Gas turbine stator vane assembly
AssigneeUnited Technologies Corporation
InventorsDavid E. Heumann, M. Stefan Maier
Life of this patent
Estimating the term…
Abstract
A stator vane assembly for a gas turbine engine includes a plurality of stator vane segments and fasteners. Each stator vane segment includes an inner radial platform, an outer radial platform, at least one airfoil extending between said platforms, and a first mounting flange extending radially outward from said outer radial platform. Each first mounting flange is aligned with a second mounting flange extending radially inward from an outer case surrounding the stator vane assembly. Each fastener includes a bolt extending through the first and second mounting flanges, a nut for threaded engagement with the bolt, and apparatus for preventing vibration of the fasteners.
Claims4
A stator vane assembly for a gas turbine engine, comprising:
- a plurality of stator vane segments, each segment having an inner radial platform, an outer radial platform, at least one airfoil extending between said platforms, and a first mounting flange extending radially outward from said outer radial platform, said stator vane segments collectively forming an annular structure;
- wherein each said first mounting flange is aligned with a second mounting flange extending radially inward from an outer case surrounding said stator vane assembly;
- a plurality of fasteners, each said fastener including a bolt extending through said first and second mounting flanges, a nut for threaded engagement with said bolt, a flanged sleeve, and a cam sleeve having an eccentric axial bore;
- wherein each said bolt is received within said flanged sleeve and said flanged sleeve is received within said first mounting flange, and said cam sleeve is received on said bolt;
- and
- wherein a third mounting flange extends radially upward from an annular combustor;
- and said cam sleeve is received within an aperture within said third mounting flange, and said cam sleeve and said flanged sleeve are on opposite sides of said second mounting flange;
- and
- wherein threading said nut onto said bolt causes said cam sleeve and said flanged sleeve to clamp said second mounting flange.
A stator vane assembly for a gas turbine engine, comprising:
- a plurality of stator vane segments, each segment having an inner radial platform, an outer radial platform, at least one airfoil extending between said platforms, and a first mounting flange extending radially outward from said outer radial platform, said stator vane segments collectively forming an annular structure;
- wherein each said first mounting flange is aligned with a second mounting flange extending radially inward from an outer case surrounding said stator vane assembly;
- a plurality of fasteners, each said fastener including a split sleeve having an axially extending break and tapered axial ends, a bolt having a head and a first tapered surface adjacent said head, and a nut for threaded engagement with said bolt, wherein each said bolt is received within said split sleeve and said split sleeve is received within said first and second mounting flanges;
- a cam sleeve, having an eccentric axial bore for receiving said bolt and a second tapered surface, extending out from an axial end of said cam sleeve;
- wherein said first and second tapered surfaces are substantially complimentary with said tapered axial ends of said split sleeve;
- and
- wherein threading said nut onto said bolt causes said first and second tapered surfaces to engage said tapered axial ends and expand said split sleeve into contact with said first and second mounting flanges;
- and
- wherein a third mounting flange extends radially upward from an annular combustor, and said bolt and said cam sleeve are received within an aperture within said third mounting flange.
Dependencies are inferred from the claim text.