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One embodiment of the present invention is a vane assembly for a gas turbine engine. Another embodiment of the present invention is a damper seal that may be employed in conjunction with a vane assembly of a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, metho

One embodiment of the present invention is a vane assembly for a gas turbine engine. Another embodiment of the present invention is a damper seal that may be employed in conjunction with a vane assembly of a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods and combinations for vane assemblies and the sealing and damping thereof. Further embodiments, forms, features, aspects, benefits and advantages of the present application shall become apparent from the description and figures provided herewith.

대표청구항 ▼

1. A vane assembly for a gas turbine engine, comprising: an outer band;an inner band, wherein said inner band is subdivided into a plurality of circumferential segments;a plurality of airfoils spaced apart circumferentially and extending between said outer band and said inner band, wherein each airf

1. A vane assembly for a gas turbine engine, comprising: an outer band;an inner band, wherein said inner band is subdivided into a plurality of circumferential segments;a plurality of airfoils spaced apart circumferentially and extending between said outer band and said inner band, wherein each airfoil has a tip end and a root end; and wherein each airfoil is coupled to said outer band at said tip end and coupled to a respective segment of said inner band at said root end; anda damper seal, including:a friction damper portion extending along said inner band in a circumferential direction, wherein said friction damper portion is in contact with at least two circumferential segments of said plurality of circumferential segments and is structured to provide friction damping of said at least two circumferential segments based on said contact; andan integral air seal portion extending from said friction damper portion and having a compressible end face seal structured to extend outward of and away from said at least two circumferential segments in an axial direction substantially perpendicular to the circumferential direction toward an engine component that is spaced apart from said vane assembly in the axial direction, said air seal portion being structured as a face seal to seal against an axial face of the engine component that is spaced apart from said vane assembly in the axial direction. 2. The vane assembly of claim 1, wherein said air seal portion is integral with said friction damper portion. 3. The vane assembly of claim 1, wherein said friction damper portion is a continuous strip extending circumferentially along said inner band. 4. The vane assembly of claim 3, wherein said friction damper portion is structured to contact each circumferential segment of said plurality of circumferential segments. 5. The vane assembly of claim 4, wherein said inner band is split between each airfoil, and wherein each segment extends from a single airfoil. 6. The vane assembly of claim 3, wherein said air seal portion is structured as a bellows. 7. The vane assembly of claim 6, wherein said air seal portion includes at least two convolutions extending in the axial direction. 8. The vane assembly of claim 1, wherein said vane assembly is a compressor vane assembly. 9. The vane assembly of claim 8, wherein said engine component is a diffuser located downstream of a compressor of the gas turbine engine. 10. The vane assembly of claim 1, wherein said outer band defines an outer flowpath wall and wherein said inner band defines an inner flowpath wall. 11. The vane assembly of claim 1, wherein said friction damper portion and said air seal portion are formed from sheet metal. 12. The vane assembly of claim 1, wherein said damper seal is at least one of bolted and pinned to said inner band. 13. A damper seal for a vane assembly of a gas turbine engine, comprising: a friction damper portion having a surface structured to contact a plurality of segments of said vane assembly to provide friction damping of said plurality of segments; andan air seal portion having a compressible end face seal structured to extend axially outward of and axially away from said plurality of segments toward a gas turbine engine component that is spaced apart from said plurality of segments in an axial direction, wherein said compressible end face seal is structured to seal against an axial face of the gas turbine engine component,wherein said air seal portion is integral with said friction damper portion. 14. The damper seal of claim 13, wherein said friction damper portion and said air seal portion are formed as a continuous ring. 15. The damper seal of claim 13, wherein said damper seal is formed from sheet metal. 16. The damper seal of claim 15, wherein said air seal portion is compressible in the axial direction. 17. The damper seal of claim 13, wherein said air seal portion is structured as a bellows. 18. The damper seal of claim 17, wherein said air seal portion includes at least two convolutions extending in the axial direction. 19. The damper seal of claim 13, wherein said surface extends in the axial direction. 20. A gas turbine engine, comprising: a vane assembly having a plurality of segments; anda damper seal for said vane assembly, wherein said damper seal includes:means for providing friction damping of at least some of said plurality of segments of said vane assembly; andmeans for sealing against a face of a gas turbine engine component that is spaced apart from said plurality of segments in an axial direction,wherein said means for sealing is integral with said means for providing friction damping; andwherein said means for sealing is axially compressible and extends axially outward of and away from said plurality of vane segments and toward the gas turbine engine component.