Gas turbine combustor exit piece with hinged connections
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/20
F01D-009/02
F23R-003/42
출원번호
US-0834185
(2013-03-15)
등록번호
US-9322335
(2016-04-26)
발명자
/ 주소
Charron, Richard C.
Pankey, William W.
출원인 / 주소
SIEMENS ENERGY, INC.
인용정보
피인용 횟수 :
0인용 특허 :
7
초록▼
An exit piece (66) with an inlet throat (67) that conducts a combustion gas flow (36A) in a path (82) from a combustor (63) to an annular chamber (68) that feeds the first blade section (37) of a gas turbine (26). The exit piece further includes an outlet portion (69) that forms a circumferential se
An exit piece (66) with an inlet throat (67) that conducts a combustion gas flow (36A) in a path (82) from a combustor (63) to an annular chamber (68) that feeds the first blade section (37) of a gas turbine (26). The exit piece further includes an outlet portion (69) that forms a circumferential segment of the annular chamber. The outlet portion interconnects with adjacent outlet portions by hinges (78A, 78B, 80A, 80B). Each hinge may have a hinge axis (82A, 82B) parallel to a centerline (21) of the turbine. Respective gas flows (36A) are configured by an assembly (60) of the exit pieces to converge on the feed chamber (68) into a uniform helical flow that drives the first blade section with minimal circumferential variations in force.
대표청구항▼
1. An exit piece for conducting combustion gas from a combustor to a first stage of turbine blades of a gas turbine engine, the exit piece comprising: an inlet portion; andan outlet portion comprising a circumferentially upstream end and a circumferentially downstream end relative to a direction of
1. An exit piece for conducting combustion gas from a combustor to a first stage of turbine blades of a gas turbine engine, the exit piece comprising: an inlet portion; andan outlet portion comprising a circumferentially upstream end and a circumferentially downstream end relative to a direction of rotation of a rotor shaft about an engine centerline;wherein each circumferential end of the outlet portion comprises a radially inner hinge part and a radially outer hinge part relative to the engine centerline; andwherein each of the hinge parts is configured to directly hingedly connect to a mating hinge part on a respective adjacent outlet portion of an adjacent exit piece when assembled in the gas turbine engine. 2. The exit piece of claim 1, wherein each of the hinge parts comprises a hinge axis that is parallel to the engine centerline. 3. The exit piece of claim 1, wherein each of the hinge parts hingedly connects to its respective mating hinge part via a first portion of a hinge pin inserted in the hinge part with a hinge axis parallel to the engine centerline, and the hinge pin further comprises a second portion configured to fasten to a boss formed on the exit piece or on the respective adjacent exit piece. 4. The exit piece of claim 1, wherein: the outer hinge part on the downstream end of the outlet portion comprises a segmented hinge barrel set back from a seal plane of said downstream end; andthe outer hinge part on the upstream end of the outlet portion comprises a segmented hinge barrel extending beyond a seal plane of said upstream end, wherein each hinge barrel comprises an axis parallel to the engine centerline. 5. The exit piece of claim 4, wherein: the inner hinge part on the downstream end of the outlet portion comprises a segmented hinge barrel extending beyond the seal plane of the downstream end; andthe inner hinge part on the upstream end of the outlet portion comprises a segmented hinge barrel set back from the seal plane of the upstream end. 6. The exit piece of claim 1, wherein the upstream end of the outlet portion is configured for fluid communication with an outlet end of an upstream adjacent exit piece, and wherein the downstream end of the outlet portion is configured for fluid communication with an outlet end of a downstream adjacent exit piece. 7. The exit piece of claim 1, wherein at least one of the hinge parts at the circumferentially upstream end comprises plural knuckles, and wherein at least one of the hinge parts at the circumferentially downstream end comprises plural knuckles. 8. An annular array of adjacent exit pieces, wherein each exit piece is formed in accordance with claim 1, wherein respective radially inner and radially outer hinge parts of a downstream end of each exit piece are engaged with respective radially inner and radially outer hinge parts of an upstream end of an adjacent exit piece, and each pair of engaged hinge parts is joined by a respective hinge pin. 9. The annular array of adjacent exit pieces of claim 8, wherein a first one of each pair of engaged hinge parts comprises a segmented hinge barrel set back from a seal plane between the respective adjacent exit pieces, and a second one of each pair of engaged hinge parts comprises a segmented hinge barrel extending beyond the seal plane to form a hinge axis parallel to the engine centerline. 