Combustor assembly for a turbine engine

Abstract

A combustor assembly for a gas turbine engine includes a dome defining a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end is received within the slot of the dome. In one exemplary aspect, the combustor assembly includes features that warm the forward end of the liner during transient operation of the engine. Furthermore, the combustor assembly includes features that reduce the thermal gradient between the forward end and the other portions of the liner. In this way, improved durability of the liner may be achieved.

What is claimed is: 
     
         1 . A combustor assembly for a gas turbine engine defining an axial direction, a radial direction, and a circumferential direction, the combustor assembly comprising:
 a dome defining a slot;   a liner at least partially defining a combustion chamber and extending between an aft end and a forward end, the forward end of the liner received within the slot of the dome; and   a baffle extending between an aft end and a forward end, the forward end of the baffle attached to the dome, the baffle spaced from the liner in a direction opposite the combustion chamber along the radial direction;   wherein a warming passage is defined between the liner and the baffle, the warming passage extending between an inlet and outlet, and wherein the baffle defines the inlet of the warming passage aft of the forward end of the liner and the outlet is at least partially defined by the forward end of the liner.   
     
     
         2 . The combustor assembly of  claim 1 , wherein the aft end of the baffle is positioned proximate the aft end of the liner along the axial direction, and wherein the inlet is defined by the baffle proximate the aft end of the baffle. 
     
     
         3 . The combustor assembly of  claim 2 , wherein the aft end of the baffle is attached to a structural member positioned at the aft end of the combustor assembly. 
     
     
         4 . The combustor assembly of  claim 1 , wherein a midplane is defined between the aft end and the forward end of the liner, and wherein the inlet is defined by the baffle at or aft of the midplane. 
     
     
         5 . The combustor assembly of  claim 1 , wherein a midplane is defined between the aft end and the forward end of the liner and a quarter plane is defined between the midplane and the forward end of the liner, and wherein the inlet is defined by the baffle at or aft of the quarter plane. 
     
     
         6 . The combustor assembly of  claim 1 , wherein a midplane is defined between the aft end and the forward end of the liner and a three-quarter plane is defined between the midplane and the aft end of the liner, and wherein the inlet is defined by the baffle at or aft of the three-quarter plane. 
     
     
         7 . The combustor assembly of  claim 1 , wherein the warming passage is defined between an outer surface of the liner and an inner surface of the baffle. 
     
     
         8 . The combustor assembly of  claim 1 , wherein the outlet is defined at least partially by the forward end of the liner and a yoke of the dome. 
     
     
         9 . The combustor assembly of  claim 1 , further comprising:
 a mounting assembly coupling the dome and the forward end of the liner, the mounting assembly spaced apart from the warming passage along the circumferential direction.   
     
     
         10 . The combustor assembly of  claim 9 , wherein the mounting assembly is positioned forward of the outlet in the axial direction. 
     
     
         11 . The combustor assembly of  claim 1 , wherein the baffle is positioned outward from the liner in the radial direction. 
     
     
         12 . The combustor assembly of  claim 11 , wherein the warming passage is defined between an outer radial surface of the liner and an inner radial surface of the baffle. 
     
     
         13 . A gas turbine engine, comprising:
 a compressor section;   a turbine section; and   a combustor assembly defining an axial direction, a radial direction, and a circumferential direction, the combustor assembly comprising:
 a dome defining a slot; 
 a liner at least partially defining a combustion chamber and extending between an aft end and a forward end, the forward end of the liner received within the slot of the dome; and 
 a baffle extending between an aft end and a forward end, the forward end of the baffle attached to the dome, the baffle spaced from the liner in a direction opposite the combustion chamber along the radial direction; 
 wherein a warming passage is defined between the liner and the baffle, the warming passage extending between an inlet and outlet, and wherein the baffle defines the inlet of the warming passage aft of the forward end of the liner and the outlet is at least partially defined by the forward end of the liner. 
   
     
     
         14 . The gas turbine engine of  claim 9 , wherein the aft end of the baffle is positioned proximate the aft end of the liner along the axial direction, and wherein the inlet is defined by the baffle proximate the aft end of the baffle. 
     
     
         15 . The gas turbine engine of  claim 10 , wherein the aft end of the baffle is attached to a structural member positioned at the aft end of the combustor assembly. 
     
     
         16 . The gas turbine engine of  claim 9 , wherein a midplane is defined between the aft end and the forward end of the liner, and wherein the inlet is defined by the baffle at or aft of the midplane. 
     
     
         17 . The gas turbine engine of  claim 9 , wherein a midplane is defined between the aft end and the forward end of the liner and a quarter plane is defined between the midplane and the forward end of the liner, and wherein the inlet is defined by the baffle at or aft of the quarter plane. 
     
     
         18 . The gas turbine engine of  claim 9 , wherein a midplane is defined between the aft end and the forward end of the liner and a three-quarter plane is defined between the midplane and the aft end of the liner, and wherein the inlet is defined by the baffle at or aft of the three-quarter plane. 
     
     
         19 . The gas turbine engine of  claim 9 , wherein the warming passage is defined between an outer surface of the liner and an inner surface of the baffle. 
     
     
         20 . The gas turbine engine of  claim 9 , wherein the outlet is defined at least partially by the forward end of the liner and a yoke of the dome.