Convective cooling of gas turbine engine airfoil platforms is enhanced by grooving the interface of the platforms with corresponding platform-to-platform seals, thereby accelerating cooling airflow over the platform surfaces.
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1. A gas turbine engine comprising: a circumferential array of airfoils, each of said airfoils including a platform defining a radial boundary of a working fluid flow path, and wherein said airfoils comprise turbine blades with said platforms of adjacent turbine blades being spaced from each other b
1. A gas turbine engine comprising: a circumferential array of airfoils, each of said airfoils including a platform defining a radial boundary of a working fluid flow path, and wherein said airfoils comprise turbine blades with said platforms of adjacent turbine blades being spaced from each other by a gap;said platform including a first major surface exposed to a flow of working fluid and a second major surface defining at least in part, a cavity containing cooling air;the platforms of adjacent airfoils being engaged by a seal spanning said gap and which bears against said second major surfaces of said platforms across a first major surface of said seal and is exposed to said cooling air across a second major surface of said seal, and wherein said seal is defined by a length extending between first and second seal ends and is defined by a width extending between first and second longitudinal seal edges, and wherein said first and second seal ends are radially retained within said cavity;said second major surfaces of said platforms and said first major surface of said seal defining at least one cooling air passage therebetween which establishes a flow of said cooling air through said cooling air passage, thereby enhancing the convective cooling of said platform; andsaid cooling air passage comprising a plurality of grooves in one of said second major surface of said platform and said first major surface of said seal such that said cooling fluid enters said cooling air passage from an end thereof and traverses said passage between said seal and said platform and exhausts along said first major surface of said seal between said adjacent platforms, and wherein said seal includes at least one of a concave or convex portion formed along at least one of said longitudinal seal edges said at least one concave or convex portion spanning multiple grooves. 2. The gas turbine engine of claim 1 wherein said platforms and said seal define a plurality of cooling air passages therebetween, extending generally in the direction of rotation of said rotor, and wherein said platforms include fore and aft hooks that define fore and aft extremities of said cavity, and wherein said first and second seal ends are radially retained within said cavity by said fore and aft hooks during static conditions. 3. The gas turbine engine of claim 1 wherein said cooling air passage comprises a groove formed in said first major surface of said seal. 4. The gas turbine engine of claim 3 wherein said groove extends generally in the direction of rotation of said rotor. 5. The gas turbine engine of claim 1 wherein said airfoils comprise turbine blades and said at least one cooling air passage comprises a groove formed in the second major surface of at least one of said platforms. 6. The gas turbine engine of claim 5 wherein said seal comprises an elongate, plate having a longitudinal axis generally parallel to longitudinal axes of said platforms. 7. The gas turbine engine of claim 6 wherein said at least one cooling air passage comprises a plurality of grooves formed in said first major surface of said seal. 8. The gas turbine engine of claim 7 wherein said grooves are sealed by a surface-to-surface contact of said first major surface of said seal with said second major surface of said platform. 9. The gas turbine engine of claim 1 wherein said at least one cooling air passage comprises a plurality of grooves formed in said first major surface of said seal. 10. The gas turbine engine of claim 9 wherein said grooves extend generally in the direction of rotation of said rotor. 11. A feather seal for sealing a gap between the respective platforms of adjacent gas turbine engine components, said feather seal including at least one cooling air passage in a major surface thereof for enhanced cooling of said platforms, and said feather seal including at least one of a concave or convex portion formed along at least one longitudinal edge of said feather seal to accommodate suction and pressure surfaces, said at least one concave or convex portion formed separate of said cooling air passage. 12. The feather seal of claim 11 wherein said cooling air passage comprises an open groove in said major surface of said feather seal, said groove being adapted for closure by surface-to-surface contact with a major surface of said platform. 13. The feather seal of claim 11 wherein said feather seal comprises an elongate sheet having a pair of longitudinal edges and adapted to bridge juxtaposed edges of adjacent turbine platforms, and wherein said at least one cooling air passage comprises a plurality of grooves at least partially spanning said elongate sheet between said longitudinal edges thereof, and wherein said at least one concave or convex portion is formed to span multiple grooves. 