The J-2X engine, a liquid oxygen/liquid hydrogen propellant rocket engine available for future use on the upper stage of the Space Launch System vehicle, has completed testing of three developmental engines at NASA Stennis Space Center. Twenty-one tests of engine E10001 were conducted from June 2011 through September 2012, thirteen tests of the engine E10002 were conducted from February 2013 through September 2013, and twelve tests of engine E10003 were conducted from November 2013 to April 2014. Verification of combustion stability of the thrust chamber assembly was conducted by perturbing each of the three developmental engines. The primary mechanism for combustion stability verification was examining the response caused by an artificial perturbation (bomb) in the main combustion chamber, i.e., dynamic combustion stability rating. No dynamic instabilities were observed in the TCA, although a few conditions were not bombed. Additional requirements, included to guard against spontaneous instability or rough combustion, were also investigated. Under certain conditions, discrete responses were observed in the dynamic pressure data. The discrete responses were of low amplitude and posed minimal risk to safe engine operability. Rough combustion analyses showed that all three engines met requirements for broad-banded frequency oscillations. Start and shutdown transient chug oscillations were also examined to assess the overall stability characteristics, with no major issues observed.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Combustion Stability Verification for the Thrust Chamber Assembly of J-2X Developmental Engines 10001, 10002, and 10003


    Beteiligte:
    Morgan, C. J. (Autor:in) / Hulka, J. R. (Autor:in) / Casiano, M. J. (Autor:in) / Kenny, R. J. (Autor:in) / Hinerman, T. D. (Autor:in) / Scholten, N. (Autor:in)

    Kongress:

    JANNAF Propulsion Meeting ; 2015 ; Nashville, TN, United States
    Spacecraft Propulsion Subcommittee ; 2015 ; Nashville, TN, United States
    Modeling and Simulation Subcommittee ; 2015 ; Nashville, TN, United States
    Liquid Propulsion Subcommittee ; 2015 ; Nashville, TN, United States


    Erscheinungsdatum :

    2015-06-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch






    Transpiration Cooled Ceramic Thrust Chamber Applicability for High-Thrust Rocket Engines

    Herbertz, Armin / Ortelt, Markus / Müller, Ilja et al. | AIAA | 2012


    The Thrust Chamber Assembly

    de Iaco Veris, Alessandro | Springer Verlag | 2020


    Design Verification Test Matrix Development for the STME Thrust Chamber Assembly

    C. E. Dexter / S. K. Elam / D. L. Sparks | NTIS | 1993