초록 ▼

One embodiment of the present invention is a gas turbine engine. Another embodiment is a gas turbine engine vane system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engine vanes. Further embodiments, forms, features, aspects, benefits,

One embodiment of the present invention is a gas turbine engine. Another embodiment is a gas turbine engine vane system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engine vanes. 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 segment for a gas turbine engine, comprising: an outer shroud;an inner shroud;a composite airfoil having a span slidably disposed between said outer shroud and said inner shroud, the entirety of the span being configured to move in a flowpath direction, the airfoil being configured at its

1. A vane segment for a gas turbine engine, comprising: an outer shroud;an inner shroud;a composite airfoil having a span slidably disposed between said outer shroud and said inner shroud, the entirety of the span being configured to move in a flowpath direction, the airfoil being configured at its ends to slide against said outer shroud and inner shroud from a first position to a second position, said airfoil having a passage extending between said outer shroud and said inner shroud; anda spoke extending through said passage between said outer shroud and said inner shroud, wherein said airfoil is moveable in the flowpath direction from the first position to the second position, and in the second position the spoke is operative to limit the movement of said airfoil. 2. The vane segment of claim 1, wherein in the second position said airfoil is structured to transfer aerodynamic loads from said airfoil to the inner and outer shroud through said spoke. 3. The vane segment of claim 1, wherein said spoke is pre-stressed at room temperature conditions with a tensile preload. 4. The vane segment of claim 1, wherein said spoke is a metal wire. 5. The vane segment of claim 1, wherein said vane segment is structured to transfer loads from said inner shroud to said outer shroud via said spoke. 6. The vane segment of claim 1, wherein said spoke is affixed to said inner shroud and to said outer shroud. 7. The vane segment of claim 1, further comprising a tube disposed in said passage, wherein said spoke extends through said tube. 8. The vane segment of claim 7, further comprising a compliant pad structured to transfer aerodynamic loads from said airfoil to said tube, and wherein said tube is structured to transfer said aerodynamic loads to said spoke. 9. The vane segment of claim 1, further comprising a second spoke extending through said passage and between said outer shroud and said inner shroud. 10. The vane segment of claim 1, further comprising a bushing disposed on said spoke and structured to transmit aerodynamic loads to said spoke. 11. A gas turbine engine, comprising: a compressor;a turbine; anda vane stage having an inner ring, an outer ring, a plurality of airfoils having a span and slidably disposed between said inner ring and said outer ring, the entirety of the span being configured to move in a flowpath direction, the airfoils being configured at their ends to slide against said inner ring and outer ring from a first position to a second position, and a plurality of spokes extending between said inner ring and said outer ring through said plurality of airfoils, wherein said plurality of spokes interconnects said inner ring and said outer ring in a hub-and-spoke. 12. The gas turbine engine of claim 11, further comprising a vane case structure, wherein said outer ring is supported by said vane case structure. 13. The gas turbine engine of claim 12, wherein each of said spokes are coupled to said inner ring and to said outer ring, and wherein said vane stage is structured to transfer loads from said inner ring to said vane case structure via said spokes and said outer ring. 14. The gas turbine engine of claim 11, wherein said outer ring is formed of a plurality of vane segment outer shrouds. 15. The gas turbine engine of claim 11, wherein said inner ring is formed of a plurality of individual vane segment inner shrouds. 16. The gas turbine engine of claim 11, further comprising an engine component supported by said inner ring, wherein said vane stage is structured to transfer loads from said engine component via said inner ring and said spokes to said outer ring. 17. The gas turbine engine of claim 11, wherein said plurality of airfoils are movable in the flowpath direction relative to the spokes and in the second position are structured to transfer aerodynamic loads imposed on said plurality of airfoils to said spokes. 18. A gas turbine engine, comprising: at least one of a fan, a compressor and a turbine, wherein at least one of said fan, said compressor and said turbine includes a vane stage, said vane stage including:an inner ring;an outer ring;a plurality of airfoils having a span and slidably disposed between said inner ring and said outer ring, the entirety of the span being configured to move in a flowpath direction, the airfoils being configured at their ends to slide against said inner ring and outer ring from a first position to a second position; anda plurality of spokes for transferring loads from said inner ring to said outer ring,wherein each one of said spokes is located between said inner ring and said outer ring and extends through a passage in one of said plurality of airfoils;wherein said plurality of airfoils are moveable in the flowpath direction from the first position to the second position, and in the second position the plurality of spokes are operative to limit the movement of the airfoils. 19. The gas turbine engine of claim 18, wherein said plurality of spokes are operable in the second position for transferring loads from said inner ring to said outer ring and for transferring aerodynamic loads from said plurality of airfoils to said outer ring. 20. The gas turbine engine of claim 18, wherein said plurality of airfoils are composite airfoils.