Turbomachine with trapped vortex feature

Abstract

A turbomachine with a trapped vortex feature includes a unibody liner formed to define a flow path for combustion products, the unibody liner including first and second portions defining first radial planes, a third portion defining a second radial plane and fourth and fifth portions extending substantially radially between proximal ends of the first and third portions and proximal ends of the second and third portions, respectively, and an injector configured to deliver a fuel or a fuel/air mixture to a space partially bound by the third, fourth and fifth portions.

1 . A turbomachine with a trapped vortex feature, comprising:
 a unibody liner formed to define a flow path for combustion products, the unibody liner comprising:   first and second portions defining first radial planes, a third portion defining a second radial plane and fourth and fifth portions extending substantially radially between proximal ends of the first and third portions and proximal ends of the second and third portions, respectively; and   an injector configured to deliver a fuel or a fuel/air mixture to a space partially bound by the third, fourth and fifth portions.   
     
     
         2 . The turbomachine according to  claim 1 , wherein the injector is configured to deliver the fuel or the fuel/air mixture to the space in a substantially axial direction. 
     
     
         3 . The turbomachine according to  claim 1 , wherein the unibody liner comprises a combustor liner and a transition piece liner and the space is defined proximate to a connection of the combustor liner and the transition piece. 
     
     
         4 . The turbomachine according to  claim 1 , wherein the space has an annular shape. 
     
     
         5 . The turbomachine according to  claim 1 , wherein the space has a substantially rectangular cross-sectional shape. 
     
     
         6 . A turbomachine, comprising:
 a unibody liner formed to define a flow path for combustion products;   the unibody liner being formed to define a trapped vortex feature into which a portion of combustion products flow; and   an injector configured to deliver a fuel or a fuel/air mixture to the trapped vortex feature.   
     
     
         7 . The turbomachine according to  claim 6 , wherein the injector is configured to deliver the fuel or the fuel/air mixture to the trapped vortex feature in a substantially axial direction. 
     
     
         8 . The turbomachine according to  claim 6 , wherein the unibody liner comprises a combustor liner and a transition piece liner and the trapped vortex feature is defined proximate to a connection of the combustor liner and the transition piece. 
     
     
         9 . The turbomachine according to  claim 6 , wherein the trapped vortex feature has an annular shape. 
     
     
         10 . The turbomachine according to  claim 6 , wherein the trapped vortex feature has a substantially rectangular cross-sectional shape. 
     
     
         11 . A turbomachine, comprising:
 a combustor liner defining a first interior in which combustion occurs and a second interior through which products of combustion flow;   a transition piece liner disposed downstream from the combustor liner, the transition piece liner defining a third interior, which is receptive of the products of combustion and through which the products of combustion continue to flow,   at least one of the combustor liner and the transition piece liner being formed to define a recess into which a portion of the products of combustion flow; and   an injector configured to deliver combustible materials to the recess whereby the combustible materials and the portion of the products of combustion form respectively trapped vortices.   
     
     
         12 . The turbomachine according to  claim 11 , wherein the combustible materials comprise fuel or a fuel mixed with compressor discharge casing air. 
     
     
         13 . The turbomachine according to  claim 11 , further comprising:
 a flow sleeve disposed about the combustor liner to define a first annulus; and   an impingement sleeve disposed about the transition piece liner to define a second annulus,   the second annulus being fluidly coupled to the first annulus.   
     
     
         14 . The turbomachine according to  claim 11 , wherein the injector comprises:
 a vane formed to define a flowpath by which air is transmitted from a compressor discharge casing to the recess; and   a fuel source configured to provide a supply of fuel to the flowpath.   
     
     
         15 . The turbomachine according to  claim 14 , wherein the vane comprises a micromixer. 
     
     
         16 . The turbomachine according to  claim 14 , wherein the fuel source comprises a flexible hose. 
     
     
         17 . The turbomachine according to  claim 11 , wherein the injector is configured to deliver the combustible materials to the recess in a substantially axial direction. 
     
     
         18 . The turbomachine according to  claim 11 , wherein the recess is defined proximate to a connection of the combustor liner and the transition piece liner. 
     
     
         19 . The turbomachine according to  claim 11 , wherein the recess has an annular shape. 
     
     
         20 . The turbomachine according to  claim 11 , wherein the recess has a substantially rectangular cross-sectional shape.