IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0355702
(2009-01-16)
|
등록번호 |
US-8152439
(2012-04-10)
|
발명자
/ 주소 |
|
출원인 / 주소 |
- Ramgen Power Systems, LLC
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
3 인용 특허 :
20 |
초록
▼
A supersonic gas compressor. The compressor includes aerodynamic duct(s) situated on a rotor journaled in a casing. The aerodynamic duct(s) generate a plurality of oblique shock waves for efficiently compressing a gas at supersonic conditions. The convergent inlet is adjacent to a bleed air collecto
A supersonic gas compressor. The compressor includes aerodynamic duct(s) situated on a rotor journaled in a casing. The aerodynamic duct(s) generate a plurality of oblique shock waves for efficiently compressing a gas at supersonic conditions. The convergent inlet is adjacent to a bleed air collector, and during acceleration of the rotor, bypass gas is removed from the convergent inlet via a collector to enable supersonic shock stabilization. Once the oblique shocks are stabilized at a selected inlet relative Mach number and pressure ratio, the bleed of bypass gas from the convergent inlet via the bypass gas collectors is eliminated.
대표청구항
▼
1. A method for starting a supersonic gas compressor, said supersonic gas compressor comprising one or more aerodynamic ducts mounted for rotary movement, said one or more aerodynamic ducts comprising a converging inlet portion and a diverging outlet portion, said aerodynamic duct comprising one or
1. A method for starting a supersonic gas compressor, said supersonic gas compressor comprising one or more aerodynamic ducts mounted for rotary movement, said one or more aerodynamic ducts comprising a converging inlet portion and a diverging outlet portion, said aerodynamic duct comprising one or more structures that at supersonic inflow conditions generate oblique shock waves in a gas within said converging inlet portion and a normal shock wave in a gas as said gas enters or passes through said diverging outlet portion, said aerodynamic duct having an inlet relative Mach number with a design operating point selected within a design operating envelope for a selected gas composition, gas quantity, and gas compression ratio, said method comprisinginitiating rotary movement of said converging inlet portion of said one or more aerodynamic duct(s)s with an inlet gas stream to be compressed;removing a selected quantity of bypass gas from said converging inlet portion as said one or more aerodynamic duct(s) increase in rotary speed while said gas therein transforms from a subsonic inflow condition to a supersonic condition at an inlet relative Mach number associated with said design operating point, said selected quantity of bypass gas at an inlet relative Mach number associated with said design operating point being between (a) an upper limit described by the equation (mbld/mcap)=0.0329M4−0.3835M3+1.5389M2−2.150M+0.9632 and (b) a lower limit described by the equation (mbld/mcap)=0.0197M4−0.230M3+0.9233M2−1.29M+0.5779 wherein mbld=mass of bypass gas removed from said aerodynamic duct(s),mcap=mass of gas captured by said aerodynamic duct(s),M=the inlet relative Mach number for the aerodynamic duct(s), andeffectively eliminating removal of said quantity of bypass gas from said converging inlet portion after said oblique shocks are effectively stabilized. 2. The method as set forth in claim 1, wherein removal of said bypass gas is completely terminated after said aerodynamic ducts(s) have reached a selected inlet relative Mach number for said design operating point, wherein normal operation of said compressor occurs without removal of bypass gas. 3. The method as set forth in claim 1, wherein the quantity of said bypass gas required at a selected aerodynamic duct inlet relative Mach number at a design operating point increases at increased inlet relative Mach number. 4. The method as set forth in claim 1, wherein said inlet relative Mach number of said aerodynamic duct is in excess of 1.8. 5. The method as set forth in claim 1, wherein said inlet relative Mach number of said aerodynamic duct is at least 2. 6. The method as set forth in claim 1, wherein said inlet relative Mach number of said aerodynamic duct is at least 2.5. 7. The method as set forth in claim 1, wherein said inlet relative Mach number is in excess of about 2.5. 8. The method as set forth in claim 1, wherein said inlet relative Mach number of said aerodynamic duct is between about 2 and about 2.5, inclusive of said bounding parameters. 9. The method as set forth in claim 1, wherein said inlet relative Mach number of said aerodynamic duct is between about 2.5 and about 2.8, inclusive of said bounding parameters. 10. The method as set forth in claim 1, wherein said inlet relative Mach number is between about 2 and about 2.5, inclusive of said bounding parameters. 