IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0710764
(2010-02-23)
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등록번호 |
US-8640464
(2014-02-04)
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발명자
/ 주소 |
- Condevaux, Jamey J.
- Simpkins, Lisa M.
- Sordyl, John
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출원인 / 주소 |
- Williams International Co., L.L.C.
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
0 인용 특허 :
44 |
초록
▼
Fuel and air are injected in a first poloidal flow in a first poloidal direction within a first annular zone of an annular combustor. A first combustion gas from the at least partial combustion of the fuel and air is discharged into an annular transition zone of the annular combustor and transformed
Fuel and air are injected in a first poloidal flow in a first poloidal direction within a first annular zone of an annular combustor. A first combustion gas from the at least partial combustion of the fuel and air is discharged into an annular transition zone of the annular combustor and transformed to a second combustion gas therein within an at least partial second poloidal flow followed by an at least partial third poloidal flow in the annular transition zone, wherein the direction of the second poloidal flow is opposite to that of the first and third poloidal flows. The second combustion gas is discharged into a second annular zone of the annular combustor, and then transformed to a third combustion gas therein before being discharged therefrom, responsive to which a back pressure is generated in the annular combustor.
대표청구항
▼
1. A method of operating a combustion system, comprising: a. injecting fuel into a first annular zone of an annular combustor;b. injecting a first portion of air into said first annular zone, wherein at least one of the operations of injecting said fuel or injecting said first portion of air provide
1. A method of operating a combustion system, comprising: a. injecting fuel into a first annular zone of an annular combustor;b. injecting a first portion of air into said first annular zone, wherein at least one of the operations of injecting said fuel or injecting said first portion of air provides for inducing a first poloidal flow in a first poloidal direction within said first annular zone of said annular combustor;c. at least partially combusting said fuel with first portion of air in said first poloidal flow within said first annular zone of said annular combustor so as to generate a first combustion gas;d. discharging said first combustion gas from said first annular zone of said annular combustor into an annular transition zone of said annular combustor;e. transforming said first combustion gas to a second combustion gas within said annular transition zone of said annular combustor;f. inducing at least a partial second poloidal flow of said second combustion gas within said annular transition zone of said annular combustor, wherein said second poloidal flow is in a second poloidal direction that is opposite to said first poloidal direction;g. inducing at least a partial third poloidal flow of said second combustion gas within said annular transition zone of said annular combustor, wherein said third poloidal flow is in said first poloidal direction, wherein the operation of inducing said at least a partial third poloidal flow comprises deflecting said second combustion gas within said annular transition zone with a radially-inwardly-extending annular step aft of said first annular zone and at a location that is radially outward of said first annular zone;h. discharging said second combustion gas from said annular transition zone of said annular combustor into a second annular zone of said annular combustor;i. transforming said second combustion gas to a third combustion gas within said second annular zone of said annular combustor;j. discharging said third combustion gas from said second annular zone of said annular combustor; andk. generating a back pressure within said annular combustor responsive to the operation of discharging said third combustion gas therefrom. 2. A method of operating a combustion system as recited in claim 1, wherein the operation of injecting said first portion of air into said first annular zone comprises injecting at least a portion of said first portion of air at least partially radially outwards and at least partially forwards from a radially inward boundary of said first annular zone from a location that is aftward of a forward boundary of said first annular zone. 3. A method of operating a combustion system as recited in claim 1, wherein the operation of injecting said first portion of air into said first annular zone comprises injecting at least a portion of said first portion of air at least partially radially outwards from a forward boundary of said first annular zone from a location that is radially inward of a center of said first annular zone. 4. A method of operating a combustion system as recited in claim 1, wherein the operation of injecting said first portion of air into said first annular zone comprises injecting at least a portion of said first portion of air at least partially aftwards from a forward boundary of said first annular zone from a location that is radially outward of a center of said first annular zone. 5. A method of operating a combustion system as recited in claim 1, wherein the operation of injecting said first portion of air into said first annular zone comprises injecting at least a portion of said first portion of air at least partially radially inwards from a radially outward boundary of said first annular zone from a location that is aftward of a center of said first annular zone. 6. A method of operating a combustion system as recited in claim 1, wherein said first poloidal direction is such that at least a portion of a mean flow of said first poloidal flow aft of a center of said first annular zone is in a radially inward direction. 7. A method of operating a combustion system as recited in claim 1, wherein the operations of injecting said fuel and injecting said first portion of air into said first annular zone of said annular combustor are adapted to provide for accommodating a mass ratio of said fuel to said first portion of air at or in excess of a lower flammability limit of said fuel and said air within said first annular zone. 8. A method of operating a combustion system as recited in claim 1, further comprising injecting a first portion of effusion cooling air from at least one surface of said annular combustor bounding or surrounding said first annular zone. 9. A method of operating a combustion system as recited in claim 1, wherein the operation of injecting said first portion of air into said first annular zone comprises at least two of: injecting at least a portion of said first portion of air at least partially radially outwards and at least partially forwards from a radially inward boundary of said first annular zone from a location that is aftward of a forward boundary of said first annular zone, injecting at least a portion of said first portion of air at least partially radially outwards from said forward boundary of said first annular zone from a location that is radially inward of a center of said first annular zone, injecting at least a portion of said first portion of air at least partially aftwards from a forward boundary of said first annular zone from a location that is radially outward of said center of said first annular zone, and injecting at least a portion of said first portion of air at least partially radially inwards from a radially outward boundary of said first annular zone from a location that is aftward of said center of said first annular zone, and at least two of the operations of injecting at least a portion of said first portion of air are azimuthally offset or interleaved with respect to one another with respect to said first annular zone of said annular combustor. 