10. The annular array of adjacent exit pieces of claim 9, further comprising an outer hinge pin and an inner hinge pin joining the respective engaged hinge parts of a respective upstream end with a respective downstream end of adjacent exit pieces are affixed to a boss formed on one of the respective adjacent exit pieces. 11. A plurality of exit pieces for conducting combustion gas from a respective plurality of can annular combustors to a first stage blade section of a gas turbine, each exit piece comprising: an inlet throat that receives combustion gas from a respective one of the combustors; andan outlet portion comprising a segment of an annular combustion gas feed chamber;wherein the outlet portion comprises a circumferentially upstream end connected to an adjacent circumferentially upstream one of the exit pieces by a first radially inner hinge and a first radially outer hinge, and the outlet portion comprises a circumferentially downstream end connected to an adjacent circumferentially downstream one of the exit pieces by a second radially inner hinge and a second radially outer hinge;wherein in each hinge respective hinge parts directly engage each other about a hinge axis, andwherein upstream and downstream are relative to a direction of rotation of rotor blades about a centerline of the turbine. 12. The apparatus of claim 11, wherein each hinge comprises a segmented hinge barrel extending beyond a seal plane of a first of a respective pair of adjacent exit pieces, a cooperating segmented hinge barrel set back from the seal plane of a seal plane of a second of a respective pair of adjacent exit pieces, and a hinge pin disposed there through. 13. The apparatus of claim 12, further comprising a boss formed on one of the respective pair of adjacent exit pieces, and an end of the hinge pin affixed to the boss. 14. The apparatus of claim 13, wherein the plurality of exit pieces forms a circular array about the turbine centerline, each inlet throat provides a straight flow path from an inlet end thereof to the annular chamber, and each flow path is primarily tangential relative to an arc of the annular chamber, and partly rearward. 15. The plurality of exit pieces of claim 13 wherein each inlet throat fully bounds a gas flow from one of the combustors, and delivers the gas flow to the annular feed chamber in a primarily tangential and partly rearward direction, wherein adjacent ones of the exit pieces provide respective gas flows that enter the feed chamber adjacently in a converging flow configuration. 16. An exit piece assembly for delivering gasses from a plurality of can annular combustors to a first stage blade section of a gas turbine, the assembly comprising; a flow-directing structure comprising a plurality of interconnected exit pieces, each exit piece configured to receive a gas flow from a respective combustor;each exit piece comprising a throat portion and an outlet portion that forms a circumferential segment of an annular chamber;wherein the outlet portion comprises a front wall that is coplanar with a back wall of the throat portion and is further coplanar with a front wall of an upstream adjacent throat portion, wherein upstream is relative to a direction of rotation of a rotor shaft about a centerline of the turbine;wherein the annular chamber is formed of a circular array of the outlet portions interconnected by respective hinges with respective axes parallel to the centerline of the turbine; andwherein adjacent ones of the exit pieces guide respective gas flows to converge into the chamber into a generally helical flow. 17. The assembly of claim 16, wherein each outlet portion comprises: a circumferentially downstream end comprising a radially outer segmented hinge barrel set back from a seal plane of said downstream end, and a radially inner segmented hinge barrel extending circumferentially beyond the seal plane of said downstream end; anda circumferentially upstream end comprising a radially outer segmented hinge barrel extending circumferentially beyond a seal plane of said upstream end, and a radially inner segmented hinge barrel set back from the seal plane of said upstream end. 18. The assembly of claim 17, wherein each segmented hinge barrel on said each outlet portion is joined to a mating segmented hinge barrel on an adjacent outlet portion by an L-shaped pin comprising a first leg inserted through both the segmented hinge barrel and the mating segmented hinge barrel, and a second leg that is fastened to a boss on a front side of the outlet portion or on a front side of the adjacent outlet portion.
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이 특허에 인용된 특허 (7)
Meylan Pierre,CHX, Combustion chamber having integrated guide blades.
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