Trapped vortex combustor cavity manifold for gas turbine engine

Abstract

In accordance with one embodiment, the present technique provides a combustor assembly for use in a gas-turbine device. The combustor assembly includes a first combustion zone and a second combustion zone. The combustor assembly further includes a first premix chamber configured to receive a fuel and air to facilitate a first fuel-air mixture having a first fuel-to-air ratio, wherein the first premix chamber is fluidiclly coupled to the combustion chamber at the first combustion zone. The combustor assembly also includes a second premix chamber configured to receive a fuel and air to facilitate a second fuel-air mixture having a second fuel-to-air ratio, wherein the second premix chamber is fluidiclly coupled to the combustion chamber at the second combustion zone, wherein the second combustion zone is radially outboard of the first combustion zone.

1 . A combustor assembly for use with a gas-turbine device, the assembly comprising: 
 a combustion chamber having a first combustion zone and a second combustion zone;    a first premix chamber configured to receive a fuel and air to facilitate a first fuel-air mixture having a first fuel-to-air ratio, wherein the first premix chamber is fluidiclly coupled to the combustion chamber at the first combustion zone; and    a second premix chamber configured to receive a fuel and air to facilitate a second fuel-air mixture having a second fuel-to-air ratio, wherein the second premix chamber is fluidiclly coupled to the combustion chamber at the second combustion zone, wherein the second combustion zone is radially outboard of the first combustion zone.    
   
   
       2 . The combustor assembly as recited in  claim 1 , wherein the second premix chamber is configured to avoid flashback.  
   
   
       3 . The combustor assembly as recited in  claim 1 , wherein the second combustion zone is configured to produce a vortex flow of the second fuel-air mixture.  
   
   
       4 . The combustor assembly as recited in  claim 1 , wherein the second premix chamber is configured to provide a lesser volume of compressed air to the combustion chamber than the first premix chamber.  
   
   
       5 . The combustor assembly as recited in  claim 1 , further comprising a diffusion chamber configure to receive fuel and to provide the fuel to the secondary combustion zone.  
   
   
       6 . The combustor assembly as recited in  claim 1 , wherein the second premix chamber is smaller in volume than the first premix chamber.  
   
   
       7 . The combustor assembly as recited in  claim 1 , comprising an ignition source disposed adjacent to the second combustion zone and configured to ignite the second fuel-air mixture.  
   
   
       8 . The combustor assembly as recited in  claim 1 , wherein walls of the combustion chamber comprises a plurality of aperture to facilitate air-flow towards the combustion chamber.  
   
   
       9 . The combustor assembly as recited in  claim 1 , further comprises an impingement layer configured to direct compressed air along an outer surface of the combustion chamber.  
   
   
       10 . A combustor assembly for use with a gas turbine device, the assembly comprising: 
 a combustion chamber having a first combustion zone and a second combustion zone;    a first premix chamber coupled to the combustion chamber at the first combustion zone and configured to receive fuel and air to produce a first fuel-air mixture; and    a second premix chamber coupled to the combustion chamber at the second combustion zone via an inlet and configured to receive fuel and air to produce a second fuel-air mixture, wherein the second combustion zone comprises an inner surface configured to facilitate a vortex flow of the second fuel-air mixture introduced into the second combustion zone.    
   
   
       11 . The combustor assembly as recited in  claim 10 , wherein the second combustion zone has a U-shaped profile.  
   
   
       12 . The combustor assembly as recited in  claim 10 , wherein the inlet is disposed on a first surface opposite to the inner surface of the combustion chamber, wherein the first and the inner surface are non-adjacent with respect to one another.  
   
   
       13 . The combustor assembly as recited in  claim 12 , wherein the combustion chamber comprises a further surface extending from the first surface to the inner surface.  
   
   
       14 . The combustor assembly as recited in  claim 13 , comprising an ignition source extending at least partially through the further surface.  
   
   
       15 . The combustor assembly as recited in  claim 10 , further comprising a diffusion chamber configure to receive fuel and to provide the fuel to the secondary combustion zone.  
   
