The fixed geometry for the three combination turbofan-ramjet engines is defined; i.e., the definition of the combustion chamber and flow mixer throat cross-sectional areas from general considerations such as the same ratio between corrected thrust at Mach Number sub zero = 3 and thrust at take-off, without reheat, and optimum efficiency of the mixer-diffuser-pilot burner assembly for minimum bulk. A parametric study performed under sea level static and transonic conditions scanned the whole fan-compressor operating field in order to define the primary exit cross-sectional area. After a configuration was specified, an examination followed of the possible operating fields during supersonic acceleration and of the influence on flight range from the mixer throat-sectional area, primary flow exit sectional area, and turbofan rating. Subsonic flight at various turbofan ratings without heating in the combustion chamber also was studied. The internal flow thermodynamic characteristics -- pressure, temperature, and speed values -- are given for the specified configuration and operation at maximum heating and turbofan ratings. (Author)


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    Title :

    Turbofan-Ramjet Engine Studies. Volume III. Calculated Results


    Contributors:
    P. Chaulin (author) / P. Sandre (author)

    Publication date :

    1964


    Size :

    282 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Turbofan-Ramjet Engine Studies. Volume VII. Drawings

    P. Chaulin / P. Sandre | NTIS | 1964




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    Олег Владимирович Кислов / Михаил Анатольевич Шевченко | DOAJ | 2020

    Free access