Gas turbine power plant with supersonic shock compression ramps
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-001/00
F02G-003/00
출원번호
US-0102937
(2005-03-30)
등록번호
US-7434400
(2008-10-14)
발명자
/ 주소
Lawlor,Shawn P.
Novaresi,Mark A.
Cornelius,Charles C.
출원인 / 주소
Lawlor,Shawn P.
Novaresi,Mark A.
Cornelius,Charles C.
대리인 / 주소
Goodloe, Jr.,R. Reams
인용정보
피인용 횟수 :
14인용 특허 :
43
초록▼
A gas turbine engine. The engine is based on the use of a gas turbine driven rotor having a compression ramp traveling at a local supersonic inlet velocity (based on the combination of inlet gas velocity and tangential speed of the ramp) which compresses inlet gas against a stationary sidewall. The
A gas turbine engine. The engine is based on the use of a gas turbine driven rotor having a compression ramp traveling at a local supersonic inlet velocity (based on the combination of inlet gas velocity and tangential speed of the ramp) which compresses inlet gas against a stationary sidewall. The supersonic compressor efficiently achieves high compression ratios while utilizing a compact, stabilized gasdynamic flow path. Operated at supersonic speeds, the inlet stabilizes an oblique/normal shock system in the gasdynamic flow path formed between the rim of the rotor, the strakes, and a stationary external housing. Part load efficiency is enhanced by use of a lean pre-mix system, a pre-swirl compressor, and a bypass stream to bleed a portion of the gas after passing through the pre-swirl compressor to the combustion gas outlet. Use of a stationary low NOx combustor provides excellent emissions results.
대표청구항▼
What is claimed is: 1. A gas turbine power plant, said power plant comprising: (a) a compressor section, said compressor section comprising (1) an inlet for supply of gas to be compressed; (2) a rotor, said rotor having a central axis and adapted for rotary motion thereabout, said rotor extending r
What is claimed is: 1. A gas turbine power plant, said power plant comprising: (a) a compressor section, said compressor section comprising (1) an inlet for supply of gas to be compressed; (2) a rotor, said rotor having a central axis and adapted for rotary motion thereabout, said rotor extending radially outward from said central axis to an outer surface portion having an outer extremity; (3) one or more supersonic shock compression ramps, each one of said supersonic shock compression ramps forming a features on said outer surface portion of said rotor; (4) a stationary peripheral wall, said stationary peripheral wall (i) positioned radially outward from said central axis, and (ii) positioned very slightly radially outward from said outer extremity of said rotor; and (iii) having an interior surface portion; (5) said one or more supersonic shock compression ramps and said stationary peripheral wall cooperating to compress said gas therebetween; (6) one or more strakes, each of said one or more strakes provided adjacent to one of said or more supersonic compression ramps, and at least a portion of each of said one or more strakes extending outward from at least a portion of said outer surface portion of said rotor to a point adjacent said interior surface portion of said peripheral wall, and wherein said one or more strakes effectively separate said inlet gas from compressed gas downstream of each one of said supersonic gas compression ramps; and (b) a gas turbine section, said gas turbine section comprising (1) a combustor, said combustor including (i) a high pressure combustion air chamber receiving combustion air from said compressor section, (ii) a burner section receiving fuel from a fuel supply source and air from said combustion air chamber to burn said fuel and to create energetic combustion gases exiting therefrom, (2) one or more gas turbines, said gas turbines operatively affixed to said shaft, said gas turbines adapted to receiving hot pressurized combustion gases from said combustor and to expand said hot pressurized combustion gases outward therethrough by reacting said gases with said one ore more gas turbines, to produce shaft power; (3) an exhaust gas outlet, said exhaust gas outlet adapted to receive said hot pressurized combustion gases after passage through said one or more gas turbines. 2. The apparatus as set forth in claim 1, wherein each of said one or more strakes comprises a helical structure extending substantially radially from said outer surface portion of said rotor. 3. The apparatus as set forth in claim 2, wherein the number of said one or more helical strakes is N, and the number of said one or more supersonic gas compression ramps is X, and wherein N and X are equal. 4. The apparatus as set forth in claim 1 or in claim 2, wherein each of said one or more gas compression ramps comprises a outwardly sloping gas compression ramp face, said face having a base, said base located adjacent the intersection of said outwardly sloping face and said outer surface portion of said rotor. 