System for directing airflow into a combustor

Abstract

A system includes a gas turbine combustor. The gas turbine combustor includes a combustion liner disposed about a combustion region and a sleeve disposed about the combustion liner. The combustion liner and the sleeve define an airflow passage circumferentially about the liner. The gas turbine combustor also includes multiple axial injectors configured to direct an airflow into the airflow passage in an axial direction facilitating a momentum exchange between an injection flow and a crossflow from an upstream portion of the combustor. The multiple axial injectors are asymmetrically configured to provide an uniform injection of the airflow circumferentially about an axis of the gas turbine combustor.

1 . A system, comprising:
 a gas turbine combustor, comprising:
 a combustion liner disposed about a combustion region; 
 a sleeve disposed about the combustion liner, wherein the combustion liner and the sleeve define an airflow passage circumferentially about the liner; and 
 a plurality of axial injectors configured to direct an airflow into the airflow passage in an axial direction facilitating a momentum exchange between an injection flow and a crossflow from an upstream portion of the combustor, wherein the plurality of axial injectors is asymmetrically configured to provide a uniform injection of the airflow circumferentially about an axis of the gas turbine combustor. 
   
     
     
         2 . The system of  claim 1 , wherein the system comprises a turbine engine having an axis of rotation, and the plurality of axial injectors is configured to increase an effective area for airflow injection further away from the axis of rotation. 
     
     
         3 . The system of  claim 2 , wherein a first injector of the plurality of axial injectors further away from the axis of rotation comprise a greater radial height than a second injector of the plurality axial injectors closer to the axis of rotation. 
     
     
         4 . The system of  claim 2 , wherein the plurality of axial injectors comprises an equal radial height, and a first injector of the plurality of axial injectors further away from the axis of rotation comprises a greater effective area for injection of the airflow into the airflow passage than a second injector of the plurality of axial injectors closer to the axis of rotation. 
     
     
         5 . The system of  claim 4 , wherein each injector of the plurality of axial injectors comprises an airflow area, and the first injector has a lesser number of struts through the airflow area than the second injector. 
     
     
         6 . The system of  claim 1 , wherein at least two axial injectors of the plurality of axial injectors comprise different radial heights. 
     
     
         7 . The system of  claim 1 , wherein at least two axial injectors of the plurality of axial injectors comprise different airflow areas for injection of the airflow into the airflow passage. 
     
     
         8 . The system of  claim 1 , wherein each injector of the plurality of axial injectors comprises an axial scoop disposed on a surface of the sleeve. 
     
     
         9 . The system of  claim 1 , wherein the combustor liner comprises a first axis and the sleeve comprises a second axis, and the first and second axes are offset from one another to define asymmetry in the airflow passage. 
     
     
         10 . The system of  claim 1 , wherein the system comprises a gas turbine engine having the gas turbine combustor. 
     
     
         11 . A system, comprising:
 an axial air injection system, comprising:
 a plurality of axial injectors configured to direct an airflow into an airflow passage defined by a sleeve disposed about a combustion liner surrounding a combustion region of a gas turbine combustor facilitating a momentum exchange between an injection flow and a crossflow from an upstream portion of the combustor, wherein the airflow passage is disposed circumferentially about the liner, and the plurality of axial injectors is asymmetrically configured to provide a uniform injection of the airflow circumferentially about an axis of the gas turbine combustor. 
   
     
     
         12 . The system of  claim 11 , wherein each injector of the plurality of axial injectors comprises an airflow area, and a first injector of the plurality of axial injectors has a lesser number of struts through the airflow area than a second injector of the plurality of axial injectors. 
     
     
         13 . The system of  claim 11 , wherein at least two axial injectors of the plurality of axial injectors comprise different radial heights. 
     
     
         14 . The system of  claim 11 , wherein at least two axial injectors of the plurality of axial injectors comprise different airflow areas for injection of the airflow into the airflow passage. 
     
     
         15 . The system of  claim 11 , wherein the system comprises a turbine engine having an axis of rotation, and the plurality of axial injectors is configured to increase an effective area for airflow injection further away from the axis of rotation. 
     
     
         16 . The system of  claim 15 , wherein a first injector of the plurality of axial injectors further away from the axis of rotation comprises a greater radial height than a second injector of the plurality of axial injectors closer to the axis of rotation. 
     
     
         17 . A system, comprising;
 a turbine engine, comprising:
 a compressor and a turbine having an axis of rotation; and 
 a combustor coupled to the compressor and the turbine, wherein the combustor comprises:
 a combustion liner disposed about a combustion region; 
 a sleeve disposed about the combustion liner, wherein the combustion liner and the sleeve define an airflow passage circumferentially about the liner; and 
 a plurality of axial injectors configured to direct an airflow into the airflow passage in an axial direction facilitating a momentum exchange between an injection flow and a crossflow from an upstream portion of the combustor, wherein the plurality of axial injectors is configured to increases an effective area for airflow injection further away from the axis of rotation. 
 
   
     
     
         18 . The system of  claim 17 , wherein the plurality of axial injectors is asymmetrically configured to provide a uniform injection of the airflow circumferentially about an axis of the combustor. 
     
     
         19 . The system of  claim 17 , wherein a first injector of the plurality of the plurality of axial injectors further away from the axis of rotation comprises a greater radial height than a second injector of the plurality of axial injectors closer to the axis of rotation. 
     
     
         20 . The system of  claim 17 , wherein the plurality of axial injectors comprises an equal radial height, and a first injector of the plurality of axial injectors further away from the axis of rotation comprises a greater effective area for injection of the airflow into the airflow passage than a second injector of the plurality of axial injectors closer to the axis of rotation.