11. The method as set forth in claim 4, wherein at the design operating point, the Mach number before said normal shock is in a range of from about 1.2 to about 1.5. 12. The method as set forth in claim 1, wherein said compressor comprises a plurality of aerodynamic ducts mounted on a rotor, and wherein said method comprises removal of bypass gas from said converging inlet portion of each of said aerodynamic ducts. 13. The method as set forth in claim 12, wherein removal of bypass gas further comprises discharging gas from said converging inlet portion through exit conduits located in said converging inlet portion. 14. The method as set forth in claim 12, wherein the number of aerodynamic ducts provided is selected from the group consisting of 3, 5, 7 and 9. 15. The method as set forth in claim 4, wherein said design operating envelope comprises a gas compression ratio of at least 3. 16. The method as set forth in claim 15, wherein said design operating envelope comprises a gas compression ratio of at least 5. 17. The method as set forth in claim 15, wherein said design operating envelope comprises a gas compression ratio of from about 3.75 to about 12, inclusive of said parameters. 18. The method as set forth in claim 15, wherein said design operating envelope comprises a gas compression ratio of from about 12 to about 30, inclusive of said parameters. 19. The method as set forth in claim 15, wherein said design operating envelope comprises a gas compression ratio of in excess of 30. 20. A method of starting a compressor for compressing a selected gas, said compressor comprising a casing, said casing further comprising a low pressure gas inlet for admitting a main flow of a selected gas to be compressed, and a high pressure gas exit for discharging a compressed flow of said selected compressed gas,a rotor journaled in said casing, said rotor comprising one or more aerodynamic ducts having a converging inlet portion and a diverging outlet portion, said aerodynamic ducts comprising one or more structures that at supersonic inflow conditions generate a plurality of oblique shock waves in a gas within said converging inlet portion and a normal shock wave in a gas as said gas enters or passes through said diverging outlet portion, said aerodynamic ducts having an inlet relative Mach number for operation associated with a design operating point selected within a design operating envelope for a selected gas composition, gas quantity, and gas compression ratio,a bypass passageway adapted to receive bypass gas from said aerodynamic ducts, said bypass gas passageway further comprising one or more bypass gas collectors, said one or more bypass gas collectors each co-located with one of said aerodynamic ducts and shaped and sized to facilitate removal of a bypass portion of gas directly from said aerodynamic ducts;said method comprising:raising the rotating speed of said rotor to compress said selected gas at supersonic inlet conditions;removing a selected quantity of bypass gas from said converging inlet portion of said aerodynamic duct through said bypass gas collectors;stabilizing said oblique shock wave at a selected inlet relative Mach number and compression ratio; andeffectively ending removal of said bypass gas. 21. The method as set forth in claim 20, wherein said rotor comprises a plurality of leading edges, and wherein each one of said plurality of said leading edges corresponds to, and lies upstream from, one of said one or one or more aerodynamic ducts. 22. The method as set forth in claim 20, wherein each one of said converging inlet portions comprise exit conduits therein, and wherein removal of bypass gas comprises exit of said bypass gas through said exit conduits. 23. The method as set forth in claim 22, wherein bypass gas removed through said exit conduits comprises a quantity of (a) from about 11% by mass to about 19% by mass of the inlet gas captured by said converging inlet portion for operation at an inlet relative Mach number of about 1.8, to (b) from about 36% by mass to about 61% by mass of the inlet gas captured by said converging inlet portion for operation at an inlet relative Mach number of about 2.8. 24. The method as set forth in claim 20 or in claim 22, wherein the quantity of said bypass gas removed is between an upper limit described by the equation (mbld/mcap)=0.0329M4−0.3835M3+1.5389M2−2.150M+0.9632 and a lower limit described by the equation (mbld/mcap)=0.0197M4−0.230M3+0.9233M2−1.29M+0.5779 wherein mbld=mass of bypass gas removed from said aerodynamic ducts,mcap=mass of gas captured by said aerodynamic ducts,M=the inlet relative Mach number for the aerodynamic ducts. 25. The method as set forth in claim 24, wherein removal of bypass gas comprises discharging gas from said converging inlet portion through exit conduits in a bounding portion of said converging inlet portion. 