Opposed flow combustor

Abstract

In accordance with one embodiment of the present invention a combustor is provided. The combustor includes a combustion chamber having a first inlet adapted to provide a first air flow to the combustion chamber in a first direction, a fuel controller adapted to provide a fuel flow to the combustion chamber in the first direction, an opposing inlet adapted to provide an opposing air flow to the combustion chamber in a second direction generally in opposition to the first direction and wherein the first air flow and the fuel flow interact with the opposing air flow to form a stagnation zone in the combustion chamber.

1 . A combustor, comprising: 
 a combustion chamber;    a first inlet adapted to provide a first air flow to the combustion chamber in a first direction;    a fuel controller adapted to provide a fuel flow to the combustion chamber in the first direction;    an opposing inlet adapted to provide an opposing air flow to the combustion chamber in a second direction generally in opposition to the first direction; and    wherein the first air flow and the fuel flow interact with the opposing air flow to form a stagnation zone in the combustion chamber.    
   
   
       2 . The combustor as recited in  claim 1 , wherein the fuel controller is adapted to provide an opposing fuel flow to the combustion chamber in the second direction.  
   
   
       3 . The combustor as recited in  claim 2 , wherein the opposing air flow and the opposing fuel flow are premixed before being provided to the combustion chamber.  
   
   
       4 . The combustor as recited in  claim 2 , wherein the opposing air flow and the opposing fuel flow are partially premixed before being provided to the combustion chamber.  
   
   
       5 . The combustor as recited in  claim 2 , wherein the opposing air flow and the opposing fuel flow are fully premixed before being provided to the combustion chamber.  
   
   
       6 . The combustor as recited in  claim 1 , wherein the first air flow and the fuel flow are partially premixed before being provided to the combustion chamber.  
   
   
       7 . The combustor as recited in  claim 1 , wherein the first air flow and the opposing air flow are created from a single air flow received from a compressor.  
   
   
       8 . The combustor as recited in  claim 1 , wherein the first inlet extends into the combustion chamber.  
   
   
       9 . The combustor as recited in  claim 1 , wherein the opposing inlet extends into the combustion chamber.  
   
   
       10 . The combustor as recited in  claim 1 , wherein the combustion chamber comprises a perforated wall adapted to receive the opposing air flow before the opposing air flow reaches the stagnation zone.  
   
   
       11 . The combustor as recited in  claim 1 , wherein the fuel controller is adapted to control a velocity of the opposing air flow to move the stagnation zone within the combustion chamber.  
   
   
       12 . The combustor as recited in  claim 11 , wherein the velocity of the opposing air flow is controlled by fluidic means.  
   
   
       13 . The combustor as recited in  claim 1 , wherein combustion within the combustion chamber results in a combusted gas flow that exits the combustion chamber upstream relative to the first direction from the stagnation zone.  
   
   
       14 . The combustor as recited in  claim 13 , wherein a direction in which the combusted gas flow exits the combustion chamber is not coaxial with the first direction.  
   
   
       15 . A gas turbine system, comprising: 
 at least one compressor stage adapted to provide compressed air;    a combustion chamber adapted to receive the compressed air and to create a first air flow and an opposing airflow therefrom;    a first inlet adapted to receive the first air flow and a fuel flow into the combustion chamber in a first direction;    an opposing inlet adapted to receive the opposing air flow into the combustion chamber in a second direction generally in opposition to the first direction, wherein the first air flow and the fuel flow interact with the opposing air flow to form a stagnation zone in the combustion chamber; and    at least one turbine stage adapted to receive a combusted gas flow created by a combustion in the combustion chamber.    
   
   
       16 . The gas turbine system recited in  claim 15 , comprising a fuel controller adapted to provide an opposing fuel flow to the combustion chamber in the second direction.  
   
   
       17 . The gas turbine system recited in  claim 15 , wherein the first air flow and the fuel flow are partially premixed before being provided to the combustion chamber.  
   
   
       18 . The gas turbine system recited in  claim 15 , wherein the first inlet extends into the combustion chamber.  
   
   
       19 . The gas turbine system recited in  claim 15 , wherein the opposing inlet extends into the combustion chamber.  
   
   
       20 . The gas turbine system recited in  claim 15 , wherein the combustion chamber comprises a perforated wall adapted to receive the opposing air flow before the opposing air flow reaches the stagnation zone.  
   
   
       21 . The gas turbine system recited in  claim 15 , comprising a fuel controller that is adapted to control a velocity of the opposing air flow to move the stagnation zone within the combustion chamber.  
   
   
       22 . The combustor as recited in  claim 21 , wherein the velocity of the opposing air flow is controlled by fluidic means.  
   
   
       23 . A method of operating a combustion chamber, the method comprising: 
 injecting a first air flow and a fuel flow into the combustion chamber in a first direction; and    injecting an opposing air flow into the combustion chamber in opposition to the first air flow to form a stagnation zone in the combustion chamber.    
   
   
       24 . The method recited in  claim 23 , comprising injecting an opposing fuel flow into the combustion chamber in opposition to the first air flow.  
   
   
       25 . The method recited in  claim 24 , comprising premixing the opposing air flow and the opposing fuel flow.  
   
   
       26 . The method recited in  claim 24 , comprising partially premixing the opposing air flow and the opposing fuel flow.  
   
   
       27 . The method recited in  claim 24 , comprising fully premixing the opposing air flow and the opposing fuel flow.  
   
   
       28 . The method recited in  claim 23 , comprising partially premixing the first air flow and the fuel flow.  
   
   
       29 . The method recited in  claim 23 , comprising adjusting a velocity of the opposing air flow to control a location of the stagnation zone within the combustion chamber.  
   
   
       30 . The method recited in  claim 29 , wherein the velocity of the opposing air flow is controlled by fluidic means.  
   
   
       31 . The method recited in  claim 23 , comprising directing the opposing air flow through a perforated plate before the opposing air flow reaches the stagnation zone.  
   
   
       32 . The method recited in  claim 23 , comprising combusting a mixture in the combustion chamber to create a combusted gas flow that exits the combustion chamber upstream relative to the first direction from the stagnation zone.  
   
   
       33 . The method recited in  claim 32 , wherein a direction in which the combusted gas flow exits the combustion chamber is not coaxial with the first direction.