Fuel air mixer assembly for a gas turbine engine combustor

Abstract

A combustor for a gas turbine engine includes a multiple of fuel air mixer assemblies arranged around an engine central longitudinal axis, each of the multiple of fuel air mixer assemblies including a non-round swirler which at least partially receives a nozzle along the axis of each of the respective multiple of mixer assemblies.

1 . A fuel air mixer assembly, comprising:
 a non-round swirler arranged along a swirler axis; and   a non-round fuel nozzle received at least partially within the non-round swirler.   
     
     
         2 . The assembly as recited in  claim 1 , wherein the non-round fuel nozzle includes a multiple of fuel jets, a first of the multiple of fuel jets of a size different than a second of the multiple of fuel jets. 
     
     
         3 . The assembly as recited in  claim 1 , wherein the non-round fuel nozzle is arranged along the swirler axis. 
     
     
         4 . The assembly as recited in  claim 1 , wherein the non-round fuel nozzle is elliptical in cross-section. 
     
     
         5 . The assembly as recited in  claim 1 , wherein the non-round fuel nozzle is rectilinear in cross-section. 
     
     
         6 . A combustor for a gas turbine engine, comprising:
 a multiple of fuel air mixer assemblies defined around an engine central longitudinal axis, each of the multiple of fuel air mixer assemblies including a non-round swirler which at least partially receives a fuel nozzle along a swirler axis of each of the respective multiple of mixer assemblies, each of the multiple of fuel air mixer assemblies operable to provide a non-round fuel air mixture spray pattern that at least partially overlaps an adjacent non-round fuel air mixture spray pattern.   
     
     
         7 . The combustor as recited in  claim 6 , wherein the non-round swirler of each of the respective multiple of fuel air mixer assemblies is elliptical. 
     
     
         8 . The combustor as recited in  claim 6 , wherein the non-round swirler of each of the respective multiple of fuel air mixer assemblies is arranged such that a major axis thereof is clocked relative to the major axis of an adjacent one of the multiple of mixer assemblies. 
     
     
         9 . The combustor as recited in  claim 6 , wherein the swirler of each of the respective multiple of fuel air mixer assemblies is arranged such that a major axis thereof is clocked to define a circular distribution around an engine central longitudinal axis. 
     
     
         10 . The combustor as recited in  claim 6 , wherein the fuel-air mixture pattern from each of the respective multiple of fuel air mixer assemblies at least partially overlaps an adjacent one of the respective multiple of mixer assemblies. 
     
     
         11 . A combustor for a gas turbine engine, comprising:
 a multiple of fuel air mixer assemblies defined around an engine central longitudinal axis, each of the multiple of fuel air mixer assemblies including a non-round swirler which at least partially receives a fuel nozzle along the axis of each of the respective multiple of fuel air mixer assemblies operable to provide a non-round fuel air mixture spray pattern, each of the multiple of fuel air mixer assemblies being clocked in relation to the circumferential position within the combustor.   
     
     
         12 . The combustor as recited in  claim 11 , wherein the non-round swirler of each of the respective multiple of fuel air mixer assemblies is arranged such that a major axis thereof is clocked relative to the major axis of an adjacent one of the multiple of mixer assemblies. 
     
     
         13 . The combustor as recited in  claim 11 , wherein the swirler of each of the respective multiple of fuel air mixer assemblies is arranged such that a major axis thereof is clocked to define a circular distribution around an engine central longitudinal axis. 
     
     
         14 . The combustor as recited in  claim 11 , wherein the non-round fuel-air mixture pattern from each of the respective multiple of fuel air mixer assemblies at least partially overlaps an adjacent one of the respective multiple of mixer assemblies. 
     
     
         15 . The combustor as recited in  claim 11 , wherein the swirler of each of the respective multiple of fuel air mixer assemblies is arranged such that a major axis thereof is oriented to be generally parallel with respect to an inner and outer combustor liner assembly. 
     
     
         16 . The combustor as recited in  claim 11 , wherein the swirler of each of the respective multiple of fuel air mixer assemblies is arranged such that a major axis thereof is clocked with respect to an inner and outer combustor liner assembly. 
     
     
         17 . The combustor as recited in  claim 11 , wherein the swirler of each of the respective multiple of fuel air mixer assemblies is arranged such that a major axis thereof is clocked to form a circular arrangement around an engine axis. 
     
     
         18 . The combustor as recited in  claim 11 , wherein the fuel nozzle of each of the respective multiple of fuel air mixer assemblies is arranged such that a major axis thereof is clocked around an engine axis. 
     
     
         19 . The combustor as recited in  claim 11 , wherein the swirler of at least one of the multiple of fuel air mixer assemblies is arranged such that a major axis thereof is clocked relative to at least one other of the multiple of mixer assemblies. 
     
     
         20 . The combustor as recited in  claim 19 , wherein the fuel nozzle of at least one of the multiple of fuel air mixer assemblies is arranged such that a major axis thereof is clocked relative to at least one other of the multiple of mixer assemblies.