Gas turbine engine exhaust diffuser including circumferential vane
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-001/38
F01D-025/30
출원번호
US-0325178
(2011-12-14)
등록번호
US-9032721
(2015-05-19)
발명자
/ 주소
Orosa, John A.
Matys, Pawel
출원인 / 주소
Siemens Energy, Inc.
인용정보
피인용 횟수 :
1인용 특허 :
6
초록▼
A flow passage defined between an inner and an outer boundary for guiding a fluid flow in an axial direction. A flow control vane is supported at a radial location between the inner and outer boundaries. A fluid discharge opening is provided for discharging a flow of the compressed fluid from a trai
A flow passage defined between an inner and an outer boundary for guiding a fluid flow in an axial direction. A flow control vane is supported at a radial location between the inner and outer boundaries. A fluid discharge opening is provided for discharging a flow of the compressed fluid from a trailing edge of the vane, and a fluid control surface is provided adjacent to the fluid discharge opening and extends in the axial direction at the trailing edge of the vane. The fluid control surface has a curved trailing edge forming a Coanda surface. The fluid discharge opening is selectively provided with a compressed fluid to produce a Coanda effect along the control surface. The Coanda effect has a component in the radial direction effecting a turning of the fluid flow in the flow path radially inward or outward toward one of the inner and outer boundaries.
대표청구항▼
1. A flow passage for an axial flow machine comprising: an inner boundary;an outer boundary radially spaced from said inner boundary so that an annular flow path for guiding a fluid flow in an axial direction is defined therebetween;a source of compressed fluid;a flow control vane including leading
1. A flow passage for an axial flow machine comprising: an inner boundary;an outer boundary radially spaced from said inner boundary so that an annular flow path for guiding a fluid flow in an axial direction is defined therebetween;a source of compressed fluid;a flow control vane including leading and trailing edges, said vane supported at a radial location between said inner and outer boundaries, wherein said vane is supported on a strut structure and said strut structure extends from said inner boundary to said outer boundary and includes laterally opposing sides, and said flow control vane intersects said laterally opposing sides of said strut structure;a fluid discharge opening for discharging a flow of the compressed fluid from said trailing edge;a fluid control surface adjacent to said fluid discharge opening and extending in the axial direction at said trailing edge of said vane, said fluid control surface having a curved trailing edge forming a Coanda surface; andsaid fluid discharge opening being selectively provided with the compressed fluid from said source of compressed fluid to produce a Coanda effect along said control surface, the Coanda effect having a component in the radial direction effecting a turning of the fluid flow in said flow path radially inward or outward toward one of said inner and outer boundaries. 2. The flow passage of claim 1, wherein said source of compressed fluid is located outside of said flow passage, and including a plenum located within said vane in fluid communication with said source of compressed fluid and providing a flow of the compressed fluid to said fluid discharge opening. 3. The flow passage of claim 2, wherein said vane extends circumferentially within said flow path, and said fluid discharge opening comprises: a first fluid discharge opening located on a radially outward facing side of said vane;a second fluid discharge opening located on a radially inward facing side of said vane;said first and second fluid discharge openings being located adjacent to respective radially facing sides of said fluid control surface; andsaid first and second fluid discharge openings being located in fluid communication with said plenum to selectively provide a majority of a compressed fluid flow to either one of said first and second fluid discharge openings. 4. The flow passage of claim 3, wherein: when the majority of compressed fluid flow is provided to said first fluid discharge opening, said Coanda effect along said control surface effects a radial inward turning of the fluid flow in said flow path; andwhen the majority of compressed fluid flow is provided to said second fluid discharge opening, said Coanda effect along said control surface effects a radial outward turning of the fluid flow in said flow path. 5. The flow passage of claim 1, wherein said fluid control surface comprises opposing first and second radially facing portions that are generally symmetrical about a plane extending axially from said leading edge to said trailing edge of said vane. 6. The flow passage of claim 1, wherein said flow control vane comprises a first flow control vane and said radial location comprises a first radial location, and including a second flow control vane located at a second radial location, radially outward from said first vane, between said inner and outer boundaries. 7. The flow passage of claim 6, wherein said outer boundary diverges at a predetermined angle, and at least one of said first and second control vanes defines a chordal axis between said leading edge and said trailing edge, said chordal axis oriented in a direction generally parallel to said predetermined angle. 