Ceramic composite vane with metallic substructure

A vane assembly for a turbine assembly comprising:

• an inner endcap;
• an outer endcap;
• a body:
• said body comprises:
• a metallic core assembly which is coupled to said inner endcap and said outer endcap;
• a ceramic shell assembly;
• a support assembly coupled to said metallic core assembly;
• and
• said support assembly being a layer of a compliant material, wherein said compliant material includes a plurality of cooling passages therethrough being in fluid communication with said ceramic shell assembly.

A turbine comprising:

• a casing;
• a cooling system;
• and
• a plurality of vane assemblies comprising:
• an inner endcap;
• an outer endcap;
• a body:
• said body comprises:
• a metallic core assembly which is coupled to said inner endcap and said outer endcap;
• a ceramic shell assembly;
• a support assembly coupled to said metallic core assembly;
• and
• said support assembly being disposed between said metallic core assembly and said ceramic shell assembly and adapted to transmit substantially all aerodynamic loads from said shell assembly to said core assembly during operation.

A turbine comprising:

• a casing;
• a cooling system;
• and
• a plurality of vane assemblies comprising:
• an inner endcap;
• an outer endcap;
• a body:
• said body comprises:
• a metallic core assembly which is coupled to said inner endcap and said outer endcap;
• a ceramic shell assembly;
• a support assembly coupled to said metallic core assembly;
• and
• said support assembly disposed between said metallic core assembly and said ceramic shell assembly, wherein said support assembly is a layer of a compliant material, wherein said compliant material includes a plurality of cooling passages therethrough being in fluid communication with said ceramic shell assembly.

A turbine assembly comprising:

• a casing;
• a cooling system;
• and
• a plurality of vane assemblies comprising:
• an inner endcap;
• an outer endcap;
• a body:
• said body comprises:
• a metallic core assembly which is coupled to said inner endcap and said outer endcap;
• a ceramic shell assembly;
• a support assembly coupled to said ceramic shell assembly;
• said support assembly being disposed between said metallic core assembly and said ceramic shell assembly and adapted to transmit substantially all aerodynamic loads from said shell assembly to said core assembly during operation;
• and
• said support assembly comprises a plurality of hard contact points.