Segmented compressor inner band for variable vanes in gas turbine engines
US-2024280032-A1 · Aug 22, 2024 · US
US9062560B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9062560-B2 |
| Application number | US-201213418451-A |
| Country | US |
| Kind code | B2 |
| Filing date | Mar 13, 2012 |
| Priority date | Mar 13, 2012 |
| Publication date | Jun 23, 2015 |
| Grant date | Jun 23, 2015 |
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A variable stator vane assembly for a gas turbine engine includes a variable stator vane and a non-structural fairing on the variable stator vane.
Opening claim text (preview).
What is claimed: 1. A variable stator vane assembly for a gas turbine engine comprising: a variable stator vane including a platform adjacent to an airfoil, said airfoil comprises a leading edge and a trailing edge extending beyond an outer circumference of said platform; a fillet adjacent said platform, said platform includes a flat and said fillet extends from said trailing edge to said flat; and a fairing covering said fillet, wherein said fairing comprises a generally cylindrical member with an airfoil shaped aperture and a tab, said tab configured to interface with said flat. 2. The assembly as recited in claim 1 , wherein said fairing surrounds said airfoil. 3. The assembly as recited in claim 1 , further comprising a trunnion which extends from said platform. 4. The assembly as recited in claim 3 , wherein said fairing surrounds said airfoil opposite said trunnion. 5. The assembly as recited in claim 1 , wherein said airfoil extends beyond said platform. 6. The assembly as recited in claim 1 , further comprising a metal alloy sheath on said fairing. 7. A variable stator vane assembly for a gas turbine engine comprising: a first platform, said first platform includes a flat; a second platform; an airfoil between said first platform and said second platform along an axis of rotation, said airfoil comprises a leading edge and a trailing edge extending beyond an outer circumference of said first platform; a fillet adjacent said first platform, said fillet extends from said trailing edge to said flat; and a fairing which surrounds said airfoil adjacent to said first platform and covers said fillet, wherein said fairing comprises a generally cylindrical member with an airfoil shaped aperture and a tab, said tab configured to interface with said flat. 8. The assembly as recited in claim 7 , further comprising a first trunnion which extends from said first platform and a second trunnion which extends from said second platform. 9. The assembly as recited in claim 7 , wherein said airfoil extends beyond said first and second platform. 10. The assembly as recited in claim 7 , further comprising a metal alloy sheath on said fairing. 11. A method of manufacturing a variable stator vane assembly for a gas turbine engine comprising: molding a fairing onto a fillet of a variable stator vane; wherein said fairing comprises a generally cylindrical member with an airfoil shaped aperture and a tab, said tab configured to interface with a flat of an airfoil platform. 12. The method as recited in claim 11 , further comprising: molding the fairing adjacent to a platform of the variable stator vane. 13. The method as recited in claim 11 , further comprising: sheathing one side of the fairing. 14. The assembly as recited in claim 1 , wherein said fairing comprises: a non-metallic material configured to be formed onto said variable stator vane. 15. The assembly as recited in claim 1 , wherein said fairing is configured to prevent said fillet from blocking fluid flow.
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