Multi-slot inter-turbine duct assembly for use in a turbine engine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/00
출원번호
UP-0258547
(2005-10-25)
등록번호
US-7549282
(2009-07-01)
발명자
/ 주소
Widenhoefer, James Fredric
Graziosi, Paolo
Kirtley, Kevin Richard
출원인 / 주소
General Electric Company
대리인 / 주소
Clarke, Penny A.
인용정보
피인용 횟수 :
11인용 특허 :
4
초록▼
A bypass channel for use in an inter-turbine transition duct assembly of a turbine engine is connected to a suction port disposed upstream of a high-pressure turbine and at least two injection openings disposed downstream of the high-pressure turbine. The flow through the bypass channel is motivated
A bypass channel for use in an inter-turbine transition duct assembly of a turbine engine is connected to a suction port disposed upstream of a high-pressure turbine and at least two injection openings disposed downstream of the high-pressure turbine. The flow through the bypass channel is motivated by the natural pressure difference across the high-pressure turbine. The flow out of the at least two injection openings is used to energize the boundary layer flow downstream of the high-pressure turbine in order to allow for the use of a more aggressively expanded inter-turbine duct without boundary layer separation. Methods for optimizing the flow through the turbine engine are also disclosed.
대표청구항▼
What is claimed is: 1. An inter-turbine duct assembly for a turbine engine, the duct assembly comprising: a duct having an upstream portion fluidly coupled to a high pressure turbine and a downstream portion fluidly coupled to a low pressure turbine, wherein the duct comprises an inner body surface
What is claimed is: 1. An inter-turbine duct assembly for a turbine engine, the duct assembly comprising: a duct having an upstream portion fluidly coupled to a high pressure turbine and a downstream portion fluidly coupled to a low pressure turbine, wherein the duct comprises an inner body surface and an outer body surface, and wherein the duct defines a primary fluid flow path between high and low pressure turbines; a suction port disposed upstream of the high pressure turbine on the outer-body surface of the duct; at least two injection openings disposed along the outer body surface of the duct downstream of the high pressure turbine and upstream of the low pressure turbine; and a channel in fluid communication with the suction port and the at least two injection openings, wherein the channel defines a bypass fluid flow path between the suction port and the at least two injection openings. 2. The duct assembly of claim 1, wherein the suction port is in fluid communication with the primary flow path at a position intermediate a compressor and a high-pressure turbine. 3. The duct assembly as in claim 1, wherein the suction port comprises a scoop portion. 4. The duct assembly as in claim 1, wherein the at least two injection openings are adapted to provide a flow of fluid at or prior to a boundary separation point. 5. The duct assembly as in claim 1, wherein the channel further comprises a plenum. 6. An inter-turbine duct assembly, for a turbine engine, the duct assembly comprising: a duct having an upstream portion fluidly coupled to a high pressure turbine and a downstream portion fluidly coupled to a low pressure turbine, wherein the duct comprises an inner body surface and an outer body surface, and wherein the duct defines a primary fluid flow path between high and low pressure turbines; a suction port disposed upstream of the high pressure turbine on the outer-body surface of the duct; at least two injection openings disposed along the outer body surface of the duct downstream of the high pressure turbine; and a channel in fluid communication with the suction port and the at least two injection openings, wherein the channel defines a bypass fluid flow path between the suction port and the at least two injection openings, wherein each one of the at least two injection openings is a slot opening circumferentially disposed about the outer body surface. 7. The duct assembly as in claim 6, wherein each one of the at least two circumferentially disposed injection openings are positioned along the outer body surface of the duct at or prior to a boundary separation point. 8. The duct assembly as in claim 1, wherein each one of the at least two injection openings has a circular or oval cross sectional shape. 9. An inter-turbine duct assembly, for a turbine engine, the duct assembly comprising: a duct having an upstream portion fluidly coupled to a high pressure turbine and a downstream portion fluidly coupled to a low pressure turbine, wherein the duct comprises an inner body surface and an outer body surface, and wherein the duct defines a primary fluid flow path between high and low pressure turbines; a suction port disposed upstream of the high pressure turbine on the outer-body surface of the duct; at least two injection openings disposed along the outer body surface of the duct downstream of the high pressure turbine; and a channel in fluid communication with the suction port and the at least two injection openings, wherein the channel defines a bypass fluid flow path between the suction port and the at least two injection openings, wherein the channel comprises an annular structure. 10. An inter-turbine duct assembly, for a turbine engine, the duct assembly comprising: a duct having an upstream portion fluidly coupled to a high pressure turbine and a downstream portion fluidly coupled to a low pressure turbine, wherein the duct comprises an inner body surface and an outer body surface, and wherein the duct defines a primary fluid flow path between high and low pressure turbines; a suction port disposed upstream of the high pressure turbine on the outer-body surface of the duct; at least two injection openings disposed along the outer body surface of the duct downstream of the high pressure turbine; and a channel in fluid communication with the suction port and the at least two injection openings, wherein the channel defines a bypass fluid flow path between the suction port and the at least two injection openings, wherein each one of the at least two injection openings comprises an annular slot about the outer-body surface. 11. The An inter-turbine duct assembly, for a turbine engine, the duct assembly comprising: a duct having an upstream portion fluidly coupled to a high pressure turbine and a downstream portion fluidly coupled to a low pressure turbine, wherein the duct comprises an inner body surface and an outer body surface, and wherein the duct defines a primary fluid flow path between high and low pressure turbines; a suction port disposed upstream of the high pressure turbine on the outer-body surface of the duct: at least two injection openings disposed along the outer body surface of the duct downstream of the high pressure turbine; and a channel in fluid communication with the suction port and the at least two injection openings, wherein the channel defines a bypass fluid flow path between the suction port and the at least two injection openings, wherein each one of the at least two injection openings comprises an annular slot partially circumscribed about the outer-body surface. 12. The duct assembly of claim 1, wherein the channel further comprises an array of fluid oscillators. 13. The duct assembly of claim 1, wherein each one of the at least two openings are disposed at different axial positions along the length of the duct at and/or prior to a boundary separation point that would exist in the absence of the one opening. 14. A turbine engine including the duct assembly of claim 1.
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이 특허에 인용된 특허 (4)
Graziosi,Paolo; Kirtley,Kevin Richard, High area-ratio inter-turbine duct with inlet blowing.
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