Turbine vane with non-uniform wall thickness
First Claim
Patent Images
1. A vane for use in a gas turbine engine comprising:
- an airfoil extending between a leading edge and a trailing edge, and being generally hollow;
a radially outer platform and a radially inner platform;
with a radially inner face of said radially inner platform having thicker portions circumferentially located beyond one of said leading edge and said trailing edge, and thinner portions circumferentially beyond circumferential edges of said airfoil;
said thicker portions are at a location where said airfoil merges into said platform;
wherein said thicker portions are provided by a least one thicker bump positioned axially beyond said leading edge, but circumferentially aligned with said airfoil; and
wherein said one of said leading edge and said trailing edge is said leading edge.
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Abstract
A vane for use in a gas turbine engine has an airfoil extending between a leading edge and a trailing edge, and is generally hollow. The vane has a radially outer platform and a radially inner platform. At least one of the radially inner and radially outer platforms has thicker portions circumferentially located beyond one of the leading edge and the trailing edge, and thinner portions circumferentially beyond circumferential edges of the airfoil. A mid-turbine frame and a gas turbine engine are also disclosed.
23 Citations
8 Claims
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1. A vane for use in a gas turbine engine comprising:
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an airfoil extending between a leading edge and a trailing edge, and being generally hollow; a radially outer platform and a radially inner platform; with a radially inner face of said radially inner platform having thicker portions circumferentially located beyond one of said leading edge and said trailing edge, and thinner portions circumferentially beyond circumferential edges of said airfoil; said thicker portions are at a location where said airfoil merges into said platform; wherein said thicker portions are provided by a least one thicker bump positioned axially beyond said leading edge, but circumferentially aligned with said airfoil; and wherein said one of said leading edge and said trailing edge is said leading edge. - View Dependent Claims (2, 3)
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4. A mid-turbine frame comprising:
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a plurality of vanes having airfoils extending between a radially inner and a radially outer platform; said airfoil shape extending between a leading edge and a trailing edge, and being generally hollow; and with a radially inner face of said radially inner platform having thicker portions circumferentially located beyond said leading edge, and thinner portions circumferentially beyond circumferential edges of said airfoil, said thicker portions are at a location where said airfoil merges into said platform; and wherein said thicker portions are provided by at least one thicker bump positioned axially beyond said leading edge, but circumferentially aligned with said airfoil. - View Dependent Claims (5, 6)
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7. A gas turbine engine comprising:
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at least a first upstream turbine rotor and a downstream turbine rotor, with a mid-turbine frame located intermediate said upstream and downstream turbine rotors; the mid-turbine frame including a plurality of vanes having a radially outer platform and a radially inner platform, and an airfoil extending between a leading edge and a trailing edge, and being generally hollow; and a radially inner face of said radially inner platform having thicker portions circumferentially located beyond said leading edge, and thinner portions circumferentially beyond circumferential edges of said airfoil, said thicker portions are at a location where said airfoil merges into said platform; and wherein said thicker portions are provided by at least one thicker bump positioned axially beyond said leading edge, but circumferentially aligned with said airfoil. - View Dependent Claims (8)
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Specification