Cooling scheme for an increased gas turbine efficiency
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-001/00
F02C-003/20
출원번호
US-0465830
(2012-05-07)
등록번호
US-8572980
(2013-11-05)
우선권정보
CH-1888/09 (2009-11-07)
발명자
/ 주소
Winkler, Anton
Benz, Urs
Theuer, Andre
Lauffer, Diane
Poyyapakkam, Madhavan
출원인 / 주소
Alstom Technology Ltd
대리인 / 주소
Buchanan Ingersoll & Rooney PC
인용정보
피인용 횟수 :
0인용 특허 :
33
초록▼
A burner for a combustion chamber of a turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner is proposed. The injection device has at least one body arranged in the burner with at least two nozzles for introducing the at least one fuel into
A burner for a combustion chamber of a turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner is proposed. The injection device has at least one body arranged in the burner with at least two nozzles for introducing the at least one fuel into the burner, the body being configured with a streamlined cross-sectional profile which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The carrier air plenum is provided with holes such that carrier air exiting through the holes impinges an inner side of a leading edge portion of the body.
대표청구항▼
1. A burner for a combustion chamber of a turbine, comprising: an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device includes:at least one body which is arranged in the burner, the at least one body being a streamlined body
1. A burner for a combustion chamber of a turbine, comprising: an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device includes:at least one body which is arranged in the burner, the at least one body being a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner, wherein the body has an outer wall including two lateral surfaces substantially parallel to the main flow direction joined at their upstream side by a leading edge portion of the body and joined at their downstream side forming a trailing edge defining the streamlined cross-sectional profile, wherein within the outer wall, there is provided a longitudinal inner carrier air plenum with a wall distanced from the outer wall leaving an interspace therebetween for the introduction of carrier air into the injection device, wherein the carrier air plenum is provided with holes such that carrier air exiting through these holes impinges on an inner side of the leading edge portion of the body of the outer wall; andat least two nozzles for introducing the at least one fuel into the burner, the at least two nozzles being distributed along the trailing edge of the streamlined body. 2. The burner according to claim 1, wherein the carrier air plenum comprises: a tubular duct located in the upstream portion of a cavity defined by the outer wall, wherein a wall of the tubular duct forms the wall distanced from the outer wall leaving the interspace in between for circulation of the carrier air, wherein the wall of the tubular duct, in a region facing the outer wall, runs substantially parallel there to, and wherein a distance between the wall of the tubular duct and the outer wall is established by at least one distance keeping element at at least one of the outer wall and the wall of the tubular duct. 3. The burner according to claim 2, wherein the carrier air plenum extends substantially along a full length of the body terminated by a bottom plate, which is provided with holes for cooling of the bottom plate of the body. 4. The burner according to claim 1, wherein air exiting from the carrier air plenum is used as carrier air of the injection device, wherein the carrier air exits at the injection device via an annular slit enclosing a central fuel jet, wherein the central fuel jet exits via an annular fuel slit. 5. The burner according to claim 1, comprising: a longitudinal inner fuel tubing;wherein within the enclosing outer wall defining the streamlined cross-sectional profile, there is provided the longitudinal inner fuel tubing for an introduction of at least one of liquid and gaseous fuel, with branching off tubing leading to the at least two nozzles, wherein the carrier air plenum is located in an upstream portion of the cavity defined by the outer wall while the longitudinal inner fuel tubing is located in a downstream portion of the cavity defined by the outer wall, wherein a wall of the carrier air plenum is distanced from a wall of the longitudinal inner fuel tubing for circulation of carrier air. 6. The burner according to claim 5, wherein the longitudinal inner fuel tubing is circumferentially distanced from the outer wall, defining the interspace for the delivery of carrier air to the at least two nozzles. 7. The burner according to claim 1, comprising: effusion holes, wherein air exiting from the carrier air plenum exits the injection device via the effusion holes, wherein the effusion holes are located at at least one of the trailing edge of the injection device, the lateral surfaces, the leading edge and large scale mixing devices of the injection device. 8. The burner according to claim 1, wherein the at least two nozzles have their outlet orifices downstream of the trailing edge of the streamlined body, wherein the distance (d) between an essentially straight trailing edge at the position of a nozzle, and the outlet orifice of the nozzle, measured along the main flow direction, is at from 2 mm-10 mm. 9. The burner as claimed in claim 1, wherein the streamlined body comprises: a cross-sectional profile which is mirror symmetric with respect to the central plane of the body. 10. The burner according to claim 1, comprising: at least one nozzle inclined with respect to the flow direction. 11. The burner according to claim 5, comprising: a second inner fuel tubing wherein within the longitudinal inner fuel tubing provided for gaseous fuel there is provided the second inner fuel tubing for a second type of fuel, wherein the second type of fuel is a liquid fuel and wherein gaseous fuel is delivered by a second interspace between the walls of said longitudinal inner fuel tubing and the walls of the second inner fuel tubing. 12. The burner as claimed in claim 1, comprising: at least one vortex generator wherein upstream of the at least one nozzle on at least one lateral surface there is located the at least one vortex generator, wherein the vortex generator has an attack angle in the range of 15-40° and/or a sweep angle in the range of 40-70°, wherein at least two nozzles are arranged at different positions along the trailing edge, wherein upstream of each of these nozzles at least one vortex generator is located, and wherein vortex generators to adjacent nozzles are located at opposite lateral surfaces. 13. The burner according to claim 12, comprising: cooling elements provided for the at least one vortex generators, wherein the cooling elements are effusion cooling holes provided in at least one surface of the vortex generator, and the effusion cooling holes are fed with air from the carrier gas feed also used for the fuel injection. 14. The burner according to claim 1, wherein the streamlined body extends across substantially the entire flow cross section between opposite walls of the burner, wherein the burner is an annular burner arranged circumferentially with respect to a turbine axis, and wherein between 10-100 streamlined bodies, are arranged around the circumference distributed equally along the circumference. 15. The burner according to claim 1, wherein the fuel is injected from the nozzle together with a carrier air stream which is supplied by the carrier air plenum, and wherein the carrier air is low pressure air with a pressure in the range of 10-22 bar, and wherein this carrier air is directly derived from a compressor stage without subsequent cooling. 16. The burner according to claim 1 in combination with a turbine combustion chamber configured for combustion under high reactivity conditions, and/or for the combustion at high burner inlet temperatures and/or for combustion of MBtu fuel with a calorific value of 5000-20,000 kJ/kg. 17. The burner as claimed in claim 12, comprising: at least four nozzles arranged along the trailing edge and vortex generators alternatingly located at the two lateral surfaces and downstream of each vortex generator there are located at least two nozzles.
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이 특허에 인용된 특허 (33)
Joshi Narendra D. (Cincinnati OH) Ekstedt Edward E. (Montgomery OH) Epstein Michael J. (West Chester OH), Air fuel mixer for gas turbine combustor.
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Lawlor Shawn P., Apparatus and method for fuel-air mixing before supply of low pressure lean pre-mix to combustor for rotating ramjet engine driving a shaft.
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