness to help IT organizations lower total cost of ownership (TCO).
The AMD Opteron 6300 Series processors offer industry-leading performance in SPECjbb2005, a server benchmark used to evaluate Java performance, with up to 24 percent higher performance versus the prior generation AMD Opteron 6200 Series processors(1). Java is a critical element of the software ecosystem for next-generation data centers. Performance per watt is up to 40 percent higher than the prior generation solutions(2), which means businesses running robust large-scale software systems will be able to enjoy high performance as well as low TCO.
AMD continues to drive HPC performance with the AMD Opteron 6300 Series processors by leveraging optimizations in compilers and libraries, and combining it with the next-generation core architecture. AMD has delivered impressive results in key HPC applications such as the molecular dynamics workloads LAMMPs and NAMD(3).
"Across global IT organizations, cost-effective, scalable performance is a core requirement to support cloud computing, server consolidation and highly-threaded workloads common in HPC, big data and other areas," said Suresh Gopalakrishnan, general manager, Server Business Unit, AMD. "The key to a winning solution for customers is working with OEMs and other solution providers to minimize TCO with a combination of cost effectiveness and superior performance per watt. AMD Opteron 6300 Series processors are uniquely positioned to be the difference-maker customers are seeking."
Customer and Partner Traction
Servers from Dell and HP based on the AMD Opteron 6300 Series processors are expected to be available before the end of the year. Systems and platforms are available today from Cray, SGI, and Supermicro as well as AMAX, Appro, ASUS, ClusterVision, Colfax International, MEGWARE Computer, Microway, Penguin Computing, Silicon Mechanics and ZT Systems. AMD's own "Roadrunner" platform, developed for the Open Compute Project, will be available in the first quarter of 2013. Moreover, AMD has already seen early traction with the AMD Opteron 6300 Series processor leveraged in a supercomputing deployment at Indiana University.
"Cloud computing, data warehouse systems and HPC clusters are at the top of many CIOs agendas, but many struggle to find the right balance of performance and scalability with price," said Brian Payne, executive director of Platform Marketing, Dell. "Our PowerEdge and PowerEdge C server platforms are scalable and designed to integrate the latest technologies from AMD. The new AMD Opteron 6300 Series provides Dell customers with additional performance gains, lower cost of ownership and improved power efficiency, all of which are hugely beneficial for cloud computing, big data and other high-growth data center applications."
"Greater performance levels, increased agility and innovations that deliver business value and productivity are fundamental requirements for our clients' success," said Jim Ganthier, vice president, Marketing and Operations, HP. "The new AMD Opteron 6300 Series processors in HP's industry-leading ProLiant server portfolio meet those requirements, supporting demanding workloads that ensure enterprise productivity with lower lifecycle costs."
Key Facts, Performance and Technical Detail
- Frequency: Up to 3.5 GHz base frequency and up to 3.8 GHz using AMD Turbo CORE technology for increased performance when applications demand it;
- Up to 16 cores per socket for scaling in thread-intensive environments;
- AMD-P power management features maximize performance-per-watt across workloads while giving IT managers more control over their data center power profiles;
- AMD Virtualization (AMD-V) technology for near-native performance in virtualized environments and lowest cost per virtual machine (VM);
- Up to four memory channels with up to 1866 MHz memory;
- The only x86 processor to support ultralow voltage 1.25v memory;
- Supports up to 12 DIMMs per CPU for up to 384GB memory per processor;
- Up to four x16 HyperTransport technology (HT3) links at up to 6.4GT/s per link.
