A gas turbine engine has a combustor module including an annular combustor having a liner assembly that defines an annular combustion chamber having a length, L. The liner assembly includes a radially inner liner, a radially outer liner that circumscribes the inner liner, and a bulkhead, having a height, H1, which extends between the respective forward ends of the inner liner and the outer liner. The combustor has an exit height, H3, at the respective aft ends of the inner liner and the outer liner interior. The annular combustor has a ratio H1/H3 having a value less than or equal to 1.7. The annular combustor may also have a ration L/H3 having a value less than or equal to 6.0.


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    Title :

    Gas turbine combustor



    Publication date :

    2011-06-07


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




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    C. T. Norgren / S. M. Riddlebaugh | NTIS | 1983


    Small gas turbine combustor study - Combustor liner evaluation

    NORGREN, C. / RIDDLEBAUGH, S. | AIAA | 1983