Dilution Structure for Gas Turbine Engine Combustor

Abstract

The present disclosure is directed to a combustor assembly for a gas turbine engine. The combustor assembly includes a liner defining a combustion chamber therewithin and a pressure plenum surrounding the liner. The liner defines an opening. The liner includes a walled chute disposed at least partially within the opening. The walled chute defines an inner surface at least partially defining a jet destabilizer.

What is claimed is: 
     
         1 . A combustor assembly for a gas turbine engine, the combustor assembly comprising:
 a liner defining a combustion chamber therewithin and a pressure plenum surrounding the liner, wherein the liner comprises an opening, and wherein the liner comprises a walled chute disposed at least partially within the opening, and further wherein the walled chute comprises an inner surface, and wherein the inner surface comprises a jet destabilizer.   
     
     
         2 . The combustor assembly of  claim 1 , wherein the walled chute defines a span of the inner surface from a cold end proximate to the pressure plenum to a hot end proximate to the combustion chamber, and wherein the jet destabilizer comprises a contoured surface defined within approximately 33% of the span from the hot end. 
     
     
         3 . The combustor assembly of  claim 2 , wherein the contoured surface comprises a chevron, a waveform, a rib structure, or a vane structure. 
     
     
         4 . The combustor assembly of  claim 1 , wherein the inner surface comprises a groove. 
     
     
         5 . The combustor assembly of  claim 4 , wherein the groove is defined substantially helical. 
     
     
         6 . The combustor assembly of  claim 4 , wherein the groove is defined substantially perpendicular to the inner surface. 
     
     
         7 . The combustor assembly of  claim 1 , wherein the jet destabilizer comprises a member extended from the inner surface at least partially across the opening. 
     
     
         8 . The combustor assembly of  claim 7 , wherein the member is extended from the inner surface of the walled chute substantially perpendicular to a direction of flow of combustion gases formed within the combustion chamber. 
     
     
         9 . The combustor assembly of  claim 7 , wherein the member is extended from the inner surface of the walled chute substantially co-directional to a direction of flow of combustion gases formed within the combustion chamber. 
     
     
         10 . The combustor assembly of  claim 1 , wherein the walled chute is extended at least partially into the combustion chamber. 
     
     
         11 . The combustor assembly of  claim 1 , wherein the walled chute is extended at least partially into the pressure plenum. 
     
     
         12 . A gas turbine engine, the gas turbine engine comprising:
 a combustor assembly comprising a liner defining a combustion chamber therebetween and a pressure plenum surrounding the liner, wherein the liner comprises an opening, and wherein the liner comprises a walled chute disposed at least partially within the opening, and further wherein the walled chute comprises an inner surface, and wherein the inner surface comprises a jet destabilizer in a first flow passage defined within the walled chute.   
     
     
         13 . The gas turbine engine of  claim 12 , wherein the jet destabilizer comprises a member extended across a diameter of the opening of the liner. 
     
     
         14 . The gas turbine engine of  claim 13 , wherein the member is extended from the inner surface substantially perpendicular to a direction of flow of combustion gases formed within the combustion chamber. 
     
     
         15 . The gas turbine engine of  claim 13 , wherein the member is extended from the inner surface substantially co-directional to a direction of flow of combustion gases formed within the combustion chamber. 
     
     
         16 . The gas turbine engine of  claim 12 , wherein the jet destabilizer is defined at the inner surface between a cold end and a hot end of the first flow passage. 
     
     
         17 . The gas turbine engine of  claim 16 , wherein the jet destabilizer is defined within 33% of the walled chute from the cold end or the hot end. 
     
     
         18 . The gas turbine engine of  claim 12 , wherein the walled chute is equal to or less than six times a diameter of the opening of the liner. 
     
     
         19 . The gas turbine engine of  claim 12 , wherein the jet destabilizer comprises a groove defined at the inner surface of the walled chute. 
     
     
         20 . The gas turbine engine of  claim 12 , wherein the jet destabilizer comprises a chevron, a waveform, a rib structure, or a vane structure at the walled chute.