Transition duct assembly with late injection features
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/34
F02C-007/22
F01D-005/02
F01D-009/02
F23R-003/46
출원번호
US-0079116
(2016-03-24)
등록번호
US-10260424
(2019-04-16)
발명자
/ 주소
Flanagan, James Scott
McMahan, Kevin Weston
LeBegue, Jeffrey Scott
출원인 / 주소
General Electric Company
대리인 / 주소
Wilson, Charlotte C.
인용정보
피인용 횟수 :
0인용 특허 :
49
초록▼
A turbomachine includes a plurality of transition ducts disposed in a generally annular array. Each transition duct includes an inlet, an outlet, and a passage defining an interior and extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis.
A turbomachine includes a plurality of transition ducts disposed in a generally annular array. Each transition duct includes an inlet, an outlet, and a passage defining an interior and extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of each transition duct is offset from the inlet along the longitudinal axis and the tangential axis. Each transition duct further includes an upstream portion and a downstream portion. The turbomachine further includes a late injection assembly disposed between the upstream portion and the downstream portion of a transition duct and which provides fluid communication for an injection fluid to flow into the interior downstream of the inlet of the transition duct. The late injection assembly includes a late injection ring.
대표청구항▼
1. A turbomachine comprising: a plurality of transition ducts disposed in a generally annular array, each of the plurality of transition ducts comprising an inlet, an outlet, and a passage defining an interior and extending between the inlet and the outlet and defining a longitudinal axis, a radial
1. A turbomachine comprising: a plurality of transition ducts disposed in a generally annular array, each of the plurality of transition ducts comprising an inlet, an outlet, and a passage defining an interior and extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis, the outlet of each of the plurality of transition ducts offset from the inlet along the longitudinal axis and the tangential axis, each of the plurality of transition ducts further comprising an upstream portion and a downstream portion, the upstream portion extending between the inlet and an aft end, the downstream portion extending between a head end and the outlet; anda late injection assembly disposed between the upstream portion and the downstream portion of a first transition duct of the plurality of transition ducts, the late injection assembly comprising a late injection ring and an annular fuel manifold radially outward of and surrounding the late injection ring, the late injection ring comprising an inner flange an outer flange radially positioned between the inner flange and the annular fuel manifold and connected to the inner flange at least by circumferentially spaced partitions, and at least one main conduit defined between each adjacent pair of the spaced partitions, each of the at least one main conduit including and extending between a main conduit inlet oriented in an axial direction and a main conduit outlet defined radially through the inner flange, wherein the main conduit inlet is defined in a downstream side of the late injection ring for accepting working fluid for mixing with fuel within each of the at least one main conduit, and each of the main conduit outlet is in fluid communication with the interior of the first transition duct. 2. The turbomachine of claim 1, wherein the fuel manifold is in fluid communication with a fuel source for receiving the fuel from the fuel source and in fluid communication with each of at least one main conduit for flowing the fuel to each of the at least one main conduit. 3. The turbomachine of claim 2, wherein the fuel manifold defines a manifold conduit within the fuel manifold and the late injection ring defines a fuel plenum, and wherein the fuel flows from the manifold conduit of the fuel manifold to the fuel plenum and from the fuel plenum through one or more injection conduits to each of the at least one main conduit and mixes with working fluid in each of the at least one main conduit. 4. The turbomachine of claim 3, wherein the working fluid flowing into the main conduit enters the main conduit in an axial direction parallel to the longitudinal axis; and wherein the one or more injection conduits is disposed at an angle relative to the axial direction of flow of the working fluid as the working fluid enters the main conduit. 5. The turbomachine of claim 1, wherein at least one partition of the circumferentially spaced partitions of the late injection ring defines a bypass conduit, the bypass conduit extending between a bypass inlet defined in a downstream side of the late injection ring and a bypass outlet defined in an upstream side of the late injection ring. 6. The turbomachine of claim 1, further comprising a flow sleeve generally surrounding the first transition duct, the flow sleeve comprising an upstream portion extending between a flow sleeve inlet and a flow sleeve aft end, a downstream portion extending between a flow sleeve head end and a flow sleeve outlet, and a sleeve passage extending between the flow sleeve inlet and the flow sleeve outlet; and wherein the outer flange of the late injection ring is further disposed between the flow sleeve aft end of the upstream portion and the flow sleeve head end of the downstream portion of the flow sleeve. 7. The turbomachine of claim 6, wherein the outer flange of the late injection ring is connected to the flow sleeve aft end of the upstream portion of the flow sleeve and the flow sleeve head end of the downstream portion of the flow sleeve. 