Turbomachine combustor assembly including a liner stop

Abstract

A turbomachine combustor assembly includes a combustor housing and a combustor body. The combustor body defines a combustor liner having a first end portion that extends to a second end portion through a combustion chamber. A cap assembly is mounted at the combustor housing. The cap assembly includes an endcover, a plurality of fuel nozzles supported by the end cover, and an outer barrel member. The outer barrel member extends about the plurality of fuel nozzles. A liner stop is arranged on one of the outer barrel member and the first end portion of the combustor liner. The liner stop includes a stepped lip portion that receives the other of the outer barrel member and the first end portion of the combustor liner to form substantially smooth liner to outer barrel interface. The liner stop restricts axial movement of the combustor liner relative to the outer barrel member.

1 . A turbomachine combustor assembly comprising:
 a combustor housing having a first end;   a combustor body arranged within the combustor housing, the combustor body defining a combustor liner having a first end portion that extends to a second end portion through a combustion chamber;   a cap assembly mounted at the first end of the combustor housing, the cap assembly including an endcover, a plurality of fuel nozzles supported by the end cover and an outer barrel member extending between the end cover and the combustor housing, the outer barrel member extending about the plurality of fuel nozzles; and   a liner stop arranged on one of the outer barrel member and the first end portion of the combustor liner, the liner stop including a stepped lip portion that receives the other of the outer barrel member and the first end portion of the combustor liner to form substantially smooth liner-to-outer barrel interface, the liner stop restricting axial movement of the combustor liner relative to the outer barrel member.   
     
     
         2 . The turbomachine combustor assembly according to  claim 1 , further comprising: a seal member arranged at the substantially smooth liner to outer barrel interface. 
     
     
         3 . The turbomachine combustor assembly according to  claim 2 , wherein the seal member is provided on the stepped lip portion. 
     
     
         4 . The turbomachine combustor assembly according to  claim 2 , wherein the seal member extends radially about the outer barrel member at the stepped lip portion. 
     
     
         5 . The turbomachine combustor assembly according to  claim 2 , wherein the seal member comprises a hula seal. 
     
     
         6 . The turbomachine combustor assembly according to  claim 1 , wherein the substantially smooth liner-to-outer barrel interface is configured and disposed to condition a fluid flow passing over the combustor liner toward the end cover. 
     
     
         7 . The turbomachine combustor assembly according to  claim 6 , wherein the stepped lip portion is configured and disposed to promote a substantially laminar flow across the substantially smooth liner to outer barrel interface. 
     
     
         8 . The turbomachine combustor assembly according to  claim 1 , wherein the liner stop is provided on the outer barrel member. 
     
     
         9 . A turbomachine comprising:
 a compressor portion;   a turbine portion operatively connected to the compressor portion; and   a combustor assembly fluidly connecting the compressor portion and the turbine portion, the combustor assembly comprising:
 a combustor housing having a first end;
 a combustor body arranged within the combustor housing, the combustor body defining a combustor liner having a first end portion that extends to a second end portion through a combustion chamber; 
 a cap assembly mounted at the first end of the combustor housing, the cap assembly including an endcover, a plurality of fuel nozzles supported by the end cover and an outer barrel member extending between the end cover and the combustor housing, the outer barrel member extending about the plurality of fuel nozzles; and 
 a liner stop arranged on one of the outer barrel member and the first end portion of the combustor liner, the liner stop including a stepped lip portion that receives the other of the outer barrel member and the first end portion of the combustor liner to form substantially smooth liner to outer barrel interface, the liner stop restricting axial movement of the combustor liner relative to the outer barrel member. 
 
   
     
     
         10 . The turbomachine according to  claim 9 , further comprising: a seal member arranged at the substantially smooth liner to outer barrel interface. 
     
     
         11 . The turbomachine according to  claim 9 , wherein the seal member is provided on the stepped lip portion. 
     
     
         12 . The turbomachine according to  claim 9 , wherein the seal member extends radially about the outer barrel member at the stepped lip portion. 
     
     
         13 . The turbomachine according to  claim 9 , wherein the seal member comprises a hula seal. 
     
     
         14 . The turbomachine according to  claim 9 , wherein the substantially smooth liner-to-outer barrel interface is configured and disposed to condition a fluid flow passing over the combustor liner toward the end cover. 
     
     
         15 . The turbomachine according to  claim 14 , wherein stepped lip portion is configured and disposed to promote a substantially laminar flow across the substantially smooth liner to outer barrel interface. 
     
     
         16 . The turbomachine according to  claim 9 , wherein the liner stop is provided on the outer barrel member. 
     
     
         17 . A method of joining a cap assembly to a turbomachine combustor housing, the method comprising:
 aligning an outer barrel member carried by the cap assembly with a combustor liner extending about a combustion chamber in the combustor housing;   inserting a stepped lip portion provided on one of the outer barrel member and the combustor liner into the other of the outer barrel member and the combustor liner to form a liner to outer barrel interface; and   securing the cap assembly to the turbomachine combustor housing.   
     
     
         18 . The method of  claim 17 , further comprising: sealing the liner to outer barrel interface. 
     
     
         19 . The method of  claim 17 , wherein inserting the stepped lip portion provided on one of the outer barrel member and the combustor liner into the other of the outer barrel member and the combustor liner includes compressing seal provided on the stepped lip portion. 
     
     
         20 . The method of  claim 17 , further comprising: restricting axial movement of the combustor liner relative to the outer barrel member with the stepped lip portion.