This paper discusses the design, fabrication, and test of a window assembly for instrumentation of liquid-fueled rocket engine hot gas systems. The window was designed to allow optical measurements of hot gas in the SSME fuel preburner and appears to be the first window designed for application in a rocket engine hot gas system. Such a window could allow the use of a number of remote optical measurement technologies including: Raman temperature and species concentration measurement, Raleigh temperature measurements, flame emission monitoring, flow mapping, laser-induced florescence, and hardware imaging during engine operation. The window assembly has been successfully tested to 8,000 psi at 1000 F and over 11,000 psi at room temperature. A computer stress analysis shows the window will withstand high temperature and cryogenic thermal shock.


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    Titel :

    High-temperature, high-pressure optical port for rocket engine applications


    Beteiligte:
    Delcher, Ray (Autor:in) / Nemeth, ED (Autor:in) / Powers, W. T. (Autor:in)

    Kongress:

    AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit ; 1993 ; Monterey, CA, United States


    Erscheinungsdatum :

    1993-06-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    High-temperature, high-pressure optical port for rocket engine applications

    DELCHER, RAY / NEMETH, ED / POWERS, W. | AIAA | 1993


    High-Temperature Rocket Engine

    Schneider, Steven J. / Rosenberg, Sanders D. / Chazen, Melvin L. | NTRS | 1994


    High Chamber Pressure Reusable Rocket Engine Technology

    Kah, Carl L. C. | SAE Technical Papers | 1970


    A high pressure bipropellant micro-rocket engine

    London, A. / Epstein, A. / Kerrebrock, J. | AIAA | 2000