Gas turbine combustor with quench wake control
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-001/00
F02G-003/00
출원번호
US-0550845
(2009-08-31)
등록번호
US-8739546
(2014-06-03)
발명자
/ 주소
Snyder, Timothy S.
Kim, Won-Wook
출원인 / 주소
United Technologies Corporation
대리인 / 주소
Miller, Matthias & Hull LLP
인용정보
피인용 횟수 :
4인용 특허 :
30
초록▼
A gas turbine engine has a combustor module including an annular combustor having a liner assembly that defines an annular combustion chamber and includes a circumferential row of a plurality of relatively large combustion dilution air admission holes and a circumferential row of a plurality of smal
A gas turbine engine has a combustor module including an annular combustor having a liner assembly that defines an annular combustion chamber and includes a circumferential row of a plurality of relatively large combustion dilution air admission holes and a circumferential row of a plurality of smaller quench air admission holes disposed downstream with respect to the flow of combustion gas products. The plurality of quench air admission holes are arranged with respect to the plurality of relatively large dilution air admission holes disposed upstream thereof such that there is associated with each dilution air admission hole a first quench air admission hole and a second quench air hole, the first quench air hole being offset laterally in a first lateral direction and the second quench air hole being offset laterally in a second lateral direction opposite to the first direction.
대표청구항▼
1. An annular combustor for a gas turbine engine, comprising: a first annular liner extending along a longitudinal axis;a second annular liner spaced radially outboard of and generally coaxially circumscribing the first liner, each of the first annular liner and the second annular liner having a hea
1. An annular combustor for a gas turbine engine, comprising: a first annular liner extending along a longitudinal axis;a second annular liner spaced radially outboard of and generally coaxially circumscribing the first liner, each of the first annular liner and the second annular liner having a heat shield mounted to a shell;a bulkhead extending between a forward end of the first liner and a forward end of the second liner and cooperating therewith to define a combustion chamber for combusting fuel in air;a plurality of first dilution air admission holes formed in the first annular liner and arranged in a circumferential row at circumferentially spaced intervals;a plurality of first dilution air admission holes formed in the second annular liner and arranged in a circumferential row at circumferentially spaced intervals; anda plurality of quench air admission holes formed in at least one of the first and the second annular liners, said plurality of quench air admission holes being arranged in a circumferential row disposed downstream of the plurality of first dilution air holes and offset circumferentially from the plurality of dilution air holes disposed upstream thereof, each of said plurality of quench air admission holes including a respective hole in the shell and a corresponding hole in the heat shield of said at least one of the first and the second annular liners. 2. The annular combustor for a gas turbine as recited in claim 1 wherein the plurality of quench air admission holes are arranged with respect to the plurality of first dilution air admission holes disposed upstream thereof such that there is associated with each first dilution air admission hole a first quench air admission hole and a second quench air hole, the first quench air hole being offset laterally from said associated first dilution air admission hole in a first lateral direction by a first circumferential distance and the second quench air hole being offset laterally from said associated first dilution air admission hole in a second lateral direction opposite to the first direction by a second circumferential distance. 3. The annular combustor for a gas turbine as recited in claim 2 wherein the first circumferential distance and the second circumferential distance are substantially the same. 4. The annular combustor for a gas turbine engine as recited in claim 3 wherein each first dilution air admission hole in said first and second annular liners defines an opening having a second air flow area, each of the quench air admission holes in said at least one of the first and second annular liners defines an opening having a first air flow area and, the first air flow area being smaller the second air flow area. 5. The annular combustor for a gas turbine engine as recited in claim 2 wherein each first dilution air admission hole defines an opening having a lateral dimension, DL, and each quench air admission hole defines an opening having a lateral dimension, DQ, the lateral dimension DQ, being less than the lateral dimension, DL. 6. The annular combustor for a gas turbine engine as recited in claim 2 wherein the plurality of first dilution air admission holes formed in said at least one of the first and second annular liners comprise a plurality of circular holes having a first diameter, DL, and said plurality of quench air admission holes comprises a plurality of circular holes having a second diameter, DQ, the second diameter, DQ, being about ⅓ of the first diameter, DL. 7. The annular combustor for a gas turbine engine as recited in claim 6 wherein the circumferential row of quench air admission holes is disposed axially downstream of the circumferential row of first dilution air admission holes by a distance, SA, ranging from about one-half the first diameter, DL, up to about one first diameter, DL. 8. The annular combustor for a gas turbine engine as recited in claim 7 wherein the circumferential row of quench air admission holes is disposed axially downstream of the circumferential row of first dilution air admission holes by a distance, SA, substantially equal to about seven tenths of the first diameter, DL. 9. The annular combustor for a gas turbine engine as recited in claim 6 wherein the first lateral distance by which each first quench air admission hole is laterally offset from the associated first dilution air admission and the second lateral distance by which each second quench air admission hole is laterally offset from the associated first dilution air admission are equal and have a magnitude about equal to the first diameter, DL. 10. The annular combustor for a gas turbine engine as recited in claim 2 wherein the plurality of dilution air admission holes formed in said at least one of the first and second annular liners comprise a plurality of