26. The method as set forth in claim 20, wherein the number of aerodynamic ducts provided is selected from the group consisting of 3, 5, 7 and 9. 27. The method as set forth in any one of claim 25, wherein at the design operating point, the Mach number before said normal shock is in a range of from about 1.2 to about 1.5. 28. The method as set forth in claim 27, wherein said design operating envelope comprises a gas compression ratio of at least 3. 29. The method as set forth in claim 27, wherein said design operating envelope comprises a gas compression ratio of at least 5. 30. The method as set forth in claim 27, wherein said design operating envelope comprises a gas compression ratio of from about 3.75 to about 12, inclusive of said parameters. 31. The method as set forth in claim 27, wherein said design operating envelope comprises a gas compression ratio of from about 12 to about 30, inclusive of said parameters. 32. The method as set forth in claim 27, wherein said design operating envelope comprises a gas compression ratio of in excess of 30. 33. The method as set forth in claim 20, wherein said selected gas comprises a hydrocarbon gas. 34. The method as set forth in claim 33, wherein said selected gas comprises one or more gases selected from the group consisting of ethane, propane, butane, pentane, and hexane. 35. The compressor as set forth in claim 20, wherein said selected gas comprises carbon dioxide. 36. A supersonic gas compressor, comprising: a casing, said casing further comprising a low pressure gas inlet for admitting a main flow of a selected gas to be compressed, and a high pressure gas exit for discharging a compressed flow of said selected compressed gas,a rotor journaled in said casing, said rotor comprising one or more aerodynamic ducts having a converging inlet portion and a diverging outlet portion, said aerodynamic ducts comprising one or more structures that at supersonic inflow conditions generate a plurality of oblique shock waves in a gas within said converging inlet portion and a normal shock wave in a gas as said gas enters or passes through said diverging outlet portion, said aerodynamic ducts having an inlet relative Mach number for operation associated with a design operating point selected within a design operating envelope for a selected gas composition, gas quantity, and gas compression ratio,a bypass gas passageway, said bypass gas passageway having an open position, for use during bypass gas passage during starting of said gas compressor, and a closed position where gas bypass passage is effectively eliminated, for use after stabilizing said oblique shocks;said bypass gas passageway adapted to receive bypass gas from said aerodynamic ducts, said bypass gas passageway further comprising one or more bypass gas collectors, and a plurality of exit conduits, said one or more bypass gas collectors each co-located with one of said aerodynamic ducts and mounted for rotary movement therewith, said bypass gas collectors shaped and sized to facilitate removal of a bypass portion of gas from said aerodynamic ducts via exit conduits defined by sidewalls between an aerodynamic duct bounding portion of said converging inlet portion and said bypass gas collectors. 37. The compressor as set forth in claim 36, wherein said bypass gas passageway is sized for increased capacity for removal of a selected quantity of bypass gas as said inlet relative Mach number increases, wherein the selected quantity of said bypass gas removed is between an upper limit described by the equation (mbld/mcap)=0.0329M4−0.3835M3+1.5389M2−2.150M+0.9632 and a lower limit described by the equation (mbld/mcap)=0.0197M4−0.230M3+0.9233M2−1.29M+0.5779 wherein mbld=mass of bypass gas removed from said aerodynamic duct(s),mcap=mass of gas captured by said aerodynamic duct(s),M=the inlet relative Mach number for the aerodynamic duct(s). 38. The compressor as set forth in claim 36, wherein said inlet relative Mach number of said aerodynamic duct is in excess of 1.8. 39. The compressor as set forth in claim 36, wherein said inlet relative Mach number of said aerodynamic duct is at least 2. 40. The compressor as set forth in claim 36, wherein said inlet relative Mach number of said aerodynamic duct is at least 2.5. 41. The compressor as set forth in claim 36, wherein said inlet relative Mach number is in excess of about 2.5. 42. The compressor as set forth in claim 36, wherein said inlet relative Mach number of said aerodynamic duct is between about 2 and about 2.5, inclusive of said bounding parameters. 43. The compressor as set forth in claim 36, wherein said inlet relative Mach number of said aerodynamic duct is between about 2.5 and about 2.8, inclusive of said bounding parameters. 44. The compressor as set forth in claim 36, wherein said inlet relative Mach number is between about 2 and about 2.5, inclusive of said bounding parameters. 