[특허]Method and apparatus for starting supersonic compressors

Ramgen Power Systems, LLC

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특허 상세정보

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Method and apparatus for starting supersonic compressors

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-001/34
미국특허분류(USC)	415/058.4; 415/090; 415/181; 415/145
출원번호	US-0441833 (2012-04-06)
등록번호	US-8500391 (2013-08-06)
발명자 / 주소	Lawlor, Shawn P.
출원인 / 주소	Ramgen Power Systems, LLC
대리인 / 주소	Goodloe, Jr., R. Reams
인용정보	피인용 횟수 : 2 인용 특허 : 21

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A supersonic gas compressor with bleed gas collectors, and a method of starting the compressor. The compressor includes aerodynamic duct(s) situated for rotary movement in a casing. The aerodynamic duct(s) generate a plurality of oblique shock waves for efficiently compressing a gas at supersonic conditions. A convergent inlet is provided adjacent to a bleed gas collector, and during startup of the compressor, bypass gas is removed from the convergent inlet via the bleed gas collector, to enable supersonic shock stabilization. Once the oblique shocks are...

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1. A method for starting a supersonic gas compressor, comprising: (a) providing a compressor, said compressor comprising a casing, comprising a low pressure gas inlet for admitting a main flow of a gas to be compressed, and a high pressure gas exit for discharging a compressed flow of said gas,a rotor, comprising one or more aerodynamic ducts within said casing, said one or more aerodynamic ducts having converging inlet portions and diverging outlet portions, said one or more aerodynamic ducts comprising one or more structures that at supersonic inflow conditions generate a plurality of oblique shock waves (S1 to SX) in said gas within said converging inlet portion and a normal shock wave (SN) in said 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, each co-located with one of said aerodynamic ducts and shaped and sized to facilitate removal of a selected quantity of bypass gas directly from said one or more aerodynamic ducts;(b) initiating rotation of said rotor and raising the rotating speed of said rotor to compress said gas at supersonic inlet conditions;(c) removing said selected quantity of bypass gas from said converging inlet portions of said one or more aerodynamic ducts through said bypass gas collectors and returning said bypass gas to said low pressure gas inlet;(d) stabilizing said oblique shock waves at a selected inlet relative Mach number and compression ratio; and(e) ending removal of said bypass gas. 2. The method as claimed in claim 1, wherein said rotor comprises a plurality of leading edges, and wherein each of said plurality of said leading edges corresponds to, and lies upstream from, one of said one or more aerodynamic ducts. 3. The method as claimed in claim 1, wherein each one of said converging inlet portions comprise exit conduits therein, and wherein removal of bypass gas comprises the exit of said bypass gas through said exit conduits. 4. The method as claimed in claim 3, wherein said bypass gas removed through said exit conduits comprises a quantity ranging (a) from about 11% by mass to about 19% by mass of an 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. 5. The method as set forth in claim 4, wherein at the design operating point, a Mach number upstream of said normal shock wave is in a range of from about 1.2 to about 1.5. 6. The method as claimed in claim 1 or in claim 3, wherein the quantity of said bypass gas removed is between an upper limit described by the equation (mbid/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 whereinmbld=mass of bypass gas removed from said one or more aerodynamic ducts,mcap=mass of gas captured by said one or more aerodynamic ducts, andM=the inlet relative Mach number for said one or more aerodynamic ducts. 7. The method as claimed in claim 6, wherein removal of said bypass gas comprises discharge of said bypass gas from said converging inlet portion through exit conduits in a bounding portion of said converging inlet portion. 8. The method as set forth in claim 6, wherein said gas has a molecular weight of at least that of nitrogen. 9. The method as set forth in claim 6, wherein said gas comprises carbon dioxide. 10. The method as set forth in claim 6, wherein said gas comprises a hydrocarbon gas. 11. The method as set forth in claim 10, wherein said gas comprises propane. 12. The method as set forth in claim 10, wherein said gas comprises butane. 13. The method as set forth in claim 10, wherein said gas comprises ethane. 14. The method as set forth in claim 1, wherein said inlet relative Mach number of said one or more aerodynamic ducts is in excess of 1.8. 15. The method as set forth in claim 1, wherein said inlet relative Mach number of said one or more aerodynamic ducts is at least 2. 16. The method as set forth in claim 1, wherein said inlet relative Mach number of said one or more aerodynamic ducts is between about 2 and about 2.5. 17. The method as set forth in claim 1, wherein said inlet relative Mach number of said one or more aerodynamic ducts is at least 2.5. 18. The method as set forth in claim 1, wherein said inlet relative Mach number of said one or more aerodynamic ducts is between about 2.5 and about 2.8. 19. The method as set forth in claim 1, wherein said design operating envelope comprises a gas compression ratio of at least 3. 20. The method as set forth in claim 1, wherein said design operating envelope comprises a gas compression ratio of at least 5. 21. The method as set forth in claim 1, wherein said design operating envelope comprises a gas compression ratio of from about 3.75 to about 12. 22. The method as set forth in claim 1, wherein said design operating envelope comprises a gas compression ratio of from about 12 to about 30. 23. The method as set forth in claim 1, wherein said design operating envelope comprises a gas compression ratio of in excess of 30. 24. A supersonic gas compressor, comprising: a casing, said casing further comprising a low pressure gas inlet for admitting a main flow of a gas to be compressed, and a high pressure gas exit for discharging a compressed flow of said gas to be compressed,one or more aerodynamic ducts mounted for rotary movement within said casing, said one or more aerodynamic ducts each having a converging inlet portion and a diverging outlet portion, said one or more aerodynamic ducts each comprising one or more structures that at supersonic inflow conditions generate a plurality of oblique shock waves (S1 to SX) in a gas within said converging inlet portion and a normal shock wave (SN) 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, for use after stabilizing said oblique shock waves and where gas bypass passage is eliminated;said bypass gas passageway adapted to receive bypass gas from said one or more aerodynamic ducts and return said bypass gas to said low pressure gas inlet, 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 one or more aerodynamic ducts and mounted for rotary movement therewith, said one or more bypass gas collectors shaped and sized to facilitate removal of a bypass portion of gas from said one or more aerodynamic ducts via exit conduits defined by sidewalls located between an aerodynamic duct bounding portion of said converging inlet portion and said one or more bypass gas collectors. 25. The compressor as set forth in claim 24, 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 whereinmbld=mass of bypass gas removed from said one or more aerodynamic ducts,mcap=mass of gas captured by said one or more aerodynamic ducts, andM=the inlet relative Mach number for said one or more aerodynamic ducts. 26. The compressor as set forth in claim 24, wherein said one or more bypass gas collectors each comprise chambers at least partially defined by a floor comprising an exterior portion of a bounding portion of said one or more aerodynamic ducts. 27. The compressor set forth in claim 24, wherein said one or more bypass gas collectors each comprise chambers at least partially defined by axially oriented and radially extending opposing ribs. 28. The compressor as set forth in claim 24, wherein said one or more bypass gas collectors each 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 one or more bypass gas collectors. 29. The compressor as set forth in claim 24, further comprising an interconnecting conduit between said diverging outlet portion of said one or more aerodynamic ducts and said high pressure gas exit of said casing, and 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 gas exit of said casing.

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Method and apparatus for starting supersonic compressors

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Method and apparatus for starting supersonic compressors

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