5. The apparatus as set forth in claim 1, wherein each of said one or more gas compression ramps further comprise one or more boundary layer bleed ports. 6. The apparatus as set forth in claim 5, wherein at least one of said one or more boundary bleed ports is located at said base of said gas compression ramps. 7. The apparatus as set forth in claim 5, wherein at least one of said one or more boundary bleed ports is located on said face of said gas compression ramp. 8. The apparatus as set forth in claim 4, wherein said face and said outer surface of said rotor intersect at an angle alpha from about one degree to about fifteen degrees. 9. The apparatus as set forth in claim 1, wherein said gas compression ramps further comprise (a) a throat, and (b) an inwardly sloping gas deceleration ramp. 10. The apparatus as set forth in claim 5, wherein each of said gas compression ramps further comprise a bleed air receiving chamber, and wherein each of said bleed air receiving chambers effectively contains therein, for ejection therefrom, bleed air provided thereto. 11. The apparatus as set forth in claim 1, further comprising a high pressure combustion gas outlet throat, said outlet throat configured to receive and pass therethrough high pressure outlet gas resulting from compression of gas by said one or more gas compression ramps on said rotor. 12. The apparatus as set forth in claim 11, further comprising an inlet casing containing therein a pre-swirl impeller, said pre-swirl impeller located intermediate said gas inlet and said rotor, said pre-swirl impeller configured for compressing said inlet gas to a pressure intermediate the pressure of said inlet gas and said outlet gas. 13. The apparatus as set forth in claim 12, wherein said pre-swirl impeller is configured to provide a compression ratio of up to about 2:1. 14. The apparatus as set forth in claim 12, wherein said pre-swirl impeller is configured to provide a compression ratio between about 1.3:1 to about 2:1. 15. The apparatus as set forth in claim 12, further comprising, downstream of said pre-swirl impeller and upstream of said one or more gas compression ramps on said rotor, a plurality of inlet guide vanes, said inlet guide vanes imparting spin on gas passing therethrough so as to increase the apparent inflow velocity of gas entering said one or more gas compression ramps. 16. The apparatus as set forth in claim 15, wherein said pre-swirl impeller comprises a centrifugal compressor. 17. The apparatus as set forth in claim 16, wherein said pre-swirl impeller is mounted on a common shaft with said rotor. 18. The apparatus as set forth in claim 15, wherein the apparent velocity of gas entering said one or more gas compression ramps is in excess of Mach 1. 19. The apparatus as set forth in claim 15, wherein the apparent velocity of gas entering said one or more gas compression ramps is in excess of Mach 2. 20. The apparatus as set forth in claim 15, wherein the apparent velocity of gas entering said one or more gas compression ramps is between about Mach 1.5 and Mach 3.5. 21. The apparatus as set forth in claim 12, or in claim 20, further comprising, downstream of said pre-swirl impeller, an outlet line for intermediate pressure gas, said outlet line configured to bleed a portion of said intermediate pressure gas away from said one or more gas compression ramps. 22. The apparatus as set forth in claim 21, further comprising a gas flow regulating valve, said valve configured to vary the rate of passage of intermediate pressure gas therethrough, so as to in turn vary the amount of intermediate pressure gas entering said one or more gas compression ramps. 23. The apparatus as set forth in claim 22, where in said valve is adjustable at any preselected flow rate from (a) a closed position, wherein said valves forms a seal in said bypass line, so that as a result substantially no intermediate pressure gas escapes to said outlet line, and (b) an open position, wherein said valve allows fluid communication between said pre-swirl impeller outlet and said outlet line, or (c) a preselected position between said closed position and said open position. 