Air cooled fuel injector for a turbine engine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/18
F23R-003/28
F23R-003/14
F02C-007/22
출원번호
US-0023606
(2014-10-06)
등록번호
US-10184663
(2019-01-22)
국제출원번호
PCT/US2014/059314
(2014-10-06)
국제공개번호
WO2015/054136
(2015-04-16)
발명자
/ 주소
Frish, John D.
출원인 / 주소
United Technologies Corporation
대리인 / 주소
O'Shea Getz P.C.
인용정보
피인용 횟수 :
0인용 특허 :
11
초록▼
An assembly is provided for a turbine engine. The assembly includes a cooling tube through which a flow path extends. The assembly also includes a fuel injector, which includes a stem connected to a tip. The stem is arranged within the cooling tube. The tip extends from the cooling tube to a nozzle.
An assembly is provided for a turbine engine. The assembly includes a cooling tube through which a flow path extends. The assembly also includes a fuel injector, which includes a stem connected to a tip. The stem is arranged within the cooling tube. The tip extends from the cooling tube to a nozzle. The cooling tube is adapted to direct cooling air through the flow path.
대표청구항▼
1. An assembly for a turbine engine, the assembly comprising: a cooling tube through which a flow path extends; anda fuel injector including a stem connected to a tip, the stem arranged within the cooling tube, and the tip extending through a sidewall of the cooling tube to a nozzle located outside
1. An assembly for a turbine engine, the assembly comprising: a cooling tube through which a flow path extends; anda fuel injector including a stem connected to a tip, the stem arranged within the cooling tube, and the tip extending through a sidewall of the cooling tube to a nozzle located outside of the cooling tube;wherein the cooling tube is adapted to direct cooling air through the flow path;wherein the cooling tube extends radially relative to a centerline of the turbine engine between an inner end and an outer end; andwherein the cooling tube includes a cooling air inlet and a cooling air outlet, the cooling air inlet is located at the outer end, and the cooling air outlet is located at the inner end. 2. The assembly of claim 1, wherein a portion of the flow path has an annular cross-sectional geometry defined between the cooling tube and the stem. 3. The assembly of claim 1, wherein a portion of the flow path has a parti-annular cross-sectional geometry defined between the cooling tube and the fuel injector. 4. The assembly of claim 1, wherein the cooling tube includes an outlet; anda portion of the flow path extends from the fuel injector to the outlet. 5. The assembly of claim 1, wherein the stem extends along an axis; andthe tip extends radially out from the stem relative to the axis. 6. The assembly of claim 1, wherein the fuel injector further includes a fuel conduit that extends through the stem and is fluidly coupled with the nozzle. 7. The assembly of claim 6, wherein the fuel conduit is one of a plurality of fuel conduits that extend through the stem and are fluidly coupled with the nozzle. 8. The assembly of claim 6, wherein an air gap extends around the fuel conduit and between the fuel conduit and the stem. 9. The assembly of claim 1, further comprising: a base connected to the cooling tube and the stem;wherein the base is adapted to mount the cooling tube and the fuel injector to a case of the turbine engine. 10. The assembly of claim 9, wherein a portion of the flow path extends through the base. 11. The assembly of claim 1, further comprising a heat exchanger adapted to provide the cooling air to the cooling tube. 12. The assembly of claim 1, further comprising a swirler mated with the tip. 13. An assembly for a turbine engine, the assembly comprising: a combustor comprising a combustion chamber;a cooling tithe through which a flow path extends;a fuel injector including a stern connected to a tip, the stem arranged within the cooling tube, and the tip extending from the cooling tube to a nozzle, wherein the nozzle is configured to direct fuel into the combustion chamber; anda duct located outside of the combustor and adapted to receive the cooling air from the cooling tube;wherein the cooling tube is adapted to direct cooling air through the flow path;wherein the cooling tube extends radially relative to a centerline of the turbine engine between an inner end and an outer end; andwherein the cooling tube includes a cooling air inlet and a cooling air outlet, the cooling air inlet is located at the outer end, and the cooling air outlet is located at the inner end. 14. The assembly of claim 13, wherein the cooling tube is connected to the duct by a movable joint. 15. The assembly of claim 13, further comprising: a turbine component;wherein the duct is adapted to provide the cooling air to the turbine component. 16. An assembly for a turbine engine, the assembly comprising: a combustor including a combustion chamber;a structure forming a plenum outside of the combustor;a cooling tube adjacent the combustor, the cooling tube configured with a radial outer cooling air inlet and a radial inner cooling air outlet, and the cooling tube extending radially across the plenum and between the radial outer cooling air inlet and the radial inner cooling air outlet; anda fuel injector including a nozzle adapted to inject fuel into the combustion chamber;wherein at least a portion of the fuel injector is arranged within a flow path that extends through the cooling tube; andwherein the cooling tube is adapted to direct cooling air through the flow path. 17. The assembly of claim 16, wherein the fuel injector further includes a stem connected to a tip;the stem is arranged within the cooling tube; andthe tip interfaces with the combustor. 18. The assembly of claim 17, wherein the fuel injector further includes a fuel conduit that extends through the stem and is fluidly coupled with the nozzle. 19. The assembly of claim 16, further comprising a heat exchanger adapted to provide the cooling air to the cooling tube. 20. The assembly of claim 16, further comprising a turbine component adapted to receive the cooling air from the radial inner cooling air outlet.
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이 특허에 인용된 특허 (11)
Lovett, Jeffery A.; Padget, Frederick C.; Mordosky, John W.; McMahon, Shawn M., Air-blast fuel-injector with shield-cone upstream of fuel orifices.
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