Gas turbine engine combustor with tailored temperature profile

Abstract

A method of tailoring a combustor flow for a gas turbine engine includes controlling an airflow into a swirler to be generally uniform and controlling an airflow into a quench zone to provide a desired pattern factor.

What is claimed is: 
     
         1 . A method of tailoring a combustor flow for a gas turbine engine, comprising:
 controlling an airflow into a swirler; and   controlling an airflow into a quench zone to provide a desired pattern factor.   
     
     
         2 . The method as recited in  claim 1 , further comprising: controlling the airflow into the swirler to be generally uniform. 
     
     
         3 . The method as recited in  claim 1 , further comprising: controlling a fuel-air mixture to be generally uniform downstream of the swirler. 
     
     
         4 . The method as recited in  claim 1 , further comprising: controlling the airflow into the swirler to increase fuel uniformity. 
     
     
         5 . The method as recited in  claim 1 , further comprising: trimming the airflow into the quench zone to achieve a desired radial profile. 
     
     
         6 . The method as recited in  claim 5 , further comprising: controlling the airflow into the quench zone to reduce said desired radial profile in a 5%-25% span region. 
     
     
         7 . The method as recited in  claim 1 , further comprising: controlling the airflow into the quench zone with a multiple of trim holes downstream of a quench hole. 
     
     
         8 . A method of tailoring a combustor flow for a gas turbine engine, comprising:
 controlling interaction of a fuel-air mixture from a swirler with an airflow into a quench zone.   
     
     
         9 . The method as recited in  claim 8 , further comprising: controlling the swirler interaction with a quench zone to increase fuel uniformity. 
     
     
         10 . The method as recited in  claim 8 , further comprising: uniformly distributing airflow to the swirler. 
     
     
         11 . The method as recited in  claim 8 , further comprising: trimming an airflow into the quench zone. 
     
     
         12 . The method as recited in  claim 8 , further comprising: providing a pattern factor below approximately 0.3. 
     
     
         13 . The method as recited in  claim 8 , further comprising: providing a profile factor below approximately 0.12.