24. A gas turbine power plant, comprising: (a) a compressor section, said compressor section comprising (1) a support structure, said support structure comprising (i) a circumferential housing with an inner side surface, and (ii) a gas inlet for receiving low pressure inlet gas; (2) a first drive shaft, said first drive shaft rotatably secured along an axis of rotation with respect to said support structure; (3) a first rotor, said first rotor rotatably affixed with said first output shaft for rotation with respect to said support structure, said first rotor further comprising a first circumferential portion having a first outer surface portion, said first rotor comprising one or more gas compression ramps, each one of said gas compression ramps comprising a portion integrally provided as part of said circumferential portion of said first rotor, said compressor section adapted to utilize at least a portion of said inner side surface of said first circumferential housing to compress said inlet gas thereagainst; (4) one or more strakes on said first rotor, wherein one of said one or more strakes on said first rotor is provided for each of said one or more gas compression ramps, and wherein each of said one or more strakes on said first rotor extends outward from at least a portion of said circumferential portion of said first rotor to a point adjacent to said inner side surface of said first circumferential housing; and (5) a first high pressure compressed gas outlet throat; and (b) a gas turbine section, said gas turbine section comprising (1) a combustor, said combustor including (i) a high pressure combustion air chamber receiving combustion air from said compressor section, (ii) a burner section receiving fuel from a fuel supply source and air from said combustion air chamber to burn said fuel and to create energetic combustion gases exiting therefrom, and (2) one or more gas turbines, said gas turbines operatively affixed to said shaft, said gas turbines adapted to receiving hot pressurized combustion gases from said combustor and to expand said hot pressurized combustion gases outward therethrough by reacting said gases with said one ore more gas turbines, to produce shaft power; and (3) an exhaust gas outlet, said exhaust gas outlet configured to received said hot pressurized combustion gases after passage through said one or more gas turbines. 25. The apparatus as set forth in claim 24, wherein said one or more gas turbines includes a single stage radial turbine. 26. The apparatus as set forth in claim 25, wherein said one or more gas turbines includes at least one axial turbine. 27. The apparatus as set forth in claim 25, wherein each of said one or more strakes on said first rotor and on said second rotor comprises a helical structure extending substantially radially from said outer surface portion of said first rotor or said second rotor, respectively. 28. The apparatus as set forth in claim 27, wherein the number of said one or more helical strakes on said first rotor or on said second rotor is N, and the number of said one or more supersonic gas compression ramps on said first rotor or on said second rotor is X, and wherein N and X are equal. 29. The apparatus as set forth in claim 25, wherein each of said one or more gas compression ramps comprises a outwardly sloping gas compression ramp face, said face having a base, said base located adjacent the intersection of said outwardly sloping face and said outer surface portion of said first rotor. 30. The apparatus as set forth in claim 29 wherein each of said one or more gas compression ramps further comprise one or more boundary layer bleed ports. 31. The apparatus as set forth in claim 30, wherein at least one of said one or more boundary bleed ports is located at said base of said gas compression ramps. 32. The apparatus as set forth in claim 30, wherein at least one of said one or more boundary bleed ports is located on said face of said gas compression ramp. 33. The apparatus as set forth in claim 25, wherein each of said gas compression ramps further comprise a bleed air receiving chamber, and wherein each of said bleed air receiving chambers effectively contains therein, for ejection therefrom, bleed air provided thereto. 34. The apparatus as set forth in claim 25, further comprising a first inlet casing containing therein a first pre-swirl impeller, said first pre-swirl impeller located intermediate said gas inlet and said first rotor, said first pre-swirl impeller configured for compressing said inlet gas to a pressure intermediate the pressure of said inlet gas and said outlet gas. 35. The apparatus as set forth in claim 34, wherein said first pre-swirl impeller is configured to provide a compression ratio of up to about 2:1. 36. The apparatus as set forth in claim 34, wherein said first pre-swirl impeller is configured to provide a compression ratio from about 1.3:1 to about 2:1. 37. The apparatus as set forth in claim 35, further comprising, downstream of said first pre-swirl impeller and upstream of said one or more gas compression ramps on said first rotor, a plurality of inlet guide vanes, said inlet guide vanes shaped to impart spin on gas passing therethrough so as to increase the apparent inflow velocity of gas entering said one or more gas compression ramps on said first rotor. 38. The apparatus as set forth in claim 35, wherein said first pre-swirl impellers comprises a centrifugal compressor. 