IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0913369
(2006-05-02)
|
등록번호 |
US-8262343
(2012-09-11)
|
국제출원번호 |
PCT/US2006/017119
(2006-05-02)
|
§371/§102 date |
20080527
(20080527)
|
국제공개번호 |
WO2006/119409
(2006-11-09)
|
발명자
/ 주소 |
|
출원인 / 주소 |
- Vast Power Portfolio, LLC
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
60 인용 특허 :
5 |
초록
▼
This wet compression invention with a vaporizable fluid mist demonstrates major performance improvements over the relevant art in achieving a high degree of saturation, providing sensible cooling, strongly reducing the temperature increase due to compression work, reducing excess diluent air flow fo
This wet compression invention with a vaporizable fluid mist demonstrates major performance improvements over the relevant art in achieving a high degree of saturation, providing sensible cooling, strongly reducing the temperature increase due to compression work, reducing excess diluent air flow for downstream combustion, reducing compression noise, and increasing the achievable compressor pressure ratio. These improvements are obtained by one or more of: high mist or overspray from a) progressive axial injection of vaporizable fluid along the streamwise compression flow path, and b) transverse vaporizable fluid delivery from stators, rotors, perforated tubes, and/or duct walls, matching the gaseous fluid flow distribution across the compressor stream; c) reducing the compressor cross-sectional flow area of downstream compressor stages relative to up-stream stages, and d) increasing the rate of downstream vaporizable fluid injection relative to the rate of upstream injection, as a function of each compressor stage pressure ratio.
대표청구항
▼
1. A method of cooling a gaseous fluid being compressed in at least one compressor portion distributed along a curvilinear stream wise flow; the method comprising: delivering a vaporizable cooling fluid to the compressor portion along a curvilinear transverse line distinct from the curvilinear strea
1. A method of cooling a gaseous fluid being compressed in at least one compressor portion distributed along a curvilinear stream wise flow; the method comprising: delivering a vaporizable cooling fluid to the compressor portion along a curvilinear transverse line distinct from the curvilinear stream wise flow path direction, and bounded by a first wall and a second wall,wherein said transverse line includes a region closer to the center of the stream wise flow and a region closer to one of the first or second walls;evaporating a fraction of the delivered cooling fluid in both said regions characterized in that the rate of cooling induced in the region closer to the center of stream wise flow is greater than the rate of cooling in the region closer to the first or second wall; andfurther characterized in that the cooling reduces the rate of heating due to compression. 2. The method according to claim 1, wherein the functional dependence of the cooling rate along the curvilinear transverse line is non-linear. 3. The method according to claim 1, wherein the cooling rate reaches a transverse maximum within about 25% to 75% of the distance between the first and second wall. 4. The method according to claim 3, wherein the cooling rate reaches a maximum closer to the centripetally inward wall than the mass weighted distribution of gaseous fluid stream wise flow within the compression stage. 5. The method according to claim 1, wherein the mass weighted transverse distribution of delivered cooling fluid delivered within a compressor stage is proportional to the desired cooling fluid delivery transverse distribution within that stage, less a transverse distribution of vaporizable cooling fluid entrained with the gaseous fluid entering that stage. 6. The method according to claim 1, wherein the mass weighted transverse distribution of injected cooling fluid delivered within a compressor stage is proportional to the desired cooling fluid delivery transverse distribution within that stage, less an evaporation weighted transverse distribution of cooling fluid entrained with the gaseous fluid entering that stage. 7. The method according to claim 1, wherein the rate of injected cooling fluid across at least one compression stage is between 60% and 250% of the flow required to saturate the gaseous fluid within that stage. 8. The method according to claim 1, wherein the average orifice size for the injection of cooling fluid is less than 10 microns. 9. The method according to claim 8, wherein the average orifice size for the injection of cooling fluid is less than 3 microns. 10. The method according to claim 1, wherein the average Sauter Mean Diameter droplet size of injected cooling fluid is less than 5 microns. 11. The method according to claim 1, wherein the noise generated during operation is reduced by at least 5 dB relative to equivalent dry compression prior art systems. 12. The method according to claim 1, wherein the ratio of the relative decrease in normalized Wet to Dry temperature ratio (“1−W/D”) to natural log of pressure ratio (LN BETA) is at least 0.01. 13. The method according to claim 1, wherein at least 95% by mass of the injected coolant fluid drops are less than 20 microns Sauter Mean Diameter. 14. The method according to claim 1, wherein the mass ratio of total coolant fluid to gaseous fluid at the compressor system outlet is greater than 60% of the ratio of coolant fluid that would have been required to saturate that gaseous fluid after adiabatic compression to the same pressure ratio. 15. The method according to claim 1, further comprising configuring one or more of drop size, temperature, and/or drop velocity relative to a compressor component surface, and/or hardening that component surface, wherein controlling the kinetic impact induced stress on a turbomachine component surface to be less than a prescribed surface design stress for at least 99% of droplet impacts. 16. The method according to claim 1, further comprising one of a combustion or chemical reaction system downstream of the compressed fluid outlet in fluid communication with the exiting compressed fluid, and comprising delivering cooling liquid as diluent into the downstream combustion and/or reaction system. 17. The method according to claim 16, further comprising controlling the degree of dilution and/or cooling of the downstream combustion or reaction by controlling the cooling liquid delivered into at least one of the gaseous fluid upstream and downstream of the compressor outlet. 18. The method according to claim 17, further comprising configuring the peak to mean ratio and peak location of the transverse cooling liquid delivery distribution at a compressor stage to compensate for the transverse mass flow distribution of the gaseous fluid caused by upstream centripetal acceleration, and the projected downstream transverse motion of the cooling liquid delivered. 19. The method according to claim 1, further comprising recovering heat from the flow downstream of the compressor and using it to heat the cooling liquid. 20. The method of claim 1, further comprising controlling the attack angle of at least one stator airfoil to adjust the axial distribution of compression ratio beta for wet compression.
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