The continuing improvement of aircraft gas turbine engine operating efficiencies involves increases in overall engine pressure ratio increases that will result in combustor inlet pressure and temperature increases, greater combustion temperature rises, and higher combustor exit temperatures. These conditions entail the development of fuel injectors generating uniform circumferential and radial temperature patterns, as well as combustor liner configurations and materials capable of withstanding increased thermal radiation even as the amount of cooling air is reduced. Low NO(x)-emitting combustor concepts are required which will employ staged combustion. The development status of component technologies answering these requirements are presently evaluated.


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    Title :

    Combustor technology for future aircraft


    Contributors:

    Conference:

    Joint Propulsion Conference ; 1990 ; Orlando, FL, United States


    Publication date :

    1990-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Combustor technology for future aircraft

    Tacina, Robert R. | NTRS | 1990


    Combustor technology for future aircraft

    TACINA, ROBERT | AIAA | 1990