A boundary layer method previously developed for predicting the heat transfer to rocket nozzles is extended to the prediction of heat transfer rates inside the rocket combustion chamber. The important factor is shown to be the available enthalpy of the partly burned gases in the free stream. A mixing theory is presented which enables the rate of increase of available enthalpy to be calculated. The theory has been applied to some 524 experimental measurements, made over a range of propellent combinations and injector designs, and an overall rms deviation of approximately 15% is obtained. The effects of injector patterns on circumferential heat transfer rates and of combustion instability are also considered. (Author)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Convective Heat Transfer in Rocket Engines. Part 4. Heat Transfer in the Combustion Chamber


    Contributors:

    Publication date :

    1969


    Size :

    40 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English