IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
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출원번호 |
US-0091680
(2005-03-28)
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등록번호 |
US-7334990
(2008-02-26)
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발명자
/ 주소 |
- Lawlor,Shawn P.
- Novaresi,Mark A.
- Cornelius,Charles C.
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출원인 / 주소 |
- Ramgen Power Systems, Inc.
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
18 인용 특허 :
41 |
초록
▼
A gas compressor based on the use of a driven rotor having an axially oriented compression ramp traveling at a local supersonic inlet velocity (based on the combination of inlet gas velocity and tangential speed of the ramp) which forms a supersonic shockwave axially, between adjacent strakes. In us
A gas compressor based on the use of a driven rotor having an axially oriented compression ramp traveling at a local supersonic inlet velocity (based on the combination of inlet gas velocity and tangential speed of the ramp) which forms a supersonic shockwave axially, between adjacent strakes. In using this method to compress inlet gas, 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 gasdyanamic flow path formed between the gas compression ramp on a strake, the shock capture lip on the adjacent strake, and captures the resultant pressure within the stationary external housing while providing a diffuser downstream of the compression ramp.
대표청구항
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The invention claimed is: 1. A gas compressor, said compressor comprising: (a) a circumferential housing, said housing having a stationary peripheral wall, said stationary peripheral wall having a inner surface portion defined by a surface of rotation; (b) an inlet for supply of gas to be compresse
The invention claimed is: 1. A gas compressor, said compressor comprising: (a) a circumferential housing, said housing having a stationary peripheral wall, said stationary peripheral wall having a inner surface portion defined by a surface of rotation; (b) an inlet for supply of gas to be compressed; (c) a rotor, said rotor having a central axis and adapted for rotary motion within said housing, said rotor extending radially outward from said central axis to an outer surface portion; (d) one or more strakes, each of said one or more strakes extending outward from said outer surface portion of said rotor to a tip end, said tip end adjacent to said inner surface portion of said stationary peripheral wall, at least one of said one or more strakes further comprising (i) an upstream end having an inlet, (ii) downstream from said inlet, a supersonic compression ramp, said ramp oriented to develop an axially oriented supersonic shock during compression of an inlet gas, and (iii) a shock capture lip, said shock capture lip axially displaced from said supersonic compression ramp and positioned at a location on said outer surface of said rotor so that said shock compression ramp and said shock capture lip effectively contain a supersonic shock wave therebetween at a selected design Mach number; (e) a outlet diffuser, said diffuser situated downstream of said supersonic compression ramp; and (f) wherein said one or more strakes separate said inlet gas from compressed gas downstream of each one of said supersonic gas compression ramps. 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 to said tip end. 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 an axially directed, upstream narrowing gas compression ramp face. 5. The apparatus as set forth in claim 1, or claim 2, 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 1, wherein said gas compression ramps further comprise (a) a throat, and (b) an inwardly sloping gas deceleration ramp. 9. The apparatus as set forth in claim 5, wherein each of said gas compression ramps further form, adjacent thereto and in corporation with one of said at least one strakes, a bleed air receiving chamber, and wherein each of said bleed air receiving chambers effectively contains therein, for ejection therefrom, bleed air routed thereto. 10. The apparatus as set forth in claim 1, further comprising a gas outlet, said gas outlet configured to receive and pass therethrough high pressure outlet gas after resulting from compression of gas. 11. The apparatus as set forth in claim 1, wherein the apparent velocity of gas entering said one or more gas compression ramps is in excess of Mach 1. 12. The apparatus as set forth in claim 11, wherein the apparent velocity of gas entering said one or more gas compression ramps is in excess of Mach 2. 13. The apparatus as set forth in claim 11, wherein the design apparent velocity of gas entering said one or more gas compression ramps is between about Mach 1.5 and Mach 3.5. 14. The apparatus as set forth in claim 1, wherein said apparatus is configured to compress a gas selected from the group consisting of (a) air, (b) refrigerant, (c) steam, and (d) hydrocarbons. 15. The apparatus as set forth in claim 1, or in claim 14, wherein said apparatus compresses a selected gas at an isentropic efficiency of at least eighty percent (80%). 16. The apparatus as set forth in claim 1, or in claim 14, wherein said apparatus compresses a selected gas at an isentropic efficiency of at least eight five percent (85%). 17. The apparatus as set forth in claim 1, or in claim 14, wherein said apparatus compresses a selected gas at an isentropic efficiency of ninety (90) percent or more. 18. The apparatus as set forth in claim 1, or in claim 14, wherein said apparatus compresses a selected gas at an isentropic efficiency of ninety five (95) percent or more. 19. The apparatus of claim 1, or claim 14, wherein said rotor comprises a central disc. 20. The apparatus as set forth in claim 1, or in claim 14, 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. 21. A method of compressing gas, comprising: (a) providing one or more gas compression ramps on a rotor which is rotatably secured with respect to stationary housing having an inner surface; (b) supplying to each of said one or more gas compression ramps an inlet gas stream; (c) compressing said inlet gas stream between said one or more gas compression ramps and said stationary housing, to generate a high pressure gas therefrom; (d) 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; (e) driving said rotor by an input shaft operatively connected to said one or more gas compression ramps. 22. The method as recited in claim 21, wherein the apparent inlet velocity of said one or more gas compression ramps is at least Mach 2.5. 