   
       16 . A combustor assembly for use with a gas-turbine device, the assembly comprising: 
 a combustion chamber having a first combustion zone and a second combustion zone;    a first premix chamber configured to receive a fuel and air to facilitate a first fuel-air mixture having a first fuel-to-air ratio, wherein the first premix chamber is fluidiclly coupled to the combustion chamber; and at the first combustion zone;    a second premix chamber configured to receive a fuel and air to facilitate a second fuel-air mixture having a second fuel-to-air ratio, wherein the second premix chamber is fluidiclly coupled to the combustion chamber at the second combustion zone, wherein the second combustion zone is radially outboard of the first combustion zone; and    a diffusion chamber configured to provide a fuel to the combustion chamber.    
   
   
       17 . The combustor assembly as recited in  claim 16 , wherein the diffusion chamber is disposed between the first and second premix chambers.  
   
   
       18 . The combustor assembly as recited in  claim 16 , wherein the second combustion zone comprises an inner surface configured to facilitate a vortex flow of the second fuel-air mixture introduced into the second combustion zone.  
   
   
       19 . A two-stage combustor assembly for use with a gas turbine device, the assembly comprising: 
 a first stage combustor assembly having a combustion chamber, wherein the combustion chamber comprises a first combustion zone and a second combustion zone, the first stage combustor assembly comprising: 
 a first premix chamber coupled to the combustion chamber of the first stage at the first combustion zone and configured to receive fuel and air to produce a first fuel-air mixture;  
 a second premix chamber coupled to the combustion chamber of the first stage combustor assembly at the second combustion zone via an inlet and configured to receive fuel and air to produce a second fuel-air mixture, wherein the second combustion zone comprises an inner surface configured to facilitate a vortex flow of the second fuel-air mixture introduced into the second combustion zone; and  
 a first ignition source disposed in the second combustion zone of the combustion chamber of the first stage combustor assembly, wherein the first ignition source ignites the second fuel-air mixture and the first fuel-air mixture to produce first combustion gases at the combustion chamber of the first stage combustor assembly; and  
   a second stage combustor assembly having a combustion chamber, wherein the combustion chamber comprises a third combustion zone and is configured to receive the first combustion gases from the first stage combustor assembly, the second stage combustor assembly comprising: 
 a third premix chamber coupled to the combustion chamber of the second stage combustor assembly at the third combustion zone via an inlet and configured to receive fuel and air to produce a third fuel-air mixture, wherein the third combustion zone comprises an inner surface configured to facilitate a vortex flow of the third fuel-air mixture introduced into the third combustion zone; and  
   a second ignition source disposed in the third combustion zone of the combustion chamber of the second stage combustor assembly, wherein the second ignition source ignites the third fuel-air mixture to produce combustion gases, wherein the combustion gases mix with the first combustion gases to produce second combustion gases at the combustion chamber of the second stage combustor assembly.    
   
   
       20 . The two-stage combustor assembly as recited in  claim 19 , wherein the combustion chamber of the first stage combustor assembly comprises a diffusion chamber configured to receive fuel and to provide the fuel to the second combustion zone of the combustion chamber of the first stage combustor assembly.  
   
   
       21 . The combustor assembly as recited in  claim 19 , wherein the combustion chamber of the first stage combustor assembly or the combustion chamber of the second stage combustor assembly comprises a plurality of aperture to facilitate airflow towards the combustion chamber.  
   
   
       22 . The combustor assembly as recited in  claim 19 , wherein the first stage combustor assembly or the second stage combustor assembly further comprises an impingement layer configured to direct compressed air along an outer surface of the combustion chamber.  
   
   
       23 . A gas-turbine device, the device comprising: 
 a compressor configured to generate an airflow;    a combustor assembly comprising a first stage combustor assembly having a combustion chamber, wherein the combustion chamber comprises a first combustion zone and a second combustion zone, the first stage combustor assembly comprising:    a first premix chamber configured to receive a fuel and air to facilitate a first fuel-air mixture having a first fuel-to-air ratio, wherein the first premix chamber is fluidiclly coupled to the combustion chamber of the first stage combustor assembly; and at the first combustion zone;    a second premix chamber fluidiclly coupled to the combustion chamber of the first stage combustor assembly at the second combustion zone via an inlet and configured to receive fuel and air to produce a second fuel-air mixture, wherein the second combustion zone comprises an inner surface configured to facilitate a vortex flow of the second fuel-air mixture introduced into the second combustion zone;    a first ignition source disposed in the second combustion zone of the combustion chamber of the first stage combustor assembly; and    an exhaust pathway located downstream of the compressor and the first and second premix chambers of the combustion chamber of the first stage combustor assembly with respect to the airflow; and    a turbine disposed downstream of the exhaust pathway with respect to the airflow.    
   