AMD Opteron 6300 Series Processors ---------------------------------------------------------------------------- Base Turbo CPU Model CPU Cores Frequency Frequency TDP Pricing ---------------------------------------------------------------------------- 6386 SE 16 2.8 GHz 3.5 GHz 140W $1,392 ---------------------------------------------------------------------------- 6380 16 2.5 GHz 3.4 GHz 115W $1,088 ---------------------------------------------------------------------------- 6378 16 2.4 GHz 3.3 GHz 115W $867 ---------------------------------------------------------------------------- 6376 16 2.3 GHz 3.3 GHz 115W $703 ---------------------------------------------------------------------------- 6348 12 2.8 GHz 3.4 GHz 115W $575 ---------------------------------------------------------------------------- 6344 12 2.6 GHz 3.2 GHz 115W $415 ---------------------------------------------------------------------------- 6328 8 3.2 GHz 3.8 GHz 115W $575 ---------------------------------------------------------------------------- 6320 8 2.8 GHz 3.3 GHz 115W $293 ---------------------------------------------------------------------------- 6308 4 3.5 GHz N/A 115W $501 ---------------------------------------------------------------------------- 6366 HE 16 1.8 GHz 3.1 GHz 85W $575 ----------------------------------------------------------------------------
Full performance details can be found at www.amd.com/opteronperformance; current pricing is available at http://www.amd.com/us/products/pricing/Pages/server-opteron.aspx. AMD will be formally launching its Piledriver-based AMD Opteron 4300 and 3300 Series processors (code-named "Seoul" and "Delhi") in December. Details on those systems will be made available at that time.
About AMD
AMD (NYSE: AMD) is a semiconductor design innovator leading the next era of vivid digital experiences with its ground-breaking AMD Accelerated Processing Units (APUs) that power a wide range of computing devices. AMD's server computing products are focused on driving industry-leading cloud computing and virtualization environments. AMD's superior graphics technologies are found in a variety of solutions ranging from game consoles, PCs to supercomputers. For more information, visit http://www.amd.com.
AMD, the AMD Arrow logo, AMD Opteron and combinations thereof, are trademarks of Advanced Micro Devices, Inc. Other names are for informational purposes only and may be trademarks of their respective owners.
Cautionary Statement
This release contains forward-looking statements concerning among other things that AMD will launch products on schedule and in sufficient volumes to meet market needs, which are made pursuant to the safe harbor provisions of the Private Securities Litigation Reform Act of 1995. Forward-looking statements are commonly identified by words such as "believes, "expects," "may," "will," "should," "seeks," "intends," "pro forma," "estimates," "anticipates," "plans," "projects," and other terms with similar meaning. Investors are cautioned that the forward-looking statements in this release are based on current beliefs, assumptions and expectations, speak only as of the date of this release and involve risks and uncertainties that could cause actual results to differ materially from current expectations. Risks include the possibility that Intel Corporation's pricing, marketing and rebating programs, product bundling, standard setting, new product introductions or other activities may negatively impact the company's plans; the company may be unable to develop, launch and ramp new products and technologies in the volumes that are required by the market at mature yields on a timely basis; that the company's third party foundry suppliers will be unable to transition its products to advanced manufacturing process technologies in a timely and effective way or to manufacture the company's products on a timely basis in sufficient quantities and using competitive technologies; the company will be unable to obtain sufficient manufacturing capacity or components to meet demand for its products or will not fully utilize its commitment with respect to GLOBALFOUNDRIES, Inc.'s microprocessor manufacturing facilities in 2012 and beyond; that customers stop buying the company's products or materially reduce their operations or demand for the company's products; that the company may be unable to maintain the level of investment in research and development that is required to remain competitive; that there may be unexpected variations in the market growth and demand for its products and technologies in light of the product mix that the company may have available at any particular time or a decline in demand; that the company will require additional funding and may be unable to raise sufficient capital on favorable terms, or at all; that global business and economic conditions will not improve or will worsen; that demand for computers will be lower than currently expected; and the effect of political or economic instability, domestically or internationally, on the company's sales or supply chain. Investors are urged to review in detail the risks and uncertainties in the company's Securities and Exchange Commission filings, including but not limited to the Quarterly Report on Form 10-Q for the quarter ended June 30, 2012.
(1) SVR-168 - Comparison based on highest 2P SPECjbb2005 benchmark data as of Oct. 16, 2012. 1493967 bops (16 JVMs and 93373 bops/JVM) using 2 x AMD Opteron processors Model 6380 in Supermicro 1022G-URF server, 128GB (16 x 8GB DDR3-1600) memory, Microsoft® Windows Server® 2008 Enterprise x64 Edition R2. 1199838 bops (16 JVMs and 74990 bops/JVM) using 2 x AMD Opteron processors Model 6278 in HP ProLiant BL465c Gen8 server, 128GB (16 x 8GB DDR3-1600) memory, Microsoft® Windows Server® 2008 Enterprise x64 Edition R2. SPEC and SPECjbb are registered trademarks of the Standard Performance Evaluation Corporation. See www.spec.org.