23. The method as recited in claim 22, wherein the inlet velocity of said one or more gas compression ramps is between Mach 2.5 and Mach 4. 24. The method as recited in claim 23, wherein the apparent inlet velocity of said gas compression ramps is approximately Mach 3.5. 25. The method as recited in claim 24, wherein said gas is selected from the group consisting of (a) air, (b) steam, (c) refrigerant, and (d) hydrocarbons. 26. The method as recited in claim 25, wherein said gas is essentially natural gas. 27. The method as recited in claim 23, wherein said gas is air. 28. The method as recited in claim 23, wherein said gas comprises a refrigerant. 29. The method as recited in claim 23, wherein said gas comprises steam. 30. The method as recited in claim 23, 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. 31. The method as recited in claim 30, 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. 32. The method as set forth in claim 23, wherein the helical strakes are offset at a preselected angle delta. 33. The apparatus as set forth in claim 1, wherein said upstream strake, said downstream strake, and said compression ramp cooperate to form a mixed compression inlet. 34. The apparatus as set forth in claim 33, further comprising a centerbody diffuser downstream of said compression ramp, said diffuser bifurcating a gas dynamic flow path circumferentially about said rotor. 35. The apparatus as set forth in claim 1, wherein said upstream strake, said downstream strake, and said compression ramp cooperate to form an internal compression inlet. 36. The apparatus as set forth in claim 35, wherein said apparatus comprises a pair of opposing gas compression ramps. 37. A gas compressor, comprising: (a) 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; (b) a first drive shaft, said first drive shaft rotatably secured along an axis of rotation with respect to said support structure; (c) a first rotor, said first rotor rotatably affixed with said first drive 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 axially oriented 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, (d) said gas compressor adapted to utilize at least a portion of said inner side surface of said first circumferential housing to contain compressed gas thereagainst; (e) 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 (f) a first high pressure compressed gas outlet. 38. The apparatus as set forth in claim 37, further comprising: (a) a second rotor, said second rotor rotatably affixed with said first drive shaft for rotation with respect to said support structure, said second rotor further comprising a second circumferential portion having a second outer surface portion, said second rotor comprising one or more axially oriented gas compression ramps, each one of said gas compression ramps comprising a portion integrally provided as part of said circumferential portion of said second rotor, (b) said gas compressor adapted to utilize at least a portion of said inner side surface of said second circumferential housing to contain compressed gas thereagainst; (c) one or more strakes on said second rotor, wherein one of said one or more strakes on said second rotor is provided for each of said one or more gas compression ramps, and wherein each of said one or more strakes on said second rotor extends outward from at least a portion of said circumferential portion of said second rotor to a point adjacent to said inner side surface of said second circumferential housing; and (d) a second high pressure compressed gas outlet. 39. The apparatus as set forth in claim 38, wherein said first and second high pressure gas outlets are in fluid communication with a single high pressure gas outlet nozzle. 40. The apparatus as set forth in claim 38, 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. 41. The apparatus as set forth in claim 40, 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. 42. The apparatus as set forth in claim 38, wherein each of said one or more gas compression ramps comprises an axially sloping gas compression ramp, said ramp having a base, a face, and a throat, and wherein said base is located adjacent the intersection of said axially sloping face and said downstream strake of said rotor. 43. The apparatus as set forth in claim 40 wherein each of said one or more gas compression ramps further comprise one or more boundary layer bleed ports. 44. The apparatus as set forth in claim 43, wherein at least one of said one or more boundary bleed ports is located at said base of said gas compression ramps. 45. The apparatus as set forth in claim 43, wherein at least one of said one or more boundary bleed ports is located at said face of said gas compression ramp. 46. The apparatus as set forth in claim 43, wherein at lest one of said one or more boundary bleed ports is located at said throat of said gas compression ramp. 47. The apparatus as set forth in claim 37, wherein each of said gas compression ramps further comprise a bleed air receiving chamber adjacent thereto, and wherein each of said bleed air receiving chambers effectively contains therein, for ejection therefrom, bleed air provided thereto. 48. The apparatus as set forth in claim 37, 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. 49. The apparatus as set forth in claim 48, further comprising a second inlet casing containing therein a second pre swirl impeller, said second preswirl impeller located intermediate said gas inlet and said second rotor, said second pre-swirl impeller configured for compressing said inlet gas to a pressure intermediate the pressure of said inlet gas and said outlet gas. 50. The apparatus as set forth in claim 49, wherein said first and said second pre-swirl impellers are configured to provide a compression ratio of up to about 2:1. 51. The apparatus as set forth in claim 50, wherein said first and said second pre-swirl impellers are configured to provide a compression ratio from about 1.3:1 to about 2:1. 52. The apparatus as set forth in claim 49, further comprising, downstream of said first and said second pre-swirl impellers and upstream of said one or more gas compression ramps on said first and said second rotors, respectively, 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 on said first rotor and on said second rotor. 53. The apparatus as set forth in claim 49, wherein said first and said second preswirl impellers each comprise a centrifugal compressor. 54. The apparatus as set forth in claim 49, wherein said first and said second pre-swirl impeller is mounted on a common shaft with said first rotor and with said second rotor.
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