8. The turbomachine of claim 6, wherein the upstream portions of the first transition duct and the flow sleeve define an upstream cavity therebetween, and wherein the downstream portions of the first transition duct and the flow sleeve define a downstream cavity therebetween. 9. The turbomachine of claim 8, wherein the main conduit inlet of each of the at least one main conduit is in fluid communication with the downstream cavity. 10. The turbomachine of claim 6, wherein the flow sleeve is an impingement sleeve. 11. The turbomachine of claim 1, wherein the outlet of each of the plurality of transition ducts is further offset from the inlet of respective each of the plurality of transition ducts along the radial axis. 12. The turbomachine of claim 1, further comprising a turbine section in communication with the plurality of transition ducts, the turbine section comprising a first stage bucket assembly. 13. The turbine system of claim 12, wherein no nozzles are disposed upstream of the first stage bucket assembly. 14. A turbomachine comprising: a plurality of transition ducts disposed in a generally annular array, each of the plurality of transition ducts comprising an inlet, an outlet, and a passage defining an interior and extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis, the outlet of each of the plurality of transition ducts offset from the inlet along the longitudinal axis and the tangential axis, each of the plurality of transition ducts further comprising an upstream portion and a downstream portion, the upstream portion extending between the inlet and an aft end, the downstream portion extending between a head end and the outlet; wherein the plurality of transition ducts includes a first transition duct;a flow sleeve generally surrounding the first transition duct, the flow sleeve comprising an upstream portion extending between a flow sleeve inlet and a flow sleeve aft end, a downstream portion extending between a flow sleeve head end and a flow sleeve outlet, and a sleeve passage extending between the flow sleeve inlet and the flow sleeve outlet; wherein the upstream portion of the first transition duct and the upstream portion of the flow sleeve define an upstream cavity therebetween, and wherein the downstream portion of the first transition duct and the downstream portion of the flow sleeve define a downstream cavity therebetween; anda late injection assembly disposed between the upstream portion of the first transition duct and the upstream portion of the flow sleeve and the downstream portion of the first transition duct and the downstream portion of the flow sleeve, the late injection assembly comprising:a late injection ring, the late injection ring comprising an inner flange, an outer flange radially positioned between the inner flange and an annular fuel manifold and connected to the inner flange at least by circumferentially spaced partitions, and at least one main conduit defined between each adjacent pair of the spaced partitions, each of the at least one main conduit including and extending between a main conduit inlet oriented in an axial direction and a main conduit outlet defined radially through the inner flange, the main conduit inlet defined in a downstream side of the late injection ring and in fluid communication with the downstream cavity for accepting working fluid for mixing with fuel within each of the at least one main conduit, each main conduit outlet in fluid communication with the interior of the first transition duct; andthe fuel manifold radially outward of and surrounding the late injection ring, the fuel manifold being in fluid communication with a fuel source for receiving the fuel from the fuel source and in fluid communication with the at least one main conduit for flowing the fuel to each of the at least one main conduit, wherein the fuel manifold defines a manifold conduit within the fuel manifold and the late injection ring defines a fuel plenum, and wherein the fuel flows from the manifold conduit of the fuel manifold to the fuel plenum and from the fuel plenum through one or more injection conduits to each of the at least one main conduit and mixes with working fluid in each of the at least one main conduit. 15. The turbomachine of claim 14, wherein at least one partition of the circumferentially spaced partitions of the late injection ring defines a bypass conduit, the bypass conduit extending between a bypass inlet defined in a downstream side of the late injection ring and a bypass outlet defined in an upstream side of the late injection ring. 16. The turbomachine of claim 14, wherein the inner flange of the late injection ring is connected to the aft end of the upstream portion and the head end of the downstream portion of the first transition duct; and wherein the outer flange of the late injection ring is connected to the flow sleeve aft end of the upstream portion of the flow sleeve and the flow sleeve head end of the downstream portion of the flow sleeve. 17. The turbomachine of claim 14, wherein the flow sleeve is an impingement sleeve. 18. The turbomachine of claim 14, further comprising a turbine section in communication with the plurality of transition ducts, the turbine section comprising a first stage bucket assembly, and wherein no nozzles are disposed upstream of the first stage bucket assembly. 19. The turbomachine of claim 14, wherein the working fluid flowing into the main conduit enters the main conduit in an axial direction parallel to the longitudinal axis; and wherein the one or more injection conduits is disposed at an angle relative to the axial direction of flow of the working fluid as the working fluid enters the main conduit.
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