Airfoil assembly formed of high temperature-resistant material
An airfoil assembly includes an airfoil that has an exterior wall that defines an interior cavity. The exterior wall extends between a leading end and a trailing end and an open inboard end and an open outboard end. The exterior wall is formed of a high temperature-resistant material selected from refractory metal-based alloys, ceramic-based material or combinations thereof. A support frame extends in the interior cavity and protrudes from the interior cavity through at least one of the open inboard end and the open outboard end.
1. A gas turbine engine comprising:
a compressor section;
a combustor in fluid communication with the compressor section; and
a turbine section in fluid communication with the combustor, the turbine section including a vane assembly comprising an airfoil having an exterior wall defining an interior cavity, the exterior wall extending between a leading end and a trailing end and between an open inboard end and an open outboard end, the exterior wall being formed of a material selected from the group consisting of refractory metal-based alloys, ceramic-based material and combinations thereof, a support frame extending in the interior cavity and protruding from the interior cavity through at least one of the open inboard end and the open outboard end, and at least one spacer located between the airfoil and the support frame, the at least one spacer arranged between the open outboard end of the airfoil and a first flange of the support frame, and a spring member located between the open inboard end of the airfoil and a second flange of the support frame.
2. The gas turbine engine of claim 1 , further comprising first and second end wall platforms arranged, respectively, at the open inboard end and the open outboard end, wherein the exterior wall has a radial extent that extends past the first and second end wall platforms.