14. The feather seal of claim 13, wherein said grooves extend generally in the direction of rotation of a gas turbine engine. 15. The feather seal of claim 11 wherein said feather seal is defined by a length extending between first and second ends and is defined by a width extending between first and second longitudinal edges, and wherein said first and second ends are configured to be radially retained within a plenum formed within a radially inner major surface of said platform. 16. A gas turbine engine including: at least one circular array of turbine airfoils, each of said turbine airfoils including an airfoil portion and a platform defining across a first major surface thereof, a boundary for the flow of working fluid past said airfoil portion;each of said platforms including an opposite, second major surface communicating with a reservoir of cooling air at a pressure higher than that of said working fluid; andsaid gas turbine engine including flow accelerators spanning said platforms of adjacent turbine airfoil blades, said flow accelerators reducing the volume of said cooling air applied to said second major surface of said platform to accelerate the flow thereof, thereby enhancing the convection cooling of said platform by said cooling air, and wherein each flow accelerator comprises a seal defined by a length extending between first and second seal ends and defined by a width extending between first and second longitudinal seal edges, and wherein at least one of said seals and said second major surfaces of said platforms define passages fed by said reservoir of cooling air, and wherein said seal includes at least one of a concave or convex portion formed along at least one of said longitudinal seal edges, said at least one concave or convex portion spanning multiple passages. 17. The gas turbine engine of claim 16, wherein said seals span adjacent blade platforms along said second major surfaces thereof, and wherein said each platform includes fore and aft hooks that define fore and aft extremities of said reservoir of cooling air, and wherein said first and second seal ends are radially retained within said reservoir by said fore and aft hooks during static conditions. 18. The gas turbine engine of claim 17 wherein said adjacent blade platforms are spaced apart by a gap, said seals spanning said gap and said passages discharging said cooling air into said working fluid at outlets of said passages in fluid communication with said gap. 19. The gas turbine engine of claim 18 wherein said passages comprise open grooves formed in the second major surfaces of said platforms, said grooves being at least partially closed by surface-to-surface contact between said grooves and a major surface of said seal. 20. The gas turbine engine of claim 18 wherein said passages comprise grooves formed in major surfaces of said seals, said grooves being at least partially closed by surface-to-surface contact between said grooves and said second major surfaces of said platforms. 21. The gas turbine engine of claim 20, wherein said grooves are formed in a radially outer surface of said seal and said second major surface of said platform comprises a radially inner major surface thereof. 22. The gas turbine engine of claim 21 wherein said grooves in said radially outer major surface of said seal are open along those portions thereof between said adjacent turbine airfoil blade platforms in said gap. 23. A turbine blade comprising: an airfoil portion;a platform having a radially outer major surface facing said airfoil portion and a radially inner major surface defining a plenum;a seal having first and second seal ends that are radially retained within said plenum, and wherein said seal is defined by a length extending between said first and second seal ends and by a width extending between first and second longitudinal seal edges, and wherein said seal includes at least one of a convex or concave portion formed along at least one of said longitudinal seal edges; andwherein at least one of said seal and said radially inner major surface define cooling passages therein to cool said platform, said at least one of said convex or concave portion of said seal spanning multiple cooling passages. 24. The turbine blade of claim 23 wherein said platform includes fore and aft hooks that define fore and aft extremities of said plenum, and wherein said first and second seal ends are radially retained within said cavity by said fore and aft hooks during static conditions.
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이 특허에 인용된 특허 (17)
Kelch George W. (Palm Beach Gardens FL) Auxier Thomas A. (Palm Beach Gardens FL), Blade outer air seal cooling enhanced with inter-segment film slot.
Serge Louis Antunes FR; Eric Stephan Bil FR; Isabelle Monique Marie Bourriaud FR; Maurice Guy Judet FR, System for ventilating a pair of juxtaposed vane platforms.
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