Combustor assembly for a turbine engine

Abstract

A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end generally along an axial direction. The combustor assembly also includes an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner. A cap is positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome. The cap includes a surface configured to contact at least one of the enclosed surface of the annular dome and the forward end of the liner. Such a configuration may form a substantially airtight seal between the forward end of the liner and the annular dome despite a relative thermal expansion between the components.

1 . A combustor assembly for a gas turbine engine defining an axial direction, the combustor assembly comprising:
 a liner at least partially defining a combustion chamber and extending between an aft end and a forward end generally along the axial direction;   an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner; and   a cap positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome, the cap including a surface configured to contact at least one of the enclosed surface of the annular dome or the forward end of the liner;   wherein the surface of the cap is an inside surface configured to contact the forward end of the liner, wherein the cap further defines an end surface opposite the inside surface, and wherein a resilient member is positioned adjacent the end surface of the cap for forming a seal between the end surface of the cap and the enclosed surface of the annular dome.   
     
     
         2 . A cap assembly for a liner of a gas turbine engine combustor assembly, the cap assembly comprising:
 a first arm;   a second arm extending substantially parallel with the first arm, the first and second arms together defining an opening for receipt of a forward end of the liner;   a base extending between the first and second arms and defining an inside surface and an outside surface; and   a resilient member positioned adjacent to the inside surface of the base for pressing the base away from the forward end of the liner and forming a seal between the base and the forward end of the liner when the cap assembly is positioned over the forward end of the liner.   
     
     
         3 . The cap assembly of  claim 2 , wherein the first arm, the second arm, and the base are all formed integrally of a metal material or a CMC material. 
     
     
         4 . The cap assembly of  claim 2 , wherein the resilient member is a rope seal including a silicone core. 
     
     
         5 . The cap assembly of  claim 2 , wherein the first arm and the second arm each define one or more openings for receiving a mounting assembly for mounting a forward end of the liner to an annular dome. 
     
     
         6 . A gas turbine engine defining an axial direction, the gas turbine engine comprising:
 a compressor section;   a turbine section mechanically coupled to the compressor section through a shaft; and   a combustor assembly disposed between the compressor section and the turbine section, the combustor assembly including   a liner at least partially defining a combustion chamber and extending between an aft end and a forward end generally along the axial direction;   an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner; and   a cap positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome, the cap including a surface configured to contact at least one of the enclosed surface of the annular dome or the forward end of the liner.   
     
     
         7 . The gas turbine engine of  claim 6 , wherein the cap is positioned over the forward end of the liner, and wherein the surface of the cap is an end surface configured to contact the enclosed surface of the annular dome 
     
     
         8 . The gas turbine engine of  claim 7 , wherein a resilient member is positioned in a gap defined between the cap and the forward end of the liner, the resilient member configured to press the end surface of the cap against the enclosed surface and form a seal between the cap and the liner. 
     
     
         9 . The gas turbine engine of  claim 6 , wherein the gas turbine engine further defines a circumferential direction, and wherein the combustor assembly further includes a plurality fuel/air mixers spaced along the circumferential direction within the annular dome. 
     
     
         10 . The combustor assembly of  claim 1 , wherein the cap is positioned over the forward end of the liner, and wherein the first surface of the cap is an end surface configured to contact the enclosed surface of the annular dome. 
     
     
         11 . The combustor assembly of  claim 1 , wherein the end surface defines a notch. 
     
     
         12 . The combustor assembly of  claim 11 , wherein the resilient member is positioned within the notch. 
     
     
         13 . The combustor assembly of  claim 1 , wherein the resilient member is configured to press the cap against the forward end of the liner such that the inside surface of the cap contacts the forward end of the liner. 
     
     
         14 . The combustor assembly of  claim 1 , wherein the resilient member is a rope seal including a silicone core. 
     
     
         15 . The combustor assembly of  claim 1 , wherein the liner is an outer liner and wherein the annular dome is an outer annular dome. 
     
     
         16 . The combustor assembly of  claim 1 , wherein the liner is an inner liner and wherein the annular dome is an inner annular dome. 
     
     
         17 . The combustor assembly of  claim 1 , wherein the liner is comprised of a ceramic matrix composite material. 
     
     
         18 . The combustor assembly of  claim 17 , wherein the annular dome is comprised of a metal material. 
     
     
         19 . The combustor assembly of  claim 18 , wherein the annular dome includes a base plate and a yoke, the base plate and the yoke extending substantially parallel to one another, the enclosed surface of the annular dome including a second surface of the base plate and a third surface of the yoke. 
     
     
         20 . The combustor assembly of  claim 19 , further comprising:
 a mounting assembly extending through the yoke of the annular dome, through the forward end of the liner, and through the base plate of the annular dome, wherein the mounting assembly attaches the liner to the annular dome.