Gas turbine combustion chamber arrangement of axial type of construction
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-003/06
F02C-003/14
F23R-003/16
F23R-003/50
F23R-003/58
F01D-009/04
출원번호
US-0704972
(2011-06-15)
등록번호
US-9151223
(2015-10-06)
우선권정보
DE-10 2010 023 816 (2010-06-15)
국제출원번호
PCT/EP2011/002959
(2011-06-15)
§371/§102 date
20121217
(20121217)
국제공개번호
WO2011/157418
(2011-12-22)
발명자
/ 주소
Negulescu, Dimitrie
출원인 / 주소
Rolls-Royce Deutschland Ltd & Co KG
대리인 / 주소
Klima, Timothy J.
인용정보
피인용 횟수 :
1인용 특허 :
9
초록▼
A gas-turbine combustion chamber arrangement includes a flame tube, a diffuser element arranged upstream of the flame tube in the flow direction, the diffuser element including an annular duct, and an axial compressor arranged upstream of the diffuser element. The diffuser element features an annula
A gas-turbine combustion chamber arrangement includes a flame tube, a diffuser element arranged upstream of the flame tube in the flow direction, the diffuser element including an annular duct, and an axial compressor arranged upstream of the diffuser element. The diffuser element features an annular guide vane area in which guide vanes are arranged, which for redirecting an incoming flow are provided at an angle (α) in a range between 28° and 32° relative to a central axis of the gas turbine. Downstream of the guide vane area, a diffuser area is arranged, the diffuser area not being provided with flow-guiding elements affecting the flow, where burners arranged in the annular combustion chamber are provided with their burner axes at an angle (β) between 40° and 50° relative to the central axis.
대표청구항▼
1. A gas turbine combustion chamber arrangement, comprising: a flame tube;a diffuser element arranged upstream of the flame tube in a flow direction, the diffuser element including an annular duct; andan axial compressor arranged upstream of the diffuser element;the diffuser element including an ann
1. A gas turbine combustion chamber arrangement, comprising: a flame tube;a diffuser element arranged upstream of the flame tube in a flow direction, the diffuser element including an annular duct; andan axial compressor arranged upstream of the diffuser element;the diffuser element including an annular guide vane area having guide vanes for redirecting an incoming flow, the axial compressor configured to provide an inflow to the annular guide vane area at an angle in a range approximately from 45° to 50° in a circumferential direction relative to a central axis of the gas turbine, the guide vanes being provided to reverse the inflow to an angle (α) in a range approximately from 25° to 32° in the circumferential direction relative to the central axis of the gas turbine;a diffuser area positioned downstream of the guide vane area;a plurality of burners arranged in the flame tube, the burners each having axes and being oriented so that the burner axes are positioned at an angle (β) from 40° to 50° in the circumferential direction relative to the central axis. 2. The gas turbine combustion chamber arrangement of claim 1, and further comprising a flame tube inlet and a heat shield associated with each burner and arranged inclined to the burner axis. 3. The gas turbine combustion chamber arrangement of claim 2, wherein the flame tube is constructed and arranged for the formation of swirl flames. 4. The gas turbine combustion chamber arrangement of claim 3, wherein the flame tube has a length (L) to height (H) ratio of L/H<1.4. 5. The gas turbine combustion chamber arrangement of claim 4, and further comprising, downstream of the flame tube, a nozzle guide vane ring having nozzle guide vanes for deflecting flow entering the nozzle guide vane ring, the nozzle guide vanes provided at an angle in a range from 65° to 70° with respect to the central axis. 6. The gas turbine combustion chamber arrangement of claim 5, and further comprising a convergent annular nozzle, the nozzle guide vanes being integrated in the convergent annular nozzle. 7. The gas turbine combustion chamber arrangement of claim 6, and further comprising struts arranged in the diffuser area. 8. The gas turbine combustion chamber arrangement of claim 1, wherein the flame tube is constructed and arranged for the formation of swirl flames. 9. The gas turbine combustion chamber arrangement of claim 8, wherein the flame tube has a length (L) to height (H) ratio of L/H<1.4. 10. The gas turbine combustion chamber arrangement of claim 9, and further comprising, downstream of the flame tube, a nozzle guide vane ring having nozzle guide vanes for deflecting flow entering the nozzle guide vane ring, the nozzle guide vanes provided at an angle in a range from 65° to 70° with respect to the central axis. 11. The gas turbine combustion chamber arrangement of claim 10, and further comprising a convergent annular nozzle, the nozzle guide vanes being integrated in the convergent annular nozzle. 12. The gas turbine combustion chamber arrangement of claim 11, and further comprising struts arranged in the diffuser. 13. The gas turbine combustion chamber arrangement of claim 1, wherein the flame tube has a length (L) to height (H) ratio of L/H<1.4. 14. The gas turbine combustion chamber arrangement of claim 13, and further comprising, downstream of the flame tube, a nozzle guide vane ring having nozzle guide vanes for deflecting flow entering the nozzle guide vane ring, the nozzle guide vanes provided at an angle in a range from 65° to 70° with respect to the central axis. 15. The gas turbine combustion chamber arrangement of claim 14, and further comprising a convergent annular nozzle, the nozzle guide vanes being integrated in the convergent annular nozzle. 16. The gas turbine combustion chamber arrangement of claim 15, and further comprising struts arranged in the diffuser area. 17. The gas turbine combustion chamber arrangement of claim 1, and further comprising, downstream of the flame tube, a nozzle guide vane ring having nozzle guide vanes for deflecting flow entering the nozzle guide vane ring, the nozzle guide vanes provided at an angle in a range from 65° to 70° with respect to the central axis. 18. The gas turbine combustion chamber arrangement of claim 17, and further comprising a convergent annular nozzle, the nozzle guide vanes being integrated in the convergent annular nozzle. 19. The gas turbine combustion chamber arrangement of claim 1, and further comprising a convergent annular nozzle, the nozzle guide vanes being integrated in the convergent annular nozzle. 20. The gas turbine combustion chamber arrangement of claim 1, and further comprising struts arranged in the diffuser area.
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이 특허에 인용된 특허 (9)
Pieussergues, Christophe; Sandelis, Denis Jean Maurice, Chamber endwall, method of producing it, combustion chamber comprising it, and turbine engine equipped therewith.
Dodds Willard J. (West Chester OH) Widener Stanley K. (San Antonio TX) Taylor Keith K. (Cincinnati OH) Foltz Howard L. (West Chester OH) Steffens Steven C. (Cincinnati OH), Method and apparatus for injecting dilution air.
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