Nozzle for turbine system

Abstract

A nozzle for a turbine system is disclosed. The nozzle includes an airfoil, an inner sidewall, and an outer sidewall. The airfoil includes exterior surface defining a pressure side and a suction side extending between a leading edge and a trailing edge. The airfoil further defines a tip and a root. The inner sidewall is connected to the airfoil at the tip. The outer sidewall is connected to the airfoil at the root. The inner sidewall and outer sidewall each includes a peripheral edge defining a pressure side slash face, a suction side slash face, a leading edge face, and a trailing edge face. At least one of the inner sidewall pressure side slash face, the inner sidewall suction side slash face, the outer sidewall pressure side slash face, or the outer sidewall suction side slash face has a generally curvilinear profile.

What is claimed is: 
     
         1 . A nozzle for a turbine system, the nozzle comprising:
 an airfoil comprising exterior surface defining a pressure side and a suction side extending between a leading edge and a trailing edge, the airfoil further defining a tip and a root;   an inner sidewall connected to the airfoil at the tip, the inner sidewall comprising a peripheral edge defining a pressure side slash face, a suction side slash face, a leading edge face, and a trailing edge face; and   an outer sidewall connected to the airfoil at the root, the outer sidewall comprising a peripheral edge defining a pressure side slash face, a suction side slash face, a leading edge face, and a trailing edge face,   wherein at least one of the inner sidewall pressure side slash face, the inner sidewall suction side slash face, the outer sidewall pressure side slash face, or the outer sidewall suction side slash face has a generally curvilinear profile.   
     
     
         2 . The nozzle of  claim 1 , wherein the inner sidewall pressure side slash face and the outer sidewall pressure side slash face each has a generally curvilinear profile. 
     
     
         3 . The nozzle of  claim 1 , wherein the inner sidewall suction side slash face and the outer sidewall suction side slash face each has a generally curvilinear profile. 
     
     
         4 . The nozzle of  claim 1 , wherein the inner sidewall pressure side slash face, the outer sidewall pressure side slash face, the inner sidewall suction side slash face and the outer sidewall suction side slash face each has a generally curvilinear profile. 
     
     
         5 . The nozzle of  claim 1 , wherein the curvilinear profile is defined by a single centerpoint and a single radius extending from the centerpoint. 
     
     
         6 . The nozzle of  claim 1 , wherein the curvilinear profile is defined by a plurality of centerpoints and a plurality of radii, each of the plurality of radii extending from one of the plurality of centerpoints. 
     
     
         7 . The nozzle of  claim 6 , wherein the curvilinear profile is further defined by a minimum distance between the one of the inner sidewall pressure side slash face, the inner sidewall suction side slash face, the outer sidewall pressure side slash face, or the outer sidewall suction side slash face and the leading edge and trailing edge of the airfoil. 
     
     
         8 . The nozzle of  claim 1 , wherein the airfoil is a plurality of airfoils. 
     
     
         9 . A nozzle assembly for a turbine system, the nozzle assembly comprising:
 a plurality of nozzles disposed in an annular array and defining a hot gas path, each of the plurality of nozzles comprising:
 an airfoil comprising exterior surface defining a pressure side and a suction side extending between a leading edge and a trailing edge, the airfoil further defining a tip and a root; 
 an inner sidewall connected to the airfoil at the tip, the inner sidewall comprising a peripheral edge defining a pressure side slash face, a suction side slash face, a leading edge face, and a trailing edge face; and 
 an outer sidewall connected to the airfoil at the root, the outer sidewall comprising a peripheral edge defining a pressure side slash face, a suction side slash face, a leading edge face, and a trailing edge face, 
 wherein at least one of the inner sidewall pressure side slash face, the inner sidewall suction side slash face, the outer sidewall pressure side slash face, or the outer sidewall suction side slash face has a generally curvilinear profile. 
   
     
     
         10 . The nozzle assembly of  claim 9 , wherein the curvilinear profile is defined by a single centerpoint and a single radius extending from the centerpoint. 
     
     
         11 . The nozzle assembly of  claim 9 , wherein the curvilinear profile is defined by a plurality of centerpoints and a plurality of radii, each of the plurality of radii extending from one of the plurality of centerpoints. 
     
     
         12 . The nozzle assembly of  claim 11 , wherein the curvilinear profile is further defined by a minimum distance between the one of the inner sidewall pressure side slash face, the inner sidewall suction side slash face, the outer sidewall pressure side slash face, or the outer sidewall suction side slash face and the leading edge and trailing edge of the airfoil. 
     
     
         13 . The nozzle assembly of  claim 9 , wherein the airfoil is a plurality of airfoils. 
     
     
         14 . The nozzle assembly of  claim 9 , wherein the nozzle is a first stage nozzle. 
     
     
         15 . A gas turbine system, comprising:
 a compressor section;   a combustor section; and   a turbine section, the turbine section comprising a plurality of turbine stages, each of the plurality of turbine stages comprising a nozzle assembly, the nozzle assembly comprising a plurality of nozzles disposed in an annular array and defining a hot gas path, each of the plurality of nozzles comprising:
 an airfoil comprising exterior surface defining a pressure side and a suction side extending between a leading edge and a trailing edge, the airfoil further defining a tip and a root; 
 an inner sidewall connected to the airfoil at the tip, the inner sidewall comprising a peripheral edge defining a pressure side slash face, a suction side slash face, a leading edge face, and a trailing edge face; and 
 an outer sidewall connected to the airfoil at the root, the outer sidewall comprising a peripheral edge defining a pressure side slash face, a suction side slash face, a leading edge face, and a trailing edge face, 
 wherein at least one of the inner sidewall pressure side slash face, the inner sidewall suction side slash face, the outer sidewall pressure side slash face, or the outer sidewall suction side slash face has a generally curvilinear profile. 
   
     
     
         16 . The gas turbine system of  claim 15 , wherein the curvilinear profile is defined by a single centerpoint and a single radius extending from the centerpoint. 
     
     
         17 . The gas turbine system of  claim 15 , wherein the curvilinear profile is defined by a plurality of centerpoints and a plurality of radii, each of the plurality of radii extending from one of the plurality of centerpoints. 
     
     
         18 . The gas turbine system of  claim 17 , wherein the curvilinear profile is further defined by a minimum distance between the one of the inner sidewall pressure side slash face, the inner sidewall suction side slash face, the outer sidewall pressure side slash face, or the outer sidewall suction side slash face and the leading edge and trailing edge of the airfoil. 
     
     
         19 . The gas turbine system of  claim 15 , wherein the airfoil is a plurality of airfoils. 
     
     
         20 . The gas turbine system of  claim 15 , wherein the nozzle assembly is a first stage nozzle assembly.