TITANIUM ALUMINIDE TURBINE EXHAUST STRUCTURE
A turbine exhaust case for a gas turbine engine includes a multiple of CMC turbine exhaust case struts between a CMC core nacelle aft portion and a CMC tail cone.
1 . A turbine exhaust case for a gas turbine engine comprising:
a CMC core nacelle aft portion;
a CMC tail cone; and
a multiple of CMC turbine exhaust case struts between said CMC core nacelle aft portion and said CMC tail cone.
2 . The turbine exhaust case as recited in claim 1 , wherein said CMC core nacelle aft portion defines a trailing edge of a core nacelle
3 . The turbine exhaust case as recited in claim 1 , wherein said CMC core nacelle aft portion defines a portion of an outer aerodynamic surface to provide essentially uninterrupted flow along a core nacelle
4 . A gas turbine engine comprising:
a turbine case; and
a CMC turbine exhaust case mounted to said turbine case.
5 . The gas turbine engine as recited in claim 4 , wherein said turbine case is a low pressure turbine case.
6 . The gas turbine engine as recited in claim 4 , wherein said turbine case is manufactured of CMC.
7 . The gas turbine engine as recited in claim 4 , wherein said CMC turbine exhaust case comprises:
a CMC core nacelle aft portion;
a CMC tail cone; and
a multiple of CMC turbine exhaust case struts between said CMC core nacelle aft portion and said CMC tail cone.
8 . The gas turbine engine as recited in claim 4 , wherein said CMC turbine exhaust case is mounted to said turbine case at a flange.
9 . The gas turbine engine as recited in claim 4 , wherein said multiple of CMC turbine exhaust case struts are bonded between said CMC core nacelle aft portion and said CMC tail cone.
10 . A method of assembling a gas turbine engine comprising:
mounting a CMC turbine exhaust case to a turbine case.
11 . The method as recited in claim 10 , further comprising:
bolting the CMC turbine exhaust case to the turbine case.
12 . The method as recited in claim 10 , further comprising:
defining at least a portion of a core nacelle with the CMC turbine exhaust case.
13 . The method as recited in claim 10 , further comprising:
defining at least a portion of an aerodynamic outer surface of a core nacelle with the CMC turbine exhaust case.
14 . The method as recited in claim 10 , further comprising:
defining a trailing edge of a core nacelle with the CMC turbine exhaust case.