TY - GEN
T1 - Numerical modeling of priming event peak pressures in liquid propulsion systems
AU - Moore, Jeffrey D.
AU - Risha, Grant A.
AU - Tiwari, Arpit
AU - Harrison, Jonathan
AU - Zenker, Jon
N1 - Funding Information:
The authors wish to thank the Penn State Altoona Research and Sponsored Programs Office and Mr. Corey Griffin for sponsoring the previous experimental internally-funded effort.
Publisher Copyright:
© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2019
Y1 - 2019
N2 - A numerical study was performed to determine the pressure transient levels in unrestricted liquid monopropellant propulsion system configurations and propellant manifolds generated from surge events during system priming. This was accomplished through the use of a commercial multi-physics system-level simulation software called GT-SUITE, which predicted the maximum peak priming event pressures in various liquid system configurations. Experimental data from multiple literature research efforts involving priming after the opening of a latch valve were evaluated using the numerical model to determine the accuracy of the results among various internal diameters, line lengths, manifold layouts, and flow control valves at different pre-test pressure levels in the system. Based upon the results, it was determined that the numerical model was a promising tool to predict liquid system pressure transient levels.
AB - A numerical study was performed to determine the pressure transient levels in unrestricted liquid monopropellant propulsion system configurations and propellant manifolds generated from surge events during system priming. This was accomplished through the use of a commercial multi-physics system-level simulation software called GT-SUITE, which predicted the maximum peak priming event pressures in various liquid system configurations. Experimental data from multiple literature research efforts involving priming after the opening of a latch valve were evaluated using the numerical model to determine the accuracy of the results among various internal diameters, line lengths, manifold layouts, and flow control valves at different pre-test pressure levels in the system. Based upon the results, it was determined that the numerical model was a promising tool to predict liquid system pressure transient levels.
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U2 - 10.2514/6.2019-4123
DO - 10.2514/6.2019-4123
M3 - Conference contribution
AN - SCOPUS:85095970532
SN - 9781624105906
T3 - AIAA Propulsion and Energy Forum and Exposition, 2019
BT - AIAA Propulsion and Energy Forum and Exposition, 2019
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Propulsion and Energy Forum and Exposition, 2019
Y2 - 19 August 2019 through 22 August 2019
ER -