Corrugated cyclone mixer assembly to facilitate reduced nox emissions and improve operability in a combustor system

Abstract

A corrugated cyclone mixer for use in a fuel injection assembly of a turbine engine. The corrugated cyclone mixer generally includes an annular housing including a flange portion and a lip portion configured downstream of the flange portion. The mixer further including a swirler disposed therein the annular housing for inducing a cyclonic motion in the corrugated cyclone mixer. The swirler is configured upstream of the flange portion and including a plurality of swirler vanes to produce a swirling air flow. The lip portion forming an outlet downstream of the swirler and including a plurality of corrugations at an aft end. The plurality of corrugations are configured to mix the swirling air flow and an injected fuel stream flowing therethrough the corrugated cyclone mixer. Additionally disclosed is a fuel injection assembly and a turbine assembly including the corrugated cyclone mixer.

What is claimed is: 
     
         1 . A corrugated cyclone mixer assembly for use in a fuel injection assembly of a turbine engine, the assembly comprising:
 an annular housing comprising a flange portion and a lip portion configured downstream of the flange portion; and   a swirler disposed therein the annular housing for inducing a cyclonic motion in the corrugated cyclone mixer assembly, the swirler configured upstream of the flange portion and including a plurality of swirler vanes to produce a swirling air flow,   the lip portion forming an outlet downstream of the swirler and including a plurality of corrugations at an aft end, the plurality of corrugations configured to mix the swirling air flow and an injected fuel stream flowing therethrough the corrugated cyclone mixer assembly.   
     
     
         2 . The corrugated cyclone mixer assembly as claimed in  claim 1 , wherein the plurality of corrugations comprise a plurality of purely radially extending corrugations. 
     
     
         3 . The corrugated cyclone mixer assembly as claimed in  claim 1 , wherein the plurality of corrugations comprise a plurality of purely axially extending corrugations. 
     
     
         4 . The corrugated cyclone mixer assembly as claimed in  claim 1 , wherein the plurality of corrugations comprise a plurality of radially and tangentially extending corrugations. 
     
     
         5 . The corrugated cyclone mixer assembly as claimed in  claim 1 , wherein the plurality of corrugations comprise a plurality of radially outwardly extending corrugations. 
     
     
         6 . The corrugated cyclone mixer assembly as claimed in  claim 1 , wherein the plurality of corrugations comprise a plurality of radially inwardly extending corrugations. 
     
     
         7 . The corrugated cyclone mixer assembly as claimed in  claim 1 , wherein the plurality of corrugations are configured substantially uniformly spaced circumferentially about the lip portion. 
     
     
         8 . The corrugated cyclone mixer assembly as claimed in  claim 1 , wherein the plurality of corrugations are configured having a uniform length, extending from an apex to a base, in at least one of a radial or axial direction. 
     
     
         9 . The corrugated cyclone mixer assembly as claimed in  claim 1 , wherein the plurality of corrugations are configured as at least one of sinusoidal corrugations or substantially triangular corrugations. 
     
     
         10 . A fuel injection assembly for use in a combustor of a turbine engine, the fuel injection assembly comprising:
 a fuel nozzle assembly including a main housing and defining an annular cavity, the fuel nozzle assembly comprising;
 a fuel manifold in fluid communication with a source of fuel; and 
 a plurality of fuel injection ports, each fuel injection port configured to introduce a fuel column into the annular cavity; and 
   a corrugated cyclone mixer assembly disposed about the fuel nozzle, the corrugated cyclone mixer assembly comprising;
 an annular housing comprising a flange portion and a lip portion configured downstream of the flange portion; and 
 a swirler disposed therein the annular housing for inducing a cyclonic motion in the corrugated cyclone mixer assembly, the swirler configured upstream of the flange portion and including a plurality of swirler vanes to produce a swirling air flow, 
 the lip portion forming an outlet downstream of the swirler and including a plurality of corrugations at an aft end, the plurality of corrugations configured to mix the swirling air flow and an injected fuel stream flowing therethrough the corrugated cyclone mixer assembly. 
   
     
     
         11 . The fuel injection assembly as claimed in  claim 10 , wherein the plurality of corrugations comprise at least one of a plurality of purely radially extending corrugations or a plurality of purely axially extending corrugations. 
     
     
         12 . The fuel injection assembly as claimed in  claim 10 , wherein the plurality of corrugations include a plurality of radially and tangentially extending corrugations. 
     
     
         13 . The fuel injection assembly as claimed in  claim 10 , wherein the plurality of corrugations comprise at least one of a plurality of radially outwardly extending corrugations or a plurality of radially inwardly extending corrugations. 
     
     
         14 . The fuel injection assembly as claimed in  claim 10 , wherein the plurality of corrugations are configured substantially uniformly spaced circumferentially about the lip portion. 
     
     
         15 . The fuel injection assembly as claimed in  claim 10 , wherein the plurality of corrugations are configured having a uniform length, extending from an apex to a base, in at least one of a radial or axial direction. 
     
     
         16 . The fuel injection assembly as claimed in  claim 10 , wherein the plurality of corrugations are configured as at least one of sinusoidal corrugations or substantially triangular corrugations. 
     
     
         17 . A turbine engine assembly comprising:
 a compressor section;   a combustor section; and   a turbine section, wherein the compressor section, the combustor section and the turbine section are configured in a downstream axial flow relationship, the combustor section comprising:
 a combustion chamber; and 
 a fuel injection assembly disposed in the combustion chamber, the fuel injection assembly comprising:
 a fuel nozzle assembly including a main housing and defining an annular cavity, the fuel nozzle assembly comprising;
 a fuel manifold in fluid communication with a source of fuel; and 
 a plurality of fuel injection ports, each fuel injection port configured to introduce a fuel column into the annular cavity; and 
 
 a corrugated cyclone mixer assembly disposed about the fuel nozzle, the corrugated cyclone mixer assembly comprising;
 an annular housing comprising a flange portion and a lip portion configured downstream of the flange portion; and 
 a swirler disposed therein the annular housing for inducing a cyclonic motion in the corrugated cyclone mixer assembly, the swirler configured upstream of the flange portion and including a plurality of swirler vanes to produce a swirling air flow, 
 the lip portion forming an outlet downstream of the swirler and including a plurality of corrugations at an aft end, the plurality of corrugations configured to mix the swirling air flow and an injected fuel stream flowing therethrough the corrugated cyclone mixer assembly. 
 
 
   
     
     
         18 . The turbine engine assembly as claimed in  claim 17 , wherein the plurality of corrugations comprise at least one of a plurality of purely radially extending corrugations, a plurality of purely axially extending corrugations, a plurality of radially and tangentially extending corrugations, a plurality of radially outwardly extending corrugations or a plurality of radially inwardly extending corrugations. 
     
     
         19 . The turbine engine assembly as claimed in  claim 18 , wherein the plurality of corrugations are configured as at least one of sinusoidal corrugations or substantially triangular corrugations. 
     
     
         20 . The turbine engine assembly as claimed in  claim 17 , wherein the assembly comprises a gas turbine engine.