The RL10-IIB engine, a derivative of the RLIO, is capable of multi-mode thrust operation. This engine operates at two low thrust levels: tank head idle (THI), which is approximately 1 to 2 percent of full thrust, and pumped idle (PI), which is 10 percent of full thrust. Operation at THI provides vehicle propellant settling thrust and efficient engine thermal conditioning; PI operation provides vehicle tank pre-pressurization and maneuver thrust for log-g deployment. Stable combustion of the RL10-IIB engine at THI and PI thrust levels can be accomplished by providing gaseous oxygen at the propellant injector. Using gaseous hydrogen from the thrust chamber jacket as an energy source, a heat exchanger can be used to vaporize liquid oxygen without creating flow instability. This report summarizes the design and analysis of a United Aircraft Products (UAP) low-rate heat transfer heat exchanger concept for the RL10-IIB rocket engine. The design represents a second iteration of the RL10-IIB heat exchanger investigation program. The design and analysis of the first heat exchanger effort is presented in more detail in NASA CR-174857. Testing of the previous design is detailed in NASA CR-179487.


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    Title :

    Low Heat Transfer Oxidizer Heat Exchanger Design and Analysis


    Contributors:
    P. G. Kanic (author) / T. D. Kmiec (author) / R. J. Peckham (author)

    Publication date :

    1987


    Size :

    51 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Low heat transfer oxidizer heat exchanger design and analysis

    Kanic, P. G. / Kmiec, T. D. / Peckham, R. J. | NTRS | 1987


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    Nonuniform Heat Transfer Coefficients for Heat Exchanger Thermal Design

    Shah, R. K. / Assembly of World Conferences on Experimental Heat Transfer, Fluid Mechanics and Thermodynamics / American Society of Mechanical Engineers | British Library Conference Proceedings | 1993