Priming event peak pressures in liquid propulsion systems

Jeffrey David Moore, Joshua Gilbert, Bryce Brindle, Grant Alexander Risha

Research output: Contribution to journalArticle

Abstract

An experimental study was conducted to evaluate pressure transient levels in unrestricted and restricted liquid monopropellant propulsion system configurations and propellant manifolds generated by water hammer effects resulting from a priming event. This was accomplished through the development of a priming event experimental setup using distilled water as a propellant simulant for hydrazine. Multiple test elements were evaluated using different internal diameters, line lengths, manifold layouts, and flow control valves at atmospheric, subatmospheric, and low-pressure pretest pressure levels. The goals of the research were to determine the influence of restrictions in a liquid propulsion system, as well as the propellant manifold design, in the mitigation of the priming event maximum pressure levels. Based upon experimental results, it was determined that the internal diameter, line length, valve flow coefficient, and pretest pressure level all contributed to the pressure magnitude of the priming event. It was also observed that peak water hammer pressure levels might be significantly minimized and equally distributed throughout a propulsion system manifold using an inline cavitating venturi and manifold layout promoting free flow of the fluid, which was independent of the line geometry, the valve flow coefficient, and the valve opening response time.

Original languageEnglish (US)
Pages (from-to)899-909
Number of pages11
JournalJournal of Spacecraft and Rockets
Volume56
Issue number3
DOIs
StatePublished - Jan 1 2019

Fingerprint

priming
propulsion
Propulsion
propellants
water hammer
liquid
flow coefficients
Liquids
liquids
Propellants
propulsion system configurations
Water hammer
layouts
monopropellants
transient pressures
control valves
lines (geometry)
free flow
hydrazines
Monopropellants

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

Cite this

@article{ee7c35b2595e4c609f747623ffe39eb2,
title = "Priming event peak pressures in liquid propulsion systems",
abstract = "An experimental study was conducted to evaluate pressure transient levels in unrestricted and restricted liquid monopropellant propulsion system configurations and propellant manifolds generated by water hammer effects resulting from a priming event. This was accomplished through the development of a priming event experimental setup using distilled water as a propellant simulant for hydrazine. Multiple test elements were evaluated using different internal diameters, line lengths, manifold layouts, and flow control valves at atmospheric, subatmospheric, and low-pressure pretest pressure levels. The goals of the research were to determine the influence of restrictions in a liquid propulsion system, as well as the propellant manifold design, in the mitigation of the priming event maximum pressure levels. Based upon experimental results, it was determined that the internal diameter, line length, valve flow coefficient, and pretest pressure level all contributed to the pressure magnitude of the priming event. It was also observed that peak water hammer pressure levels might be significantly minimized and equally distributed throughout a propulsion system manifold using an inline cavitating venturi and manifold layout promoting free flow of the fluid, which was independent of the line geometry, the valve flow coefficient, and the valve opening response time.",
author = "Moore, {Jeffrey David} and Joshua Gilbert and Bryce Brindle and Risha, {Grant Alexander}",
year = "2019",
month = "1",
day = "1",
doi = "10.2514/1.A34393",
language = "English (US)",
volume = "56",
pages = "899--909",
journal = "Journal of Spacecraft and Rockets",
issn = "0022-4650",
publisher = "American Institute of Aeronautics and Astronautics Inc. (AIAA)",
number = "3",

}

Priming event peak pressures in liquid propulsion systems. / Moore, Jeffrey David; Gilbert, Joshua; Brindle, Bryce; Risha, Grant Alexander.

In: Journal of Spacecraft and Rockets, Vol. 56, No. 3, 01.01.2019, p. 899-909.

Research output: Contribution to journalArticle

TY - JOUR

T1 - Priming event peak pressures in liquid propulsion systems

AU - Moore, Jeffrey David

AU - Gilbert, Joshua

AU - Brindle, Bryce

AU - Risha, Grant Alexander

PY - 2019/1/1

Y1 - 2019/1/1

N2 - An experimental study was conducted to evaluate pressure transient levels in unrestricted and restricted liquid monopropellant propulsion system configurations and propellant manifolds generated by water hammer effects resulting from a priming event. This was accomplished through the development of a priming event experimental setup using distilled water as a propellant simulant for hydrazine. Multiple test elements were evaluated using different internal diameters, line lengths, manifold layouts, and flow control valves at atmospheric, subatmospheric, and low-pressure pretest pressure levels. The goals of the research were to determine the influence of restrictions in a liquid propulsion system, as well as the propellant manifold design, in the mitigation of the priming event maximum pressure levels. Based upon experimental results, it was determined that the internal diameter, line length, valve flow coefficient, and pretest pressure level all contributed to the pressure magnitude of the priming event. It was also observed that peak water hammer pressure levels might be significantly minimized and equally distributed throughout a propulsion system manifold using an inline cavitating venturi and manifold layout promoting free flow of the fluid, which was independent of the line geometry, the valve flow coefficient, and the valve opening response time.

AB - An experimental study was conducted to evaluate pressure transient levels in unrestricted and restricted liquid monopropellant propulsion system configurations and propellant manifolds generated by water hammer effects resulting from a priming event. This was accomplished through the development of a priming event experimental setup using distilled water as a propellant simulant for hydrazine. Multiple test elements were evaluated using different internal diameters, line lengths, manifold layouts, and flow control valves at atmospheric, subatmospheric, and low-pressure pretest pressure levels. The goals of the research were to determine the influence of restrictions in a liquid propulsion system, as well as the propellant manifold design, in the mitigation of the priming event maximum pressure levels. Based upon experimental results, it was determined that the internal diameter, line length, valve flow coefficient, and pretest pressure level all contributed to the pressure magnitude of the priming event. It was also observed that peak water hammer pressure levels might be significantly minimized and equally distributed throughout a propulsion system manifold using an inline cavitating venturi and manifold layout promoting free flow of the fluid, which was independent of the line geometry, the valve flow coefficient, and the valve opening response time.

UR - http://www.scopus.com/inward/record.url?scp=85066308366&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=85066308366&partnerID=8YFLogxK

U2 - 10.2514/1.A34393

DO - 10.2514/1.A34393

M3 - Article

AN - SCOPUS:85066308366

VL - 56

SP - 899

EP - 909

JO - Journal of Spacecraft and Rockets

JF - Journal of Spacecraft and Rockets

SN - 0022-4650

IS - 3

ER -