Mixer retention

Abstract

Aspects of the disclosure are directed to methods and systems associated with a gas turbine engine of an aircraft. In some embodiments, a surface of a liner of the gas turbine engine is coupled to a fuel/air mixer, and a surface of a panel of the engine is coupled to the mixer such that a portion of the mixer is disposed between the liner surface and the panel surface.

What is claimed is: 
     
         1 . A method comprising:
 coupling a surface of a liner of a gas turbine engine of an aircraft to a fuel/air mixer; and   coupling a surface of a panel of the engine to the mixer such that a portion of the mixer is disposed between the liner surface and the panel surface.   
     
     
         2 . The method of  claim 1 , further comprising:
 coupling the panel to the liner.   
     
     
         3 . The method of  claim 1 , further comprising:
 bolting the panel to at least one of the liner, the mixer, and a body of the aircraft.   
     
     
         4 . The method of  claim 1 , further comprising:
 decoupling the panel from the mixer.   
     
     
         5 . The method of  claim 4 , further comprising:
 servicing at least one of the liner and the mixer.   
     
     
         6 . The method of  claim 5 , wherein servicing the at least one of the liner and the mixer comprises repairing the at least one of the liner and the mixer. 
     
     
         7 . The method of  claim 5 , wherein servicing the at least one of the liner and the mixer comprises replacing the at least one of the liner and the mixer. 
     
     
         8 . The method of  claim 5 , further comprising:
 recoupling the panel subsequent to the servicing.   
     
     
         9 . The method of  claim 1 , wherein the portion of the mixer that is disposed between the liner and the panel corresponds to a flange of the mixer. 
     
     
         10 . A system comprising:
 a liner of a gas turbine engine of an aircraft;   a panel of the engine; and   a fuel/air mixer associated with a combustion chamber of the aircraft,   wherein a portion of the mixer is disposed between a surface of the liner and a surface of the panel.   
     
     
         11 . The system of  claim 10 , wherein the liner comprises sheet metal. 
     
     
         12 . The system of  claim 10 , wherein the panel is at least one of cast and molded. 
     
     
         13 . The system of  claim 10 , wherein the portion of the mixer at is disposed between the liner and the panel comprises a flange of the mixer. 
     
     
         14 . The system of  claim 10 , wherein the mixer is configured to have a conical shape to match a conical shape of the panel. 
     
     
         15 . The system of  claim 10 , wherein the liner is configured to have a flat surface, and wherein the panel and the mixer are configured to have flat, circular shapes. 
     
     
         16 . The system of  claim 10 , wherein the mixer is a swirler.