   
       24 . The gas-turbine device as recited in  claim 23 , wherein the combustor assembly comprises a second stage combustor assembly coupled to the first stage combustor assembly, located down stream of the first stage combustor assembly with respect to the airflow and comprises a combustion chamber having a third combustion zone.  
   
   
       25 . The gas-turbine device as recited in  claim 24 , wherein second stage combustor assembly comprises a combustion gas chamber configured to receive first combustion gases from the first stage combustor assembly and fluidiclly coupled to the combustion chamber of the second stage combustor assembly; and located up stream of the combustion chamber of the second stage combustor assembly with respect to the airflow.  
   
   
       26 . The gas-turbine device as recited in  claim 24 , wherein second stage combustor assembly comprises a third premix chamber coupled to the combustion chamber of the second stage combustor assembly at the third combustion zone via an inlet and configured to receive fuel and air to produce a third fuel-air mixture having a third fuel-to-air ratio, wherein the third combustion zone comprises an inner surface configured to facilitate a vortex flow of the third fuel-air mixture introduced into the third combustion zone.  
   
   
       27 . The gas-turbine device as recited in  claim 26 , further comprises a second ignition source disposed in the third combustion zone of the combustion chamber of the second stage combustor assembly, wherein the second ignition source ignites the third fuel-air mixture to produce combustion gases, wherein the combustion gases mix with first combustion gases to produce second combustion gases at the combustion chamber of the second stage combustor assembly.  
   
   
       28 . A method of providing combustion gases for a gas-turbine device, the method comprising: 
 supplying fuel and compressed air to a first premix chamber of a combustor assembly;    producing a first fuel-air mixture having a first fuel-to-air ratio in the first premix chamber via the supplied fuel and compressed air;    routing the first fuel-air mixture to a first combustion zone of a combustion chamber of the combustor assembly;    supplying fuel and compressed air to a second premix chamber of the combustor assembly;    producing a second fuel-air mixture having a second fuel-to-air ratio in the second premix chamber via the supplied fuel and compressed air;    routing the second fuel-air mixture to a second combustion zone of the combustion chamber of the combustor assembly, wherein the second combustion zone is disposed radially outboard of the first combustion zone; and    generating a vortex flow of the second fuel-air mixture in the second combustion zone.    
   
   
       29 . The method as recited in  claim 28 , further comprising supplying a fuel to a diffusion chamber of the combustor assembly and routing the fuel to the second combustion zone of the combustion chamber of the combustor assembly.  
   
   
       30 . The method as recited in  claim 29 , further comprising igniting the fuel and the second fuel-air mixture to produce a flame and combustion gases.  
   
   
       31 . The method as recited in  claim 29 , further comprising igniting the first fuel-air mixture using the flame to produce first combustion gases.  
   
   
       32 . A method of providing combustion gases for a gas-turbine device, the method comprising: 
 igniting a first fuel-air mixture in a combustion chamber of a first stage combustor assembly to produce first combustion gases;    routing the first combustion gases to a third combustion zone of a combustion chamber of a second stage combustor assembly;    supplying fuel and compressed air to a third premix chamber of the second stage combustor assembly;    producing a third fuel-air mixture having a third fuel-to-air ratio in the third premix chamber of the second stage combustor assembly via the supplied fuel and compressed air;    routing the third fuel-air mixture to a third combustion zone of the combustion chamber of the second stage combustor assembly;    generating a vortex flow of the third fuel-air mixture in the third combustion zone of the combustion chamber of the second stage combustor assembly; and    igniting the third fuel-air mixture to generate a combustion gases and a flame, wherein the combustion gases mix with the first combustion gases to produce second combustion gases.