8. The flow passage of claim 1, wherein said inner boundary includes a tail cone having a conical surface tapering radially inward toward a central axis of said flow path, said trailing edge of said flow control vane being substantially aligned, in the axial direction, with at least a portion of said tail cone. 9. A flow passage comprising an exhaust diffuser in a gas turbine engine, the flow passage comprising: an inner boundary defined by an exhaust diffuser hub;an outer boundary defined by an exhaust diffuser shell, said outer boundary diverging radially outward at a predetermined angle and being radially spaced from said inner boundary so that an annular flow path for guiding an exhaust gas flow in an axial direction is defined therebetween;a source of compressed fluid;a plurality of strut structures, each having a radially directed axis extending between said inner and outer boundaries;a pair of radially opposing, spaced aerodynamic surfaces forming a flow control vane having a chord length extending in the axial direction, and leading and trailing edges at opposing ends of said chord length;said flow control vane being affixed to and extending between said strut structures, said flow control vane defining a ring located between said inner and outer boundaries and receiving fluid from said source of compressed fluid;first and second fluid discharge slots for discharging the compressed fluid from said trailing edge;a fluid control surface adjacent to said fluid discharge slots, said control surface extending beyond said trailing edge of said vane and having curved trailing edge portions adjacent each of said slots forming a Coanda surface; andsaid flow control slots being selectively provided with the compressed fluid from said source of compressed fluid to produce a Coanda effect along said control surface, the Coanda effect having a component in the radial direction effecting a turning of the exhaust gas flow in said flow path radially inward or outward toward one of said inner and outer boundaries. 10. The flow passage of claim 9, wherein: said source of compressed fluid is located outside of said flow passage, and including a plenum located within said vane in fluid communication with said source of compressed fluid and providing a flow of the compressed fluid to said fluid discharge slots; andsaid first and second fluid discharge slots being located in fluid communication with said plenum to selectively provide at least a majority of a compressed fluid flow to one of said first and second fluid discharge slots. 11. The flow passage of claim 9, including a plurality of said flow control vanes defining a plurality of rings located in radially spaced relation to each other between said inner and outer boundaries, each said flow control vane having first and second fluid discharge slots, on respective radially outward and inward facing sides of said vane, in fluid communication with said source of compressed air and a fluid control surface defining a Coanda surface adjacent respective ones of said first and second fluid discharge slots. 12. The flow passage of claim 11, wherein a first one of said flow control vanes comprises a radially inner vane providing a Coanda effect flow to draw the fluid flow radially inward toward said inner boundary, and a second one of said flow control vanes comprises a radially outer vane providing a Coanda effect flow to draw the fluid flow toward said outer boundary. 13. The flow passage of claim 9, wherein said inner boundary includes a tail cone located at a downstream end of said diffuser hub. 14. The flow passage of claim 9, wherein said tail cone has a conical surface tapering radially inward toward a central axis of said flow path, said trailing edge of said flow control vane being substantially aligned, in the axial direction, with at least a portion of said tail cone. 15. A method of exhaust diffusion in a turbine engine comprising: providing a turbine engine having a turbine section and an exhaust diffuser section, the exhaust diffuser section including an inner boundary defined at least by a hub structure comprising at least a hub and a tail cone, the hub having an upstream end and a downstream end, the tail cone having an upstream end located adjacent the downstream end of the hub and a downstream end, and the tail cone tapering radially inward toward an axis of the diffuser, the exhaust diffuser section further including an outer boundary radially spaced from the inner boundary so that a flow path is defined therebetween;supplying a turbine exhaust gas flow to the flow path;providing a flow of fluid from a source of compressed fluid to a vane located between the inner and outer boundaries, the flow of fluid flowing in a Coanda effect along a Coanda surface to entrain a portion of the exhaust gas flow to effect a biasing of the exhaust gas flow toward at least one of the inner and outer boundaries; andwherein the vane includes first and second fluid discharge slots, and including alternately: providing a majority of the flow fluid from one of the first and second fluid discharge slots to cause a flow along the Coanda surface in a first direction toward the inner boundary; andproviding a majority of the flow fluid from the other of the first and second fluid discharge slots to cause a flow along the Coanda surface in a second direction toward the outer boundary. 16. The method of claim 15, wherein the vane comprises a first vane adjacent to the inner boundary, and including at least a second vane radially outward from the first vane and adjacent to the outer boundary, and receiving a flow of fluid from the source of compressed air flowing along a further Coanda surface, and including simultaneously: 1) providing the flow from the first vane to effect the biasing of the exhaust gas flow radially inward toward the inner boundary; and2) providing the flow from the second vane to effect a biasing of the exhaust flow radially outward toward the outer boundary. 17. The method of claim 15, wherein the vane comprises a first vane adjacent to the inner boundary, and including at least a second vane radially outward from the first vane and adjacent to the outer boundary, and receiving a flow of fluid from the source of compressed air flow along a further Coanda surface and including: providing the flow of fluid over the Coanda surfaces such that the exhaust flow at both the first and second vanes is biased in the same radial direction.
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이 특허에 인용된 특허 (6)
Shekleton Jack R. (San Diego CA), Coanda effect turbine nozzle vane cooling.
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