Turbine vane with non-uniform wall thickness
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.
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.
2. The vane as set forth in claim 1 , wherein there are at least a plurality of said bumps.
3. The vane as set forth in claim 2 , wherein a radial thickness of a thickest portion of said bump is defined, and a ratio of said radial thickness of said thickest portion of said bump to a radially thickness of portions circumferentially spaced from said bump is equal to or between 1.1 and 5.0.
4. A mid-turbine frame comprising:
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.
5. The mid-turbine frame vane as set forth in claim 4 , wherein a radial thickness of a thickest portion of said bump is defined, and a ratio of said radial thickness of said thickest portion of said bump to a radially thickness of portions circumferentially spaced from said bump is equal to or between 1.1 and 5.0.
6. The mid-turbine frame as set forth in claim 4 , wherein there are at least a plurality of said bumps.
7. A gas turbine engine comprising:
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.
8. The gas turbine engine as set forth in claim 7 , wherein a radial thickness of a thickest portion of said bump is defined, and a ratio of said radial thickness of said thickest portion of said bump to a radially thickness of portions circumferentially spaced from said bump is equal to or between 1.1 and 5.0.