Propellant atomization for porous injectors

J. C. Deeken; D. I. Suslov; M. Oschwald; S. Schlechtriem; O. J. Haidn

doi:10.2514/1.B37569

Propellant atomization for porous injectors

J. C. Deeken, D. I. Suslov, M. Oschwald, S. Schlechtriem, O. J. Haidn

Chair of Space Mobility and Propulsion

Deutsches Zentrum für Luft- und Raumfahrt (DLR)

Research output: Contribution to journal › Article › peer-review

1 Scopus citations

Abstract

Porous injectors represent an alternative injection concept to coaxial injectors for rocket engine applications using gas/liquid propellant combinations such as liquid oxygen (LOX)/hydrogen (H₂ ). This paper summarizes the main design features of porous injectors and proposes a mechanism of atomization for porous injectors that is considerably different to the atomization mechanism for coaxial injectors. The results of hot-fire test campaigns are presented, in which several parameters relevant to the injection process were varied: the injection velocities and momentum fluxes, the combustion chamber Mach number at the beginning of the nozzle contraction, and the LOX injector diameter. All hot-fire tests were conducted at P8 test facility for high pressure combustion research at the DLR site of Lampoldshausen with 50-mm-diameter combustion chambers operated with LOX∕H₂ at sub-and supercritical chamber pressures between 30 and 100 bar. The results presented here are supporting the proposed mechanism of atomization and allow derivation of some general design guidelines for porous injectors.

Original language	English
Pages (from-to)	1116-1126
Number of pages	11
Journal	Journal of Propulsion and Power
Volume	35
Issue number	6
DOIs	https://doi.org/10.2514/1.B37569
State	Published - 2019

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title = "Propellant atomization for porous injectors",

abstract = "Porous injectors represent an alternative injection concept to coaxial injectors for rocket engine applications using gas/liquid propellant combinations such as liquid oxygen (LOX)/hydrogen (H2 ). This paper summarizes the main design features of porous injectors and proposes a mechanism of atomization for porous injectors that is considerably different to the atomization mechanism for coaxial injectors. The results of hot-fire test campaigns are presented, in which several parameters relevant to the injection process were varied: the injection velocities and momentum fluxes, the combustion chamber Mach number at the beginning of the nozzle contraction, and the LOX injector diameter. All hot-fire tests were conducted at P8 test facility for high pressure combustion research at the DLR site of Lampoldshausen with 50-mm-diameter combustion chambers operated with LOX∕H2 at sub-and supercritical chamber pressures between 30 and 100 bar. The results presented here are supporting the proposed mechanism of atomization and allow derivation of some general design guidelines for porous injectors.",

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AU - Deeken, J. C.

AU - Suslov, D. I.

AU - Oschwald, M.

AU - Schlechtriem, S.

AU - Haidn, O. J.

PY - 2019

Y1 - 2019

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AB - Porous injectors represent an alternative injection concept to coaxial injectors for rocket engine applications using gas/liquid propellant combinations such as liquid oxygen (LOX)/hydrogen (H2 ). This paper summarizes the main design features of porous injectors and proposes a mechanism of atomization for porous injectors that is considerably different to the atomization mechanism for coaxial injectors. The results of hot-fire test campaigns are presented, in which several parameters relevant to the injection process were varied: the injection velocities and momentum fluxes, the combustion chamber Mach number at the beginning of the nozzle contraction, and the LOX injector diameter. All hot-fire tests were conducted at P8 test facility for high pressure combustion research at the DLR site of Lampoldshausen with 50-mm-diameter combustion chambers operated with LOX∕H2 at sub-and supercritical chamber pressures between 30 and 100 bar. The results presented here are supporting the proposed mechanism of atomization and allow derivation of some general design guidelines for porous injectors.

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Propellant atomