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    Fundamental Aspects of the Aerodynamics of Turbojet Engine Combustors (1978)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Aerodynamic considerations in the design of high performance combustors for turbojet engines are discussed. Aerodynamic problems concerning the preparation of the fuel-air mixture, the recirculation zone where primary combustion occurs, the secondary combustion zone, and the dilution zone were examined. An aerodynamic analysis of the entire primary chamber ensemble was carried out to determine the pressure drop between entry and exit. The aerodynamics of afterburn chambers are discussed. A model which can be used to investigate the evolution of temperature, pressure, and rate and efficiency of combustion the length of the chamber was developed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-75287 , ONERA-TP-1976
    Format: application/pdf
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