(2) SVR-305 - Comparison based on 2P SPECpower_ssj2008 data as of Oct. 16, 2012: 77.9W at Active Idle, 308W and 1,636,298 ssj_ops at 100 percent of target load, and 4,040 overall ssj_ops/watt using 2 x AMD Opteron processors Model 6380 in Supermicro 1022G-NTF server, 64GB (8 x 8GB DDR3-1600) memory, Supermicro PWS-563-1H20 power supply, 240GB SATA disk drive, Microsoft® Windows Server® 2008 R2 x64 Enterprise Edition. 82.6W at Active Idle, 320W and 1,233,423 ssj_ops at 100 percent of target load, and 2,892 overall ssj_ops/watt using 2 x AMD Opteron processors Model 6278 in Supermicro 1022G-NTF server, 64GB (8 x 8GB DDR3-1600) memory, Supermicro PWS-563-1H20 power supply, 240GB SATA disk drive, Microsoft® Windows Server® 2008 R2 x64 Enterprise Edition. SPEC and SPECjbb are registered trademarks of the Standard Performance Evaluation Corporation. See www.spec.org.
(3) LAMMPS: 304 rating with 2 x AMD Opteron processors Model 6380 in Supermicro H8DGT server, 64GB (8 x 8GB DDR3-1600) memory, SuSE Linux® Enterprise Server 11 SP2 64-bit, GCC 4.7.0 Compiler, OMPI 1.5.3
Compiler Flags: -O3 -freciprocal-math -march=bdver1 -mavx -mfma4. 301 rating with 2 x Intel Xeon processors Model E5-2690 in Supermicro X9DRT-HIBFF server, 64GB (8 x 8GB DDR3-1600) memory, SuSE Linux® Enterprise Server 11 SP2 64-bit, Intel Professional Compiler v12.1.3, OMPI 1.6.0+knem 0.9.8, Hyper-Threading disabled, Turbo Boost Technology enabled. Compiler Flags: -O3 -fno-alias -ip -unroll0 -no-prec-div. NAMD: 2268 rating with 2 x AMD Opteron processors Model 6380 in Supermicro H8DGT server, 64GB (8 x 8GB DDR3-1600) memory, SuSE Linux® Enterprise Server 11 SP2 64-bit, GCC 4.7.0 Compiler, OMPI 1.6.0+Knem 0.9.8. Compiler Flags: -O3 -m64 -march=bdver1 -mfa4 -mavx. 2193 rating with 2 x Intel Xeon processors Model E5-2690 in Supermicro X9DRT-HIBFF server, 64GB (8 x 8GB DDR3-1600) memory, SuSE Linux® Enterprise Server 11 SP2 64-bit, Intel Professional Compiler v12.1.3, OMPI 1.5.5+Knem 0.98, Hyper-Threading disabled, Turbo Boost Technology enabled.
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Tara Sims
AMD Public Relations
(415) 713-5986
[email protected]
The WebRTC Summit 2015 New York, to be held June 9-11, 2015, at the Javits Center in New York, NY, announces that its Call for Papers is open. Topics include all aspects of improving IT delivery by eliminating waste through automated business models leveraging cloud technologies. WebRTC Summit is co-located with 16th International Cloud Expo, @ThingsExpo, Big Data Expo, and DevOps Summit.
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'Justified' casts Sam Elliott & Garret Dillahunt for final season roles
Want two reasons to get VERY excited about the final season of "Justified"?
Sam Elliott and Garret Dillahunt are joining the cast.
Want two reasons to get VERY excited about the final season of "Justified"?
Sam Elliott and Garret Dillahunt are joining the cast.
CBS has scheduled its new drama "Madam Secretary" to air on Sunday nights before "The Good Wife," which means two things: 1)You should expect its start time to often be interfered with by football (though its regular timeslot is 8 p.m. Eastern, it's tentatively set to debut this weekend at 8:30), and 2)CBS hopes that Téa Leoni and friends can do for political drama what Julianna Margulies and company have done for the law genre: find a way to juggle the formulaic procedural qualities of a broadcast network drama with the narrative and moral complexities of what you can find on cable.