axially elongated generally elliptical holes having a lateral axis, DL, and said plurality of quench air holes comprises a plurality of circular holes having a second diameter, the second diameter, DQ, having a magnitude lying in the range from about 0.25 to about 0.40 of the first diameter, DL. 11. The annular combustor for a gas turbine engine as recited in claim 10 wherein the circumferential row of quench air admission holes is disposed axially downstream of the circumferential row of dilution elliptical first air admission holes by a center-to-center spacing, SA, ranging from about 1.5 to about 2.0 times DL. 12. The annular combustor for a gas turbine engine as recited in claim 10 wherein the first lateral distance by which each first quench air admission hole is offset from the associated first dilution air admission and the second lateral distance by which each second quench air admission hole is offset from the associated first dilution air admission are equal and have a magnitude lying in the range from about 0.5 to about 0.9 of the lateral axis, DL, of the associated elliptical dilution air admission hole. 13. A method for controlling temperature deviations in the exhaust gases exiting an annular combustion chamber defined between an inner circumferentially extending liner and an outer circumferentially extending liner spaced radially outboard of and coaxially circumscribing the inner liner, each of the inner circumferentially extending liner and the outer circumferentially extending liner having a heat shield mounted to a shell, wherein combustion dilution air is admitted into the combustion chamber through a plurality of relatively large dilution air admission holes disposed in a circumferentially extending row in each of the inner liner and the outer liner; the method comprising the steps of: providing a plurality of relatively smaller quench air admission holes in a circumferential row in at least one of the inner and outer liners at a location downstream of the row of relatively large dilution air admission holes, each of said plurality of relatively smaller quench air admission holes including a respective hole in the shell and a corresponding hole in the heat shield of said at least one of the inner and outer liners;arranging the plurality of relatively smaller quench air admission holes relative to the plurality of relatively large dilution air admission holes upstream thereof such that there is associated with each relatively large dilution air admission hole a first quench air admission hole and second quench air admission hole, the first quench air admission hole and a second quench air admission hole, the first quench air admission hole being offset laterally in a first lateral direction and the second quench air admission hole being offset laterally in a second lateral direction opposite to the first direction; andadmitting quench air into the combustion chamber through said plurality of quench air admission holes. 14. The method as recited in claim 13 further comprising the step of offsetting the first quench air admission hole laterally in a first lateral direction by a first circumferential distance and offsetting the second quench air admission hole laterally in a second lateral direction opposite to the first direction by a second circumferential distance, the first circumferential distance and the second circumferential distance being equal. 15. The method as recited in claim 13 wherein each dilution air admission hole defines an opening having a lateral dimension, DL, and each quench air admission hole defines an opening having a lateral dimension, DQ, the lateral dimension, DQ, being less than the lateral dimension, DL. 16. The method as recited in claim 13 wherein the step of providing a plurality of relatively smaller quench air admission holes in a circumferential row in at least one of the inner and outer liners at a location downstream of the row of relatively large dilution air admission holes comprises disposing the circumferential row of quench air admission holes axially downstream of a circumferential row of circular first dilution air admission holes having a diameter, DL, by a distance, SA, ranging from about one-half the first diameter, DL, up to about one first diameter, DL. 17. The method as recited in claim 13 wherein the step of providing a plurality of relatively smaller quench air admission holes in a circumferential row in at least one of the inner and outer liners at a location downstream of the row of relatively large dilution air admission holes comprises disposing the circumferential row of quench air admission holes downstream of a circumferential row of generally elliptical first dilution air admission holes having a lateral dimension, DL, by a distance, SA, ranging from about 1.5 the lateral dimension, DL, up to about one twice the lateral dimension, DL. 18. A liner panel for an annular liner of a gas turbine engine combustor, the liner panel having a heat shield mounted to a shell, the liner panel having a longitudinal expanse and a lateral expanse and comprising: at least one relatively larger dilution air admission hole passing therethrough; andat least one relatively smaller diameter quench air admission hole passing therethrough, the at least one quench air admission hole being disposed downstream of and offset circumferentially from the at least one dilution air admission hole, the at least one quench air admission hole including a respective hole in the shell and a corresponding hole in the heat shield. 19. The liner panel as set forth in claim 18 further comprising a second relatively smaller quench air admission hole passing therethrough, said second quench air admission hole being disposed downstream of the at least one dilution air admission hole in a circumferential row with said at least one quench air admission hole and being equally offset laterally from the least at least one dilution air admission hole as the at least one quench air admission hole in a lateral direction opposite to said at least one quench air admission hole. 20. The annular combustor for a gas turbine engine as recited in claim 1, wherein the respective holes in the shell are slightly larger than the corresponding holes in the heat shield.
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이 특허에 인용된 특허 (30)
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Ansart Denis Roger Henri,FRX ; James Bruno,FRX ; Desaulty Michel Andre Albert,FRX ; Staessen Richard Emile,FRX, Turbomachine combustion chamber with inner and outer injector rows.
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