Airfoil for turbine system

Abstract

An airfoil for a turbine system is disclosed. The airfoil includes a first body having exterior surfaces defining a first portion of an aerodynamic contour of the airfoil and formed from a first material. The airfoil further includes a second body having exterior surfaces defining a second portion of an aerodynamic contour of the airfoil, the second body coupled to the first body and formed from a second material having a different temperature capability than the first material.

What is claimed is: 
     
         1 . An airfoil for a turbine system, the airfoil comprising:
 a first body having exterior surfaces defining a first portion of an aerodynamic contour of the airfoil and formed from a first material; and   a second body having exterior surfaces defining a second portion of an aerodynamic contour of the airfoil, the second body coupled to the first body and formed from a second material having a different temperature capability than the first material.   
     
     
         2 . The airfoil of  claim 1 , wherein the second material is a ceramic matrix composite. 
     
     
         3 . The airfoil of  claim 1 , wherein the exterior surfaces of the first body at least partially define a pressure side and a suction side and further define a leading edge, and wherein the exterior surfaces of the second body define a trailing edge. 
     
     
         4 . The airfoil of  claim 1 , wherein the second body is continuous throughout a cross-sectional profile. 
     
     
         5 . The airfoil of  claim 1 , wherein the second body comprises a plurality of second body sections, each of the second body sections formed from a second material. 
     
     
         6 . The airfoil of  claim 1 , wherein one of the first body or the second body defines a recess and the other of the first body or the second body comprises a protrusion, and wherein engagement of the protrusion in the recess couples the second body to the first body. 
     
     
         7 . The airfoil of  claim 1 , further comprising an end cap coupling the second body to the first body. 
     
     
         8 . The airfoil of  claim 1 , wherein the first body defines a cooling passage. 
     
     
         9 . A nozzle for a turbine section of a turbine system, the nozzle comprising:
 an airfoil having exterior surfaces defining an aerodynamic contour, the aerodynamic contour comprising a pressure side and a suction side extending between a leading edge and a trailing edge, the airfoil comprising:
 a first body having exterior surfaces defining a first portion of the aerodynamic contour of the airfoil and formed from a first material; and 
 a second body having exterior surfaces defining a second portion of the aerodynamic contour of the airfoil, the second body coupled to the first body and formed from a second material having a different temperature capability than the first material. 
   
     
     
         10 . The nozzle of  claim 9 , wherein the second material is a ceramic matrix composite. 
     
     
         11 . The nozzle of  claim 9 , wherein the exterior surfaces of the first body at least partially define a pressure side and a suction side and further define a leading edge, and wherein the exterior surfaces of the second body define a trailing edge. 
     
     
         12 . The nozzle of  claim 9 , wherein the second body is continuous throughout a cross-sectional profile. 
     
     
         13 . The nozzle of  claim 9 , wherein one of the first body or the second body defines a recess and the other of the first body or the second body comprises a protrusion, and wherein engagement of the protrusion in the recess couples the second body to the first body. 
     
     
         14 . The nozzle of  claim 9 , further comprising an end cap coupling the second body to the first body. 
     
     
         15 . A turbine system, comprising:
 a turbine section, the turbine section comprising a plurality of hot gas path components, at least one of the plurality of hot gas path components comprising an airfoil having exterior surfaces defining an aerodynamic contour, the aerodynamic contour comprising a pressure side and a suction side extending between a leading edge and a trailing edge, the airfoil comprising:
 a first body having exterior surfaces defining a first portion of the aerodynamic contour of the airfoil and formed from a first material; and 
 a second body having exterior surfaces defining a second portion of the aerodynamic contour of the airfoil, the second body coupled to the first body and formed from a second material having a different temperature capability than the first material. 
   
     
     
         16 . The turbine system of  claim 15 , wherein the second material is a ceramic matrix composite. 
     
     
         17 . The turbine system of  claim 15 , wherein the exterior surfaces of the first body at least partially define a pressure side and a suction side and further define a leading edge, and wherein the exterior surfaces of the second body define a trailing edge. 
     
     
         18 . The turbine system of  claim 15 , wherein the second body is continuous throughout a cross-sectional profile. 
     
     
         19 . The turbine system of  claim 15 , wherein one of the first body or the second body defines a recess and the other of the first body or the second body comprises a protrusion, and wherein engagement of the protrusion in the recess couples the second body to the first body. 
     
     
         20 . The turbine system of  claim 15 , further comprising an end cap coupling the second body to the first body.