10. A method of operating a combustion system as recited in claim 1, wherein the operation of transforming said first combustion gas to said second combustion gas within said annular transition zone of said annular combustor comprises further combusting said first combustion gas in said annular transition zone of said annular combustor. 11. A method of operating a combustion system as recited in claim 10, wherein the operation of further combusting said first combustion gas in said annular transition zone of said annular combustor comprises injecting additional air into said annular transition zone and further combusting said first combustion gas therewith in said annular transition zone. 12. A method of operating a combustion system as recited in claim 11, wherein an amount of said additional air injected into said annular transition zone is adapted so that said second combustion gas provides for stoichiometric or leaner combustion of said fuel. 13. A method of operating a combustion system as recited in claim 1, wherein said third combustion gas from said second annular zone of said annular combustor is richer than stoichiometric. 14. A method of operating a combustion system as recited in claim 1, wherein the operation of inducing said at least a partial third poloidal flow comprises injecting a third portion of air at least partially aftwards from a forward boundary of said annular transition zone from a location that is radially inward of a radially outermost boundary of said annular transition zone. 15. A method of operating a combustion system as recited in claim 1, further comprising injecting a second portion of effusion cooling air from at least one surface of said annular combustor bounding or surrounding said annular transition zone. 16. A method of operating a combustion system as recited in claim 1, wherein the operation of transforming said second combustion gas to said third combustion gas within said second annular zone of said annular combustor comprises injecting additional air into said second annular transition zone and diluting said second combustion gas therewith. 17. A method of operating a combustion system as recited in claim 1, further comprising injecting a third portion of effusion cooling air from at least one surface of said annular combustor bounding or surrounding said second annular zone. 18. A method of operating a combustion system as recited in claim 1, further comprising diffusing an incoming stream of air prior to extracting said first portion of air therefrom. 19. A method of operating a combustion system as recited in claim 1, wherein the operation of injecting said fuel comprises injecting at least a portion of said fuel from a location that is fixed relative to a surface of said annular combustor. 20. A method of operating a combustion system as recited in claim 1, wherein the operation of injecting said fuel comprises injecting at least a portion of said fuel within said annular combustor from a rotary injector. 21. A method of operating a combustion system as recited in claim 1, wherein the operation of generating said back pressure comprises discharging said third combustion gas through a nozzle. 22. A method of operating a combustion system as recited in claim 1, wherein the operation of generating said back pressure comprises discharging said third combustion gas through a heat exchanger. 23. A method of operating a combustion system, comprising: a. injecting fuel into a first annular zone of an annular combustor;b. injecting a first portion of air into said first annular zone, wherein at least one of the operations of injecting said fuel or injecting said first portion of air provides for inducing a first poloidal flow in a poloidal direction within said first annular zone of said annular combustor, at least one of the operations of injecting said fuel or injecting said first portion of air into said first annular zone provides for inducing a toroidal helical flow of said first combustion gas within said first annular zone of said annular combustor, and prior to the operation of injecting said first portion of air into said first annular zone, further comprising flowing said first portion of air through at least one radial strut or vane that is radially canted so as to introduce a circumferential component of swirl flow to said first portion of air so as to cause a circumferential component of flow of said first portion of air when injected into said first annular zone;c. at least partially combusting said fuel with said first portion of air in said first poloidal flow within said first annular zone of said annular combustor so as to generate a first combustion gas;d. discharging said first combustion gas from said first annular zone of said annular combustor into an annular transition zone of said annular combustor;e. transforming said first combustion gas to a second combustion gas within said annular transition zone of said annular combustor;f. inducing at least a partial second poloidal flow of said second combustion gas within said annular transition zone of said annular combustor, wherein said second poloidal flow is in a second poloidal direction that is opposite to said first poloidal direction;g. inducing at least a partial third poloidal flow of said second combustion gas within said annular transition flow of said annular combustor, wherein said third poloidal flow is in said first poloidal direction;h. discharging said second combustion gas from said annular transition zone of said annular combustor into a second annular zone of said annular combustor;i. transforming said second combustion gas to a third combustion gas within said second annular zone of said annular combustor;j. discharging said third combustion gas from said second annular zone of said annular combustor; andk. generating a back pressure within said annular combustor responsive to the operation of discharging said third combustion gas therefrom. 