Turbine Vane With Platform Rib
A vane for use in a gas turbine engine has an airfoil extending between a leading edge and a trailing edge, a radially outer platform and a radially inner platform. A rib is on one of the radially inner and radially outer platforms, and is adjacent the trailing edge of the airfoil. A mid-turbine frame is also disclosed.
1 . A vane for use in a gas turbine engine comprising:
an airfoil extending between a leading edge and a trailing edge;
a radially outer platform and a radially inner platform; and
a rib on one of said radially inner and radially outer platforms, and said rib being adjacent said trailing edge of said airfoil.
2 . The vane as set forth in claim 1 , wherein said at least one platform is said radially outer platform.
3 . The vane as set forth in claim 2 , wherein said rib is on an outer surface of said outer platform and spaced beyond said trailing edge relative to said leading edge.
4 . The vane as set forth in claim 3 , wherein said airfoil has a trailing edge at an inner surface of said outer platform, and said rib is aligned with a fillet merging into said trailing edge at said inner surface.
5 . The vane as set forth in claim 1 , wherein said rib having a height extending radially outwardly that is greater than surrounding nominal wall portions.
6 . The vane as set forth in claim 5 , wherein said height of said rib is defined from an inner surface of said outer platform to a radially outermost face of said rib, and said nominal wall thickness of said outer platform is defined between said inner surface and an outer surface of said outer platform, and a ratio of said nominal wall thickness to said height is between 1.1 and 6.0.
7 . The vane as set forth in claim 6 , wherein a width of said rib is defined in a direction between said leading edge and said trailing edge, and a ratio of said nominal wall thickness to said width is between 1.1 and 6.0.
8 . The vane as set forth in claim 2 , wherein a width of said rib is defined in a direction between said leading edge and said trailing edge, and a nominal wall thickness of the inner and outer surfaces of said outer platform is defined, and a ratio of said nominal wall thickness to said width is between 1.1 and 6.0.
9 . The vane as set forth in claim 2 , wherein said rib is circumferentially continuous, and passes across a plurality of said airfoils.
10 . The vane as set forth in claim 2 , wherein said rib is circumferentially discontinuous, and there are gaps between rib portions.
11 . The vane as set forth in claim 1 , wherein said vane is a turbine vane.
12 . A mid-turbine frame comprising:
a radially inner and a radially outer platform;
airfoils extending between a leading edge and a trailing edge, and being generally hollow; and
a rib on one of said radially inner and radially outer platforms, and said rib being adjacent said trailing edge of said airfoil.
13 . The frame as set forth in claim 12 , wherein said at least one platform is said radially outer platform.
14 . The frame as set forth in claim 13 , wherein said rib is on an outer surface of said outer platform and spaced beyond said trailing edge relative to said leading edge.
15 . The frame as set forth in claim 14 , wherein said airfoil has a trailing edge at an inner surface of said outer platform, and said rib is aligned with a fillet merging into said trailing edge at said inner surface.
16 . The frame as set forth in claim 12 , wherein said rib having a height extending radially outwardly that is greater than surrounding nominal wall portions.
17 . The frame as set forth in claim 16 , wherein said height of said rib is defined from an inner surface of said outer platform to a radially outermost face of said rib, and a nominal wall thickness of said outer platform is defined between said inner surface and an outer surface of said outer platform, and a ratio of said nominal wall thickness to said height is between 1.1 and 6.0.
18 . The frame as set forth in claim 17 , wherein a width of said rib is defined in a direction between said leading edge and said trailing edge, and a ratio of said nominal wall thickness to said width is between 1.1 and 6.0.
19 . The frame as set forth in claim 12 , wherein said rib is circumferentially continuous, and passes across a plurality of said airfoils.
20 . The frame as set forth in claim 12 , wherein said rib is circumferentially discontinuous, and there are gaps between rib portions.