39. The apparatus as set forth in claim 35, wherein said first pre-swirl impeller is mounted on a common shaft with said first rotor. 40. The apparatus as set forth in claim 35, wherein said one or more gas turbines are each mounted on a common shaft with said first rotor. 41. The apparatus as set forth in claim 25, wherein the apparent velocity of gas entering said one or more gas compression ramps is in excess of Mach 1. 42. The apparatus as set forth in claim 25, wherein the apparent velocity of gas entering said one or more gas compression ramps is in excess of Mach 2. 43. The apparatus as set forth in claim 25, wherein the apparent velocity of gas entering said one or more gas compression ramps is between about Mach 1.5 and Mach 3.5. 44. The apparatus as set forth in claim 35, further comprising, downstream of said first pre-swirl impeller, an intermediate pressure gas outlet, said intermediate pressure gas outlet configured to route a portion of said intermediate pressure gas away from said one or more compression ramps. 45. The apparatus as set forth in claim 44, further comprising downstream of said intermediate pressure gas outlet, one or more gas flow regulating valves, said valves configured to vary the rate of passage of intermediate pressure gas therethrough, so as to in turn vary the amount of intermediate pressure gas entering said one or more gas compression ramps on said first rotor. 46. The apparatus as set forth in claim 45, where in said one or more valves are adjustable at any preselected flow rate from (a) a closed position, wherein said one or more valves form a seal in said intermediate pressure gas outlet, so that as a result substantially no intermediate pressure gas escapes to said intermediate pressure gas outlet, and (b) an open position, wherein said one or more valves allows a quantity of intermediate pressure gas to escape through said intermediate pressure gas outlet, or (c) a preselected position between said closed position and said open position. 47. The apparatus as set forth in claim 1, or in claim 24, wherein said compressor section of said apparatus is configured to compress a gas comprising atmospheric air. 48. The apparatus as set forth in claim 1, or in claim 24, wherein said apparatus compresses a selected gas at an isentropic efficiency in excess of ninety (90) percent. 49. The apparatus as set forth in claim 1, or in claim 24, wherein said apparatus compresses a selected gas at an isentropic efficiency in excess of ninety (95) percent. 50. The apparatus as set forth in claim 49, wherein said compressor section operates at a non-dimensional specific speed from about 60 to about 120. 51. The apparatus of claim 1, or claim 24, wherein said rotor comprises a central disc. 52. The apparatus of claim 51, wherein said central disc is tapered, at least in part. 53. The apparatus as set forth in claim 1, or in claim 24, wherein at least a portion of said rotor is confined within a close fitting housing having a minimal distance D between said rotor and said housing, so as to minimize aerodynamic drag on said rotor. 54. A method of operating a gas turbine power plant, comprising (a) providing a compressor section, comprising: (1) providing one or more gas compression ramps on a rotor which is rotatably secured with respect to stationary housing having an inner surface; (2) supplying to each of said one or more gas compression ramps an inlet gas stream; (3) compressing said inlet gas stream between said one or more gas compression ramps and said stationary housing, to generate a high pressure gas therefrom; (4) effectively separating inlet gas from high pressure gas by using one or more strakes along the periphery of said rotor, each of said one or more strakes provided adjacent to one of said or more gas compression ramps, and at least a portion of each of said one or more strakes extending outward from at least a portion of an outer surface portion of said rotor to a point adjacent said inner surface of said stationary housing; and (b) providing a gas turbine section, comprising (1) providing a combustor, said combustor including (i) a high pressure combustion air chamber receiving combustion air from said compressor section, (ii) a burner section receiving fuel from a fuel supply source and air from said combustion air chamber to burn said fuel and to create hot, pressurized, energetic combustion gases exiting therefrom, and (2) providing one or more gas turbines, said gas turbines operatively affixed to said shaft, said gas turbines adapted to receiving said hot, pressurized, energetic combustion gases from said combustor and to expand said hot pressurized combustion gases outward therethrough by reacting said gases with said one ore more gas turbines, to produce output shaft power; (3) driving said rotor for compression of combustion air by operatively directing a portion of said output shaft power to turn said rotor and said one or more gas compression ramps. 