A quick review of the "You're the Worst" season finale coming up just as soon as my boys expect the trash juice...
FX entered this summer with more programming inventory than it's ever had in a compressed period: "The Strain" on Sundays (the first time FX has had to put one of its dramas there), "Partners" on Mondays, "Tyrant" on Tuesdays, "The Bridge" on Wednesdays and "Married" and "You're the Worst" on Thursdays. Though "The Strain" has been a success and got renewed weeks ago, it's been a rough go for almost everything else.
A man who decides the best way to fight crime in his native city is to dress up as a giant bat has to be a severely damaged individual on some level. But think about how damaged the city itself has to be for the man to think that the bat costume is necessary.
FOX's new drama series "Gotham" (it debuts Monday at 8) wants to dramatize the crumbling infrastructure of Gotham City, which would eventually lead to Batman patrolling its streets. And it wants to play with the many wonderful toys available in that corner of the DC Universe, even if Batman himself can't be one of them, since the series begins with a 12-year-old Bruce Wayne (David Mazouz) witnessing his parents' murder in a dark downtown alley.
A review of tonight's "The Bridge" coming up just as soon as my beard affords me special powers...
On Monday, I posted my review of NBC's "The Mysteries of Laura." Now it's your turn. For those who tuned in tonight, what did you think? Did you find it funny or grating? Do you have any idea yet how Debra Messing can possibly be both a cop and a mom? Were you engaged by the mystery, or too busy wondering why NYPD detectives were so busy investigating a case in Westchester? Do you have an impulse to go shopping at Laura's preferred big box store? And will you watch again? Or would you just rather listen to Linda Holmes' "CopMom MomCop" theme song?
Have at it.
I've already published my review of "Red Band Society." Now it's your turn. For those who tuned in tonight, what did you think? Too much "Glee" in a hospital, or not enough? Did you like the narration, or did you want Coma Boy to pipe down? Did any of the characters pop for you? Did your prior feelings for Coldplay enhance or detract from the final sequence? And will you watch again?
Have at it.
Late last month, Amazon released its third batch of series pilots, ahead of the premieres of any of the shows from the second batch. ("Transparent" is being released on the 26th, and I'll have a bunch of content about that next week.) "Red Oaks" — a comedy about a teenage tennis pro at a New Jersey country club in the summer of 1985, created by Gregory Jacobs and Joe Gangemi, directed by David Gordon Green and produced by Steven Soderbergh— was easily my favorite of the five new pilots (you can watch it here), and I'm hopeful that after the round of costumer feedback concludes at the end of this month, Amazon will order it to series.
A review of tonight's "The Mindy Project" season premiere coming up just as soon as I keep a box of my ex's hair for curses...


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- Product Information
Product Description
Don't forget about Uncle Sam's captivating counterpart Columbia! This legendary lass has been inspiring American spirit for years and now you can evoke her spirit in this sassy ensemble. This Adult Aunt Columbia Costume is a vision in vibrant patriotic colors and dazzles with glittering details. She's a feminine firecracker that is sure to be the life of all patriotic parties. She's as American as apple pie in this fabulous frock. Adult Aunt Columbia Costume includes; polyester sequin halter dress featuring a blue and silver top with a radiant red and white striped skirt and coordinating mini top hat. Shoes and petticoat not included. One size fits most adults.
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- Reviews
Spend a Day in Paris with a Paris Party!
Add a Paris theme to any type of soiree with the help of Paris decorations and French treats. Use these party planning tips and ideas to help you prepare for your party!
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Add an 80's theme to an upcoming party of event! Use these party tips to help you set up for an 80's theme party, complete with decorations, food ideas and more.
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Throwing a party? Try using a mix of pink and gold colors to create the color scheme for your party décor. This color combination can be used for birthday parties, bridal parties, baby showers, and much more!


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Fill out the Quit Claim Deed
Generally you should be able to find a Quit Claim Deed form in a business supply store or online. The form will require the name of the Grantor, the name of the Grantee, the marital state of each party, the legal description and the Permanent Index Number for the property and the address of the property. Depending on the County where the Deed is being recorded, it may or may not need to be notarized, but for the protection of the Grantee, to assure that there is no question that the Grantor intended to give the Deed, it would be a good idea to have the signature notarized.
Check recording requirements
You will need to check the recording requirements of the city and county where the deed is being recorded to determine whether there are any transfer or exemption stamps required. Upon meeting all the requirements, the Deed should be recorded with the Recorder of Deeds for the county in which the property resides.


text: Winnipeg Jets Dustin Byfuglien Andrew Copp Keaton Ellerby Toby Enstrom Michael Frolik T.J. Galiardi Matt Halischuk Jay Harrison Michael Hutchinson Andrew Ladd Bryan Little Adam Lowry Tyler Myers Eric O'Dell Adam Pardy Ondrej Pavelec Anthony Peluso Paul Postma Mark Scheifele Jim Slater Drew Stafford Lee Stempniak Mark Stuart Chris Thorburn Jiri Tlusty Jacob Trouba Blake Wheeler Close #14 Anthony Peluso Jets Right Wing Dashboard Career stats Game log born APR. 18 1989 Drafted '07 Years Experience 3 Age 25 Height 6'3" Weight 235 Seasonal Stats Filter by Season: Season 2013 Season 2014 Season 2013 Season 2014 Season Goals Assists Points +/- Loading... NHL Western Conference Central Division Jets pt league name Anthony Peluso Season leader League Leader More Anthony Peluso NHL Nashville Predators center Filip Forsberg, center, of Sweden, is congratulated after scoring a goal against the Winnipeg Jets in the second period of an NHL hockey game, Thursday, Feb. 12, 2015, in Nashville, Tenn. (AP Photo/Mark Zaleski) Forsberg sets team rookie mark as Predators beat Jets 3-1 0 0 0 0 0 0 0 More NHL Chicago Blackhawks' Johnny Oduya (27) plays the puck as he is hauled down by Winnipeg Jets' Blake Wheeler (26) during the first period of an NHL hockey game Friday, Feb. 6, 2015, in Winnipeg, Manitoba. (AP Photo/The Canadian Press, John Woods) Saad's overtime goal lifts Blackhawks past Jets 2-1 0 0 0 0 0 0 0 More NHL Winnipeg Jets' Andrew Ladd (16), Blake Wheeler (26), Ben Chiarot (63), Bryan Little (18) and Dustin Byfuglien (33) celebrate Wheeler's goal as Columbus Blue Jackets' David Savard (58) skates past during the first period of an NHL hockey game Wednesday, Ja Hutchinson stops 29 shots in Jets' 4-0 win over Blue Jackets 0 0 0 0 0 0 0 More NHL Los Angeles Kings defenseman Jake Muzzin, left, and Winnipeg Jets right wing Blake Wheeler battle for the puck during the first period of an NHL hockey game, Saturday, Jan. 10, 2015, in Los Angeles. Los Angeles Kings defenseman Matt Greene is at right. (A Jets score on first 3 shots, beat Kings in shootout 0 0 0 0 0 0 0 More Load More 01 02 03 04 05 06 07 08 09 Next Page


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Country/Date of Origin: United States/1800s
In spite of its name, the Australian Shepherd did not originate in Australia. It was "made in the USA" from stock that immigrating Basque sheepherders brought with them. First and foremost this is a working animal and indeed the majority of Australian Shepherds are worked with stock today. The breed became stabilized in the early 20th century and was recognized first by the Canadian and Mexican Kennel Clubs and finally by the American Kennel Club in 1993.
About This Breed:
Other Names
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Sometimes, manufacturers require that products be advertised only at their suggested prices.
When we choose to sell these items for less, we display the sale price only in the cart. To see the price, click Add to Cart.
AKC Group: Herding
Breed Club: United States Australian Shepherd Association
Rescue Club: Aussie Rescue and Placement Helpline, Inc; Second Time Around Aussie Rescue, Inc
Body Type:
Health Concerns:


text: Billy Currington Rocked The South Plains Fair By Woodson Rowan January 17, 2011 8:04 PM Share on Facebook Share on Twitter Billy Currington kick starts the South Plains Fair Show with "Everything" (9-29-10). VIDEOS Follow the Jump And we all know this one: God is Great, Beer is Good… Women are Crazy! AND Here's one for Lucious and the Boys of Badger Holler! Filed Under: Billy Currington, concert, Everything, live, People Are Crazy, South Plains Fair Category: Concerts, Music, Videos Share on Facebook Share on Twitter More Leave a comment Send to a friend! Print this page Pin it! Reddit This! Share on Tumblr! Best of Lonestar 99.5 Recommended For You Around the Web


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Phoenix Suns
ESPN Insider: Isaiah Thomas among best free agent signings
While his role is unclear, the Phoenix Suns signing Isaiah Thomas to a four-year, $27 million deal was ranked as the one of the top free-agent signings of the offseason, according to ESPN Insider Tom Haberstroh.
Haberstroh uses age and 2013-14 wins above replacement (WAR) to calculate a player's annual contract value. He says Thomas is worth $11.1 million annually, with the Suns' surplus on the deal more than $4 million annually.
Thomas, 25, averaged 20.3 points and 6.3 assists last season with the Sacramento Kings.
Haberstroh thinks the Kings were worried about his 5-foot-9 height instead of his scoring ability. Here is what he says about the signing:
This is Asset Accumulation 101 by Phoenix GM Ryan McDonough. Considering the Suns might have Eric Bledsoe and Goran Dragic in their backcourt, acquiring Thomas might seem like point guard gluttony. But smart teams find talent at discount prices, then deal with fit issues later.
Former Suns power forward Channing Frye was also on the list, with Haberstroh saying Frye was worth $12.2 million annually, while the Orlando Magic gave him a four-year contract worth $32 million.
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- Tim Kempton, Suns analyst and Notre Dame alumnusTK explains what Notre Dame has to do to have a chance against Kentucky in the Elite Eight.
- Mike D'Antoni- Former NBA head coachYou won't see Mike D'Antoni coaching college basketball.
- Lon Babby- Suns president of basketball operationsLon Babby says the Suns gave up an opportunity in their playoff race.


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Reel World
By Devin D. O'Leary
Come One, Come Bald
Film Review
Enter The Void
Sex and death make for the ultimate trip in Gaspar Noé's eye-bending flight of fancy
By Devin D. O'Leary
Video Review
The Car (1977)
By Kurly Tlapoyawa
Idiot Box
Been There, Done Chat
"Conan" on TBS
By Devin D. O'Leary
Today's Events
Aliens (1986) at KiMo Theatre
The sequel to Ridley Scott's famous sci-fi franchise, starring Sigourney Weaver and Michael Biehn. Part of the Sci-Fi Fridays film series.
Tomorrow's Events
Resistance is Futile: A Star Trek Quiz at O'Neill's Heights
Holbrook/Twain at Guild CinemaMore Recommented Events ››
BeLowLife Vids'n'Vinyl • 4.30.2015
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They want trade unions to take up their issue 'seriously'
Despite the non-responsive attitude of the Haryana Government and the Maruti Suzuki management, the dismissed workers of the Manesar plant of the company have not lost hope. To bring to the attention of the political class their continued plight, they organised a protest at Jantar Mantar here on Wednesday.
After the July 18 violence at the Manesar plant in which one senior executive was killed, the company had terminated the services of 546 "permanent" and 1,800 "temporary" workers. The police arrested 149 of them, including the office-bearers of Maruti Suzuki Workers Union (MSWU), for alleged involvement in the violence.
Despite the fact that trade union groups were supporting them in their struggle for reinstatement and withdrawal of "false" cases against their jailed colleagues and leaders of the MSWU, the protesting workers said they needed to take their struggle "much more seriously".
While addressing the protesters, Tapish of the Bigul Mazdoor Dasta said a much bigger nationwide struggle was needed possibly involving "a nationwide hartal" in all the factories across the country.
The protesting workers alleged that an all-out war has been waged against them by the Maruti Suzuki management in nexus with the Haryana Government because they expressed their right to form workers' union and questioned the "illegal" practice of contract worker system.
Their demands include an unbiased judicial inquiry into the violent incident apart from the release of all their colleagues. They also demanded that workers union must be formed in the auto belt industrial region including Gurgaon, Manesar, Dharuhera, Bawal, Faridabad, Noida and Ghaziabad.