Apparatus and method for minimizing and/or eliminating dilution air leakage in a combustion liner assembly

Abstract

A combustion liner assembly for a gas turbine includes an outer liner, the outer liner having a flange at a forward end. An inner liner is disposed within the outer liner. The inner liner has a first inner wall. A venturi includes a second inner wall, a venturi throat, and the first inner wall of the inner liner. A slip joint is connected to the second inner wall. The slip joint receives the flange of the outer liner. Alternatively, or additionally, the combustion liner assembly includes a slip joint between the inner or outer liner and an aft section.

1 . A combustion liner assembly for a gas turbine, comprising:
 an outer liner, the outer liner having a flange at a forward end;   an inner liner disposed within the outer liner, the inner liner having a first inner wall;   a venturi comprising a second inner wall, a venturi throat, and the first inner wall of the inner liner; and   a slip joint connected to the second inner wall, the slip joint receiving the flange of the outer liner.   
     
     
         2 . A combustion liner assembly according to  claim 1 , further comprising an aft section provided at aft ends of the outer liner and the inner liner. 
     
     
         3 . A combustion liner assembly according to  claim 1 , further comprising:
 a second slip joint connecting the aft section and the outer liner or the inner liner.   
     
     
         4 . A combustion liner assembly according to  claim 1 , wherein the outer liner comprises a plurality of radial drain or dump holes. 
     
     
         5 . A combustion liner assembly according to  claim 2 , wherein the aft section comprises a plurality of radial drain or dump holes. 
     
     
         6 . A combustion liner assembly according to  claim 5 , wherein the aft section further comprises a plurality of axial drain or dump holes. 
     
     
         7 . A combustion liner assembly according to  claim 2 , wherein the aft section comprises a plurality of axial drain or dump holes. 
     
     
         8 . A combustion liner assembly according to  claim 2 , wherein the aft section comprises a plurality of holes at an intersection of a cylindrical section of the aft section and a conical section of the aft section. 
     
     
         9 . A combustion liner assembly according to  claim 1 , wherein the slip joint is formed of a nickel alloy and the flange is formed of stainless steel. 
     
     
         10 . A combustion liner assembly according to  claim 1 , wherein the slip joint comprises a wear coating. 
     
     
         11 . A combustor for a gas turbine, comprising:
 a liner sleeve; and   a combustion liner assembly according to  claim 1 , wherein the combustion liner assembly is welded to the liner sleeve at least at the slip joint.   
     
     
         12 . A combustion liner assembly for a gas turbine, comprising:
 an outer liner;   an inner liner disposed within the outer liner, the inner liner having a first inner wall;   a venturi comprising a second inner wall, a venturi throat, and the first inner wall of the inner liner;   an aft section connected to aft ends of the outer liner and the inner liner; and   a slip joint provided between the aft section and the inner liner.   
     
     
         13 . A combustion liner assembly according to  claim 12 , wherein the aft section further comprises a bellows. 
     
     
         14 . A combustion liner assembly according to  claim 12 , wherein the outer liner comprises a plurality of radial drain or dump holes. 
     
     
         15 . A combustion liner assembly according to  claim 12 , wherein the aft section comprises a plurality of radial drain or dump holes. 
     
     
         16 . A combustion liner assembly according to  claim 15 , wherein the aft section further comprises a plurality of axial drain or dump holes. 
     
     
         17 . A combustion liner assembly according to  claim 12 , wherein the aft section comprises a plurality of axial drain or dump holes. 
     
     
         18 . A combustion liner assembly according to  claim 12 , wherein the aft section comprises a plurality of holes at an intersection of a cylindrical section of the aft section and a conical section of the aft section. 
     
     
         19 . A combustion liner assembly according to  claim 12 , wherein the slip joint comprises a wear coating. 
     
     
         20 . A combustor for a gas turbine, comprising:
 a liner sleeve; and   a combustion liner assembly according to  claim 12 , wherein the combustion liner assembly is welded to the liner sleeve.