55. The method as recited in claim 54, wherein the apparent inlet velocity of said one or more gas compression ramps is at least Mach 2.5. 56. The method as recited in claim 54, wherein the inlet velocity of said one or more gas compression ramps is between Mach 2.5 and Mach 4. 57. The method as recited in claim 54, wherein the apparent inlet velocity of said gas compression ramps is approximately Mach 3.5. 58. The method as recited in claim 54, wherein said combustion gas comprises ambient atmospheric air. 59. The method as recited in claim 56, wherein said fuel gas is essentially natural gas. 60. The method as recited in claim 54, further comprising the step of minimizing aerodynamic drag by minimizing the number of leading edge surfaces subjected to stagnation pressure. 61. The method as recited in claim 60, wherein the number of leading edge surfaces subjected to stagnation pressure is less than five. 62. The method as recited in claim 60, wherein the number of leading edge surfaces subjected to stagnation pressure is four. 63. The method as recited in claim 54, wherein each of said one or more gas compression ramps are circumferentially spaced equally apart so as to engage said supplied gas stream substantially free of turbulence from the previous passage through a given circumferential location of any one said one or more gas compression ramps. 64. The method as recited in claim 54, wherein the cross sectional areas of each of the one or more gas compression ramps are sized and shaped to provide a desired compression ratio. 65. The method as set forth in claim 54, wherein said helical strakes are offset at a preselected angle delta, and wherein the angle of offset matches the angle of offset of each one of said one or more gas compression ramps, and wherein said angles match to allow gas entering the one or more gas compression ramps to be at approximately the same angle as the angle of offset, to minimize inlet losses. 66. The method as set forth in claim 54, further comprising, downstream of said first pre-swirl impeller, an intermediate pressure gas outlet, and wherein said method further comprises the step of bleeding a portion of gas at said intermediate pressure outward through said intermediate pressure gas outlet. 67. The method as set forth in claim 66, wherein said intermediate pressure gas outlet further comprises a bypass line having a control valve, and wherein said method comprises adjusting said control valve to a preselected flow rate from (a) a closed position, wherein said valve forms a seal in said first bypass line, so that as a result substantially no intermediate pressure gas escapes through said intermediate pressure gas outlet, and (b) an open position, wherein said valve allows intermediate pressure gas to escape said intermediate pressure gas outlet, or (c) a preselected position between said closed position and said open position. 68. The method as set forth in claim 67, wherein said bypass line routes intermediate pressure gas to mix with said combustion gases exiting from said gas turbine. 69. The method as set forth in claim 67, wherein said bypass line routes intermediate pressure gas to an atmospheric bleed outlet. 70. The method as set forth in claim 67, wherein said bypass line routes intermediate pressure gas to a compressed air supply system. 71. The method as set forth in claim 67, wherein said burner has an equivalence ratio, and wherein said equivalence ratio is maintained constant during at least a portion of the transition of said bypass valve from said closed position to said open position. 72. The method as set forth in claim 71, wherein said burner has a flame, and wherein the temperature of combustion at said flame is maintained constant during at least a portion of the transition of said bypass valve from said closed position to said open position. 73. The method as set forth in claim 71, wherein operation of said gas turbine engine at part load power is accomplished without violating lean extinction limits. 74. The method as set forth in claim 71, wherein operation of said gas turbine engine at part load power is accomplished without violating combustion stability limits. 75. The method as set forth in claim 71, wherein operation of said gas turbine engine at part load power is accomplished at NOx emission levels below about 10 ppm. 76. The method as set forth in claim 71, wherein operation of said gas turbine engine at part load power is accomplished at NOx emission levels below about 8 ppm. 77. The method as set forth in claim 71, wherein operation of said gas turbine engine at part load power is accomplished at NOx emission levels to as lows as about 6 ppm.
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