Comparison of nozzle throat erosion behavior in a solid-propellant rocket motor and a simulator

Brian Evans, Kenneth K. Kuo, Eric Boyd, Andrew Claude Cortopassi

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

    16 Citations (Scopus)

    Abstract

    The performance deterioration of solid-rocket motors caused by nozzle throat erosion becomes more severe with increased operating pressure from higher rates of heat and mass transfer from the core flow to the nozzle surface. Understanding of the rocket nozzle throat erosion processes and developing methods for mitigation of erosion rate can allow motor operation pressures to be substantially higher than those of the existing propulsion systems. Two test rigs have been utilized in the study of nozzle throat erosion phenomena for G-90 grade graphite; an instrumented solid propellant motor (ISPM) and a solid-propellant rocket motor simulator (RMS). The X-ray translucent nozzle assembly used for the RMS and ISPM allows the real-time imaging of the nozzle-throat station. It also has the feature for incorporating a nozzle boundary-layer control system (NBLCS) to mitigate nozzle-throat erosion rates. The RMS is a gaseous reactant combustor, allows for control of product species compositions, their flow rates, and combustor operating pressure. The erosion process of G-90 graphite was also evaluated in the ISPM using both non-metallized and metallized composite solid propellants. Tests conducted at operating pressures around 21 MPa showed greatly reduced nozzle throat erosion rate when the NBLCS was utilized. A dimensionless nozzle-throat erosion rate correlation was developed in terms of the effective oxidizer mass fraction, chamber pressure, Reynolds number, and relative boundary layer thickness. The correlation equation accurately predicts erosion rate data measured in the RMS and the ISPM for both non-metallized and metallized propellants over a wide range of operating conditions. The calculated erosion rates from the correlation showed agreement within ± 0.05 mm/s of the experimentally determined values.

    Original languageEnglish (US)
    Title of host publication45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
    StatePublished - Dec 1 2009
    Event45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit - Denver, CO, United States
    Duration: Aug 2 2009Aug 5 2009

    Publication series

    Name45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

    Other

    Other45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
    CountryUnited States
    CityDenver, CO
    Period8/2/098/5/09

    Fingerprint

    solid rocket propellants
    Solid propellants
    throats
    Rocket engines
    nozzles
    simulators
    erosion
    simulator
    erosion rate
    Erosion
    Nozzles
    Simulators
    solid propellants
    rockets
    boundary layer
    boundary layer control
    graphite
    control system
    Boundary layers
    combustion chambers

    All Science Journal Classification (ASJC) codes

    • Aerospace Engineering
    • Control and Systems Engineering
    • Space and Planetary Science
    • Energy(all)
    • Electrical and Electronic Engineering
    • Mechanical Engineering

    Cite this

    Evans, B., Kuo, K. K., Boyd, E., & Cortopassi, A. C. (2009). Comparison of nozzle throat erosion behavior in a solid-propellant rocket motor and a simulator. In 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit (45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit).
    Evans, Brian ; Kuo, Kenneth K. ; Boyd, Eric ; Cortopassi, Andrew Claude. / Comparison of nozzle throat erosion behavior in a solid-propellant rocket motor and a simulator. 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2009. (45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit).
    @inproceedings{335b1ac0c27e4543a512a64878f59f2d,
    title = "Comparison of nozzle throat erosion behavior in a solid-propellant rocket motor and a simulator",
    abstract = "The performance deterioration of solid-rocket motors caused by nozzle throat erosion becomes more severe with increased operating pressure from higher rates of heat and mass transfer from the core flow to the nozzle surface. Understanding of the rocket nozzle throat erosion processes and developing methods for mitigation of erosion rate can allow motor operation pressures to be substantially higher than those of the existing propulsion systems. Two test rigs have been utilized in the study of nozzle throat erosion phenomena for G-90 grade graphite; an instrumented solid propellant motor (ISPM) and a solid-propellant rocket motor simulator (RMS). The X-ray translucent nozzle assembly used for the RMS and ISPM allows the real-time imaging of the nozzle-throat station. It also has the feature for incorporating a nozzle boundary-layer control system (NBLCS) to mitigate nozzle-throat erosion rates. The RMS is a gaseous reactant combustor, allows for control of product species compositions, their flow rates, and combustor operating pressure. The erosion process of G-90 graphite was also evaluated in the ISPM using both non-metallized and metallized composite solid propellants. Tests conducted at operating pressures around 21 MPa showed greatly reduced nozzle throat erosion rate when the NBLCS was utilized. A dimensionless nozzle-throat erosion rate correlation was developed in terms of the effective oxidizer mass fraction, chamber pressure, Reynolds number, and relative boundary layer thickness. The correlation equation accurately predicts erosion rate data measured in the RMS and the ISPM for both non-metallized and metallized propellants over a wide range of operating conditions. The calculated erosion rates from the correlation showed agreement within ± 0.05 mm/s of the experimentally determined values.",
    author = "Brian Evans and Kuo, {Kenneth K.} and Eric Boyd and Cortopassi, {Andrew Claude}",
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    Evans, B, Kuo, KK, Boyd, E & Cortopassi, AC 2009, Comparison of nozzle throat erosion behavior in a solid-propellant rocket motor and a simulator. in 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Denver, CO, United States, 8/2/09.