24. A method of operating a combustion system, comprising: a. injecting fuel into a first annular zone of an annular combustor;b. injecting a first portion of air into said first annular zone, wherein at least one of the operations of injecting said fuel or injecting said first portion of air provides for inducing a first poloidal flow in a first poloidal direction within said first annular zone of said annular combustor;c. at least partially combusting said fuel with said first portion of air in said first poloidal flow within said first annular zone of said annular combustor so as to generate a first combustion gas;d. discharging said first combustion gas from said first annular zone of said annular combustor into an annular transition zone of said annular combustor;e. transforming said first combustion gas to a second combustion gas within said annular transition zone of said annular combustor;f. inducing at least a partial second poloidal flow of said second combustion gas within said annular transition zone of said annular combustor, wherein said second poloidal flow is in a second poloidal direction that is opposite to said first poloidal direction, wherein the operation of inducing said at least a partial second poloidal flow comprises deflecting said first combustion gas discharged from said first annular zone with a radially-outwardly-extending annular step aft of said first annular zone;g. inducing at least a partial third flow of said second combustion gas within said annular transition zone of said annular combustor, wherein said third poloidal flow is in said first poloidal direction;h. discharging said second combustion gas from said annular transition zone of said annular combustor into a second annular zone of said annular combustor;i. transforming said second combustion gas to a third combustion gas within said second annular zone of said annular combustor;j. discharging said third combustion gas from said second annular zone of said annular combustor; andk. generating a back pressure within said annular combustor to the operation of discharging said third combustion gas therefrom. 25. A method of operating a combustion system, comprising: a. injecting fuel into a first annular zone of an annular combustor;b. injecting a first portion of air into said first annular zone, wherein at least one of the operations of injecting said fuel or injecting said first portion of air provides for inducing a first poloidal flow in a first poloidal direction within said first annular zone of said annular combustor;c. at least partially combusting said fuel with said first portion of air in said first poloidal flow within said first annular zone of said annular combustor so as to generate a first combustion gas;d. discharging said first combustion gas from said first annular zone of said annular combustor into an annular transition zone of said annular combustor;e. transforming said first combustion gas to a second combustion gas within said annular transition zone of said annular combustor;f. inducing at least a partial second poloidal flow of said second combustion gas within said annular transition zone of said annular combustor, wherein said second poloidal flow is in a second poloidal direction that is opposite to said first poloidal direction, wherein the operation of inducing said at least a partial second poloidal flow comprises injecting a second portion of air at least partially forwards from an aftward boundary of said annular transition zone from a location that is radially outward of a radially inward boundary of said annular transition zone;g. inducing at least a partial third poloidal flow of said second combustion gas within said annular transition zone of said annular combustor, wherein said third poloidal flow is in said first poloidal direction;h. discharging said second combustion gas from said annular transition zone of said annular combustor into a second annular zone of said annular combustor;i. transforming said second combustion gas to a third combustion gas within said second annular zone of said annular combustor;j. discharging said third combustion gas from said second annular zone of said annular combustor; andk. generating a back pressure within said annular combustor responsive to the operation of discharging said third combustion gas therefrom. 26. A method of operating a combustion system, comprising: a. injecting fuel into a first annular zone of an annular combustor;b. injecting a first portion of air into said first annular zone, wherein at least one of the operations of injecting said fuel or injecting said first portion of air provides for inducing a first poloidal flow in a first poloidal direction within said first annular zone of said annular combustor, at least one of the operations of injecting said fuel or injecting said first portion of air into said first annular zone provides for inducing a toroidal helical flow of said first combustion gas within said first annular zone of said annular combustor, and said first portion of air is injected into said first annular zone through a first plurality of orifices and through a second plurality of orifices that are respectively forward and aft of a location where said fuel is injected into said first annular zone, wherein said first and second pluralities of orifices are circumferentially interleaved with respect to one another so as to cause a circumferential component of flow of said first portion of air when injected into said first annular zone;c. at least partially combusting said fuel with said first portion of air in said first poloidal flow within said first annular zone of said annular combustor so as to generate a first combustion gas;d. discharging said first combustion gas from said first annular zone of said annular combustor into an annular transition zone of said annular combustor;e. transforming said first combustion gas to a second combustion gas within said annular transition zone of said annular combustor;f. inducing at least a partial second poloidal flow of said second combustion gas within said annular transition zone of said annular combustor, wherein said second poloidal flow is in a second poloidal direction that is opposite to said first poloidal direction;g. inducing at least a partial third poloidal flow of said second combustion gas within said annular transition zone of said annular combustor, wherein said third poloidal flow is in said first poloidal direction;h. discharging said second combustion gas from said annular transition zone of said annular combustor into a second annular zone of said annular combustor;i. transforming said second combustion gas to a third combustion gas within said second annular zone of said annular combustor;j. discharging said third combustion gas from said second annular zone of said annular combustor; andk. generating a back pressure within said annular combustor responsive to the operation of discharging said third combustion gas therefrom.
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