An experimental investigation was conducted to evaluate the effectiveness of using high-aspect-ratio cooling passenges to improve the life and reduce the colant pressure drop in high-pressure rocket thrust chambers. A plug-nozzle rocket-engine test apparatus was used to test two cylindrical chambers with low-aspect-ratio cooling passages and one with high-aspect-ratio cooling passages. The chambers were cyclically tested and data were taken over a wide range of coolant mass flows. The results showed that for the same coolant pressure drop, the hot-gas-side wall temperature of the high-aspect-ratio chamber was 30 percent lower than the baseline low-aspect-ratio chamber, resulting in no fatigue damage to the wall. The coolant pressure drop for the high-aspect-ratio chamber was reduced in increments to one-half that of the baseline chamber, by reducing the coolant mass flow, and still resulted in a reduction in the hot-gas-side wall temperature when compared to the low-aspect-ratio chambers.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    An experimental investigation of high-aspect-ratio cooling passages


    Contributors:

    Conference:

    Joint Propulsion Conference ; 1992 ; Nashville, TN, United States


    Publication date :

    1992-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    An experimental investigation of high-aspect-ratio cooling passages

    CARLILE, JULIE / QUENTMEYER, RICHARD | AIAA | 1992



    Experimental and Analytical Investigation of Local Heat Transfer in High Aspect Ratio Cooling Channels

    Neuner, F. / Preclik, D. / Popp, M. et al. | British Library Conference Proceedings | 1998



    Experimental investigation of a high-aspect-ratio supersonic inlet

    BALL, W. / SYBERG, J. / SURBER, L. | AIAA | 1981