Swirler assembly with compressor discharge injection to vane surface
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-001/00
F02G-003/00
F23R-003/14
F23R-003/28
출원번호
US-0303888
(2011-11-23)
등록번호
US-8978384
(2015-03-17)
발명자
/ 주소
Bailey, Donald Mark
Khan, Abdul Rafey
Bobba, Mohan Krishna
출원인 / 주소
General Electric Company
대리인 / 주소
Nixon & Vanderhye P.C.
인용정보
피인용 횟수 :
0인용 특허 :
39
초록▼
A swirler assembly in a gas turbine combustor includes a hub, a shroud, and a plurality of vanes connected between the hub and the shroud. The vanes include a high pressure side on which air and fuel impinge the vanes and a low pressure side. An air circuit is provided in each of the plurality of va
A swirler assembly in a gas turbine combustor includes a hub, a shroud, and a plurality of vanes connected between the hub and the shroud. The vanes include a high pressure side on which air and fuel impinge the vanes and a low pressure side. An air circuit is provided in each of the plurality of vanes receiving discharge air from a compressor. Each of the air circuits includes an air entry passage into the vanes and an air exit passage on the low pressure side of the vanes.
대표청구항▼
1. A swirler assembly in a gas turbine combustor, the swirler assembly comprising: a hub;a shroud;a plurality of vanes connected between the hub and the shroud, the vanes including a high pressure side on which air and fuel impinge the vanes and a low pressure side; andan air circuit in each of the
1. A swirler assembly in a gas turbine combustor, the swirler assembly comprising: a hub;a shroud;a plurality of vanes connected between the hub and the shroud, the vanes including a high pressure side on which air and fuel impinge the vanes and a low pressure side; andan air circuit in each of the plurality of vanes receiving discharge air from a compressor, each of the air circuits including an air entry passage into the vanes and an air exit passage on the low pressure side of the vanes. 2. A swirler assembly according to claim 1, wherein the air entry passage comprises a cap feed passage that directs the compressor discharge air into the hub toward a nozzle tip, and wherein a portion of the compressor discharge air is diverted through the exit passage to the low pressure side of the vanes. 3. A swirler assembly according to claim 2, further comprising a cap feed opening in the shroud. 4. A swirler assembly according to claim 1, further comprising a cap feed passage that directs the compressor discharge air into the hub toward a nozzle tip, wherein the air entry passage is separate from the cap feed passage. 5. A swirler assembly according to claim 1, wherein the air exit passage comprises a plurality of holes through the low pressure side of the vanes. 6. A swirler assembly according to claim 1, wherein the air entry passage receives the air directly from the compressor. 7. A swirler assembly according to claim 1, wherein the air entry passage is accessed via an opening in a side of the vane. 8. A gas turbine comprising: a compressor that progressively compresses a working fluid, the working fluid comprising air;a combustor injecting fuel into the compressed air and igniting the air and fuel to produce combustion gases; anda turbine using the combustion gases to produce work,wherein the combustor includes a swirler assembly that imparts swirl to the air and the fuel, the swirler assembly including a hub, a shroud, a plurality of vanes connected between the hub and the shroud, and an air circuit in each of the plurality of vanes, the vanes including a high pressure side on which the working fluid air and fuel impinge the vanes and a low pressure side, the air circuit in each of the plurality of vanes receiving discharge air from the compressor, wherein each of the air circuits includes an air entry passage into the vanes and an air exit passage on the low pressure side of the vanes. 9. A gas turbine according to claim 8, wherein the air entry passage comprises a cap feed passage that directs the compressor discharge air into the hub toward a nozzle tip, and wherein a portion of the compressor discharge air is diverted through the exit passage to the low pressure side of the vanes. 10. A gas turbine according to claim 9, further comprising a cap feed opening in the shroud. 11. A gas turbine according to claim 8, further comprising a cap feed passage that directs the compressor discharge air into the hub toward a nozzle tip, wherein the air entry passage is separate from the cap feed passage. 12. A gas turbine according to claim 8, wherein the air exit passage comprises a plurality of holes through the low pressure side of the vanes. 13. A gas turbine according to claim 8, wherein the air entry passage receives the air directly from the compressor. 14. A gas turbine according to claim 8, wherein the air entry passage is accessed via an opening in a side of the vane. 15. A method of mixing fuel and air in a swirler assembly, the swirler assembly including a hub, a shroud, and a plurality of vanes connected between the hub and the shroud, the vanes including a high pressure side on which air and fuel impinge the vanes and a low pressure side, the method comprising: providing an air circuit in each of the plurality of vanes, each of the air circuits including an air entry passage into the vanes and an air exit passage on the low pressure side of the vanes; anddirecting airflow from a compressor to the air entry passage into the vanes and through the air exit passage on the low pressure side of the vanes. 16. A method according to claim 15, wherein the air entry passage comprises a cap feed passage that directs the compressor discharge air into the hub toward a nozzle tip, and wherein the directing step is practiced by diverting a portion of the compressor discharge air through the exit passage to the low pressure side of the vanes. 17. A method according to claim 15, wherein the providing step is practiced by providing the air exit passage with a plurality of holes through the low pressure side of the vanes. 18. A method according to claim 15, wherein directing step is practiced by directing the airflow to the air entry passage directly from the compressor. 19. A method according to claim 15, wherein the providing step is practiced providing an opening in a side of the vane.
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