45. The compressor as set forth in claim 38, wherein at the design operating point, the Mach number before said normal shock is in a range of from about 1.2 to about 1.5. 46. The compressor as set forth in claim 36, wherein said compressor comprises a plurality of aerodynamic ducts mounted on said rotor, and wherein bypass gas collectors are co-located with each of said aerodynamic ducts. 47. The compressor as set forth in claim 46, wherein three aerodynamic ducts are provided. 48. The compressor as set forth in claim 36 or in claim 38, wherein said design operating envelope comprises a gas compression ratio of at least 3. 49. The compressor as set forth in claim 48, wherein said design operating envelope comprises a gas compression ratio of at least 5. 50. The compressor as set forth in claim 48, wherein said design operating envelope comprises a gas compression ratio of from about 3.75 to about 12, inclusive of said parameters. 51. The compressor as set forth in claim 48, wherein said design operating envelope comprises a gas compression ratio of from about 12 to about 30, inclusive of said parameters. 52. The compressor as set forth in claim 48, wherein said design operating envelope comprises a gas compression ratio in excess of 30. 53. The compressor as set forth in claim 36, wherein said aerodynamic ducts comprise a converging inlet having a compression ramp that compresses incoming gas at least partially radially outward. 54. The compressor as set forth in claim 53, wherein said bypass gas collectors are provided at a location outward from said compression ramp. 55. The compressor as set forth in claim 54, wherein said bypass gas collectors are provided at a location inward from said compression ramp. 56. The compressor as set forth in claim 53, further comprising a second compression ramp, said second compression ramp oriented to compress incoming gas at least partially radially inward. 57. The compressor as set forth in claim 56, wherein said bypass gas collectors are provided at a location (a) outward from said compression ramp, and (b) inward from said compression ramp. 58. The compressor as set forth in claim 36, wherein said aerodynamic ducts comprise a converging inlet having a compression ramp that compresses incoming gas at least partially radially inward. 59. The compressor as set forth in claim 36, wherein said bypass gas collectors comprise chambers at least partially defined by a floor comprising an exterior portion of a bounding portion of said aerodynamic duct. 60. The compressor as set forth in claim 59, wherein said bypass gas collectors comprise chambers at least partially defined by axially oriented and radially extending opposing ribs. 61. The compressor as set forth in claim 59, wherein said bypass gas collectors comprise chambers at least partially defined by opposing collector boards, said opposing collector boards provided in pairs, wherein an upstream collector board substantially prevents flow of bypass gas thereby, and wherein a downstream collector board defines at least a portion of a bypass gas outlet from said bypass gas collector. 62. The compressor as set forth in claim 36 or in claim 59, further comprising a hoop shroud, said hoop shroud extending circumferentially about said rotor to provide a bypass gas flow restrictive roof above said bypass gas collector. 63. The compressor as set forth in claim 62, wherein said hoop shroud comprises an annular hoop. 64. The compressor as set forth in claim 63, wherein said aerodynamic ducts are bounded between strakes. 65. The compressor as set forth in claim 64, wherein said strakes are helical. 66. The compressor as set forth in claim 65, wherein said helical strakes laterally bound said aerodynamic ducts. 67. The compressor as set forth in claim 62, wherein said hoop shroud comprises an outer surface, said outer surface further providing a grooved portion providing a labyrinth seal with respect to said casing. 68. The compressor as set forth in claim 36, further comprising a valve associated with said bypass gas passageways, said valve configured to open and close said bypass gas passageways. 69. The compressor as set forth in claim 36, wherein said bypass gas passageway returns said bypass gas to said low pressure gas inlet. 70. The compressor as set forth in claim 36, further comprising an interconnecting a conduit between said diverging outlet portion of said aerodynamic duct and said high pressure outlet of said casing. 71. The compressor as set forth in claim 70, further comprising outlet diffusers, said outlet diffusers adapted to slow high speed gas escaping said diverging outlet portion to convert kinetic energy to pressure in said high pressure outlet of said casing.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.