Joint between airfoil and shroud
First Claim
Patent Images
1. A vane and shroud for a gas turbine engine having a center axis, comprising:
- a shroud having a radial wall facing substantially radially with respect to the center axis, a slot wall defining a slot in the shroud, a relief wall defining a relief area of the slot and wherein the relief wall extends between the radial wall and the slot wall;
a vane having an airfoil and a lug extending into the slot;
a flowable attachment material disposed in the relief area for engagement of the vane to the shroud;
said lug merges into a transition section which curves circumferentially inwardly from said lug to said airfoil; and
said radial wall is generally radially aligned with a radial extent of said transition section which is most adjacent to said radial wall.
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Accused Products
Abstract
A stator joint for a gas turbine engine has a center axis, and a shroud having a radial wall facing substantially radially with respect to the center axis. A slot wall defines in-part a slot in the shroud. A relief wall defines a relief area of the slot. The relief wall extends between the radial wall and the slot wall. A vane has an airfoil and a lug extending into the slot. A flowable attachment material is disposed in the relief area for engagement of the vane to the shroud. A vane assembly and a gas turbine engine are also disclosed.
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Citations
21 Claims
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1. A vane and shroud for a gas turbine engine having a center axis, comprising:
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a shroud having a radial wall facing substantially radially with respect to the center axis, a slot wall defining a slot in the shroud, a relief wall defining a relief area of the slot and wherein the relief wall extends between the radial wall and the slot wall; a vane having an airfoil and a lug extending into the slot; a flowable attachment material disposed in the relief area for engagement of the vane to the shroud; said lug merges into a transition section which curves circumferentially inwardly from said lug to said airfoil; and said radial wall is generally radially aligned with a radial extent of said transition section which is most adjacent to said radial wall. - View Dependent Claims (2, 3, 4, 5)
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6. A vane and shroud for a gas turbine engine having a center axis, comprising:
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a shroud having a radial wall facing substantially radially with respect to the center axis, a slot wall defining a slot in the shroud, a relief wall defining a relief area of the slot and wherein the relief wall extends between the radial wall and the slot wall; a vane having an airfoil and a lug extending into the slot; a flowable attachment material disposed in the relief area for engagement of the vane to the shroud; and a depth of the relief wall is defined to a point most radially distant from a surface of said radial wall facing said center axis, and a radial wall thickness is defined for said shroud adjacent to said relief area, and a ratio of said depth to said radial wall thickness being between about 0.2 and 0.6. - View Dependent Claims (7, 8)
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9. A vane assembly for use in a gas turbine engine comprising:
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a circumferentially extending outer shroud and a circumferentially extending inner shroud centered on a center axis, and a plurality of vanes positioned radially between said inner and outer shrouds, a joint between said vanes and at least one of said inner and outer shrouds, said at least one said shroud having a radial wall facing substantially radially with respect to the center axis, a plurality of slots in said at least one said shroud, slot walls defining said slots in said at least one said shroud, a relief wall defining a relief area of said slots and wherein the relief wall extends between the radial wall and the slot wall; said vanes having an airfoil and a lug extending into one of the slots; a flowable attachment material disposed in the relief area for engagement of the vane to at least one of the inner and outer shrouds; said jug merging into a transition section which curves circumferentially from said lug to said airfoil; and said radial wall being generally radially aligned with a radial extent of said transition section which is most adjacent to said radial wall. - View Dependent Claims (10, 11, 12, 13, 14)
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15. A vane assembly for sue in a gas turbine engine comprising:
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a circumferentially extending outer shroud and a circumferentially extending inner shroud centered on a center axis, and a plurality of vanes positioned radially between said inner and outer shrouds, a joint between said vanes and at least one of said inner and outer shrouds, said at least one said shroud having a radial wall facing substantially radially with respect to the center axis, a plurality of slots in said at least one said shroud, slot walls defining said slots in said at least one said shroud, a relief wall defining a relief area of said slots and wherein the relief wall extends between the radial wall and the slow wall; said vanes having an airfoil and a lug extending into one of the slots; a flowable attachment material disposed in the relief area for engagement of the vane to at least one of the inner and outer shrouds; and a depth of the relief area is defined to a point most radially distant from a surface of said radial wall facing said center axis, and a radial wall thickness is defined for said shroud adjacent to said relief area, and a ratio of said depth to said radial wall thickness being between about 0.2 and 0.6. - View Dependent Claims (16, 17)
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18. A gas turbine engine comprising:
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a compressor section, a combustor section and a turbine section, with said compressor section and said turbine section being defined by a plurality of rotor stages and a plurality of vane assemblies positioned between adjacent ones of said rotor stages; at least one of said vane assemblies having a circumferentially extending outer shroud and a circumferentially extending inner shroud centered on a center axis, and a plurality of vanes positioned radially between said inner and outer shrouds, a joint between said vanes and at least one of said inner and outer shrouds such that said at least one said shroud having a radial wall facing substantially radially with respect to the center axis, a plurality of slots in said at least one said shroud, slot walls defining said slots in said at least one said shroud, a relief wall defining a relief area of said slots and wherein the relief wall extends between the radial wall and the slot wall; said vanes having an airfoil and a lug extending into one of the slots; a flowable attachment material disposed in the relief area for engagement of the vane to at least one of the inner and outer shrouds; and a depth of the relief area is defined to a point most radially distant from a surface of said radial wall facing said center axis, and a radial wall thickness is defined for said shroud adjacent to said relief area, and a ratio of said depth to said radial wall thickness being between about 0.2 and 0.6. - View Dependent Claims (19, 20, 21)
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Specification