A review of aircraft gas turbine engine performance trends indicates that the smaller the engine the lower are its cycle pressure ratios, which suggests the less the combustor design challenge. This is often reflected in projected development effort. In fact, many aspects of combustor design and performance are adversely affected in smaller engines. Furthermore, when emission reduction requirements are extended to smaller engines, the design comprises needed to meet all performance goals will become particularly acute, and design solutions from large combustors may not be applicable.


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    Titel :

    Combustor Technology for Small Aircraft Engines


    Beteiligte:
    S. Howell (Autor:in)

    Erscheinungsdatum :

    1994


    Format / Umfang :

    9 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





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