    Comparison of nozzle throat erosion behavior in a solid-propellant rocket motor and a simulator. / Evans, Brian; Kuo, Kenneth K.; Boyd, Eric; Cortopassi, Andrew Claude.

    45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2009. (45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit).

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

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    PY - 2009/12/1

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    N2 - The performance deterioration of solid-rocket motors caused by nozzle throat erosion becomes more severe with increased operating pressure from higher rates of heat and mass transfer from the core flow to the nozzle surface. Understanding of the rocket nozzle throat erosion processes and developing methods for mitigation of erosion rate can allow motor operation pressures to be substantially higher than those of the existing propulsion systems. Two test rigs have been utilized in the study of nozzle throat erosion phenomena for G-90 grade graphite; an instrumented solid propellant motor (ISPM) and a solid-propellant rocket motor simulator (RMS). The X-ray translucent nozzle assembly used for the RMS and ISPM allows the real-time imaging of the nozzle-throat station. It also has the feature for incorporating a nozzle boundary-layer control system (NBLCS) to mitigate nozzle-throat erosion rates. The RMS is a gaseous reactant combustor, allows for control of product species compositions, their flow rates, and combustor operating pressure. The erosion process of G-90 graphite was also evaluated in the ISPM using both non-metallized and metallized composite solid propellants. Tests conducted at operating pressures around 21 MPa showed greatly reduced nozzle throat erosion rate when the NBLCS was utilized. A dimensionless nozzle-throat erosion rate correlation was developed in terms of the effective oxidizer mass fraction, chamber pressure, Reynolds number, and relative boundary layer thickness. The correlation equation accurately predicts erosion rate data measured in the RMS and the ISPM for both non-metallized and metallized propellants over a wide range of operating conditions. The calculated erosion rates from the correlation showed agreement within ± 0.05 mm/s of the experimentally determined values.

    AB - The performance deterioration of solid-rocket motors caused by nozzle throat erosion becomes more severe with increased operating pressure from higher rates of heat and mass transfer from the core flow to the nozzle surface. Understanding of the rocket nozzle throat erosion processes and developing methods for mitigation of erosion rate can allow motor operation pressures to be substantially higher than those of the existing propulsion systems. Two test rigs have been utilized in the study of nozzle throat erosion phenomena for G-90 grade graphite; an instrumented solid propellant motor (ISPM) and a solid-propellant rocket motor simulator (RMS). The X-ray translucent nozzle assembly used for the RMS and ISPM allows the real-time imaging of the nozzle-throat station. It also has the feature for incorporating a nozzle boundary-layer control system (NBLCS) to mitigate nozzle-throat erosion rates. The RMS is a gaseous reactant combustor, allows for control of product species compositions, their flow rates, and combustor operating pressure. The erosion process of G-90 graphite was also evaluated in the ISPM using both non-metallized and metallized composite solid propellants. Tests conducted at operating pressures around 21 MPa showed greatly reduced nozzle throat erosion rate when the NBLCS was utilized. A dimensionless nozzle-throat erosion rate correlation was developed in terms of the effective oxidizer mass fraction, chamber pressure, Reynolds number, and relative boundary layer thickness. The correlation equation accurately predicts erosion rate data measured in the RMS and the ISPM for both non-metallized and metallized propellants over a wide range of operating conditions. The calculated erosion rates from the correlation showed agreement within ± 0.05 mm/s of the experimentally determined values.

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    M3 - Conference contribution

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    Evans B, Kuo KK, Boyd E, Cortopassi AC. Comparison of nozzle throat erosion behavior in a solid-propellant rocket motor and a simulator. In 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2009. (45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit).