Split cast vane fairing

Abstract

A turbine exhaust case ( 28 ) comprises a frame ( 102 ) and a fairing ( 118 ). The frame has inner ( 106 ) and outer ( 104 ) rings connected by a plurality of radial struts ( 108 ). The fairing defines an airflow path within the frame, and has upstream ( 202 ) and downstream ( 204 ) sections connected together about the radial struts.

1 . A turbine exhaust case comprising:
 a frame having inner and outer rings connected by a plurality of radial struts; and   a fairing defining an airflow path within the frame, the fairing comprising upstream and downstream sections connected together about the radial struts.   
     
     
         2 . The turbine exhaust case of  claim 1 , wherein the upstream and downstream sections of the vane are welded together about the radial struts along a cut line. 
     
     
         3 . The turbine exhaust case of  claim 2 , wherein the cut line defines a radial plane of separation between the upstream and downstream sections. 
     
     
         4 . The turbine exhaust case of  claim 1 , wherein the fairing comprises radially inner and outer platforms connected by a vane body. 
     
     
         5 . The turbine exhaust case of  claim 4 , wherein the upstream and downstream sections are connected along a chord near a circumferentially thickest section of the vane body. 
     
     
         6 . The turbine exhaust case of  claim 5 , wherein the chord is located upstream of the circumferentially thickest section of the vane body. 
     
     
         7 . The turbine exhaust case of  claim 1 , wherein the fairing is comprised of a plurality of joined-together angular segments. 
     
     
         8 . The turbine exhaust case of  claim 1 , further comprising a radiative heat shield disposed between the frame and the fairing. 
     
     
         9 . A method for assembling a turbine exhaust case, the method comprising;
 casting a fairing with a vane body, an inner platform, and an outer platform in a single piece;   cutting the fairing into an upstream section and a downstream section along a cut line;   assembling the upstream and downstream sections about a turbine exhaust case frame; and   attaching the upstream section to the downstream section.   
     
     
         10 . The method of  claim 9 , wherein the cut line is situated at a chord location near the widest section of the vane body. 
     
     
         11 . The method of  claim 10 , wherein the fairing includes a sacrificial region to account for weld shrinkage and material removed while cutting the fairing into upstream and downstream sections. 
     
     
         12 . The method of  claim 10 , wherein the vane is cut using electric discharge machining. 
     
     
         13 . The method of  claim 10 , wherein attaching the upstream section to the downstream section comprises performing a weld long at the chord location. 
     
     
         14 . The method of  claim 13 , wherein the chord location is situated upstream of the widest section of the vane body. 
     
     
         15 . The method of  claim 13 , wherein the chord location is situated downstream of the widest section of the vane body. 
     
     
         16 . The method of  claim 13 , wherein the weld is a manual weld. 
     
     
         17 . The method of  claim 16 , wherein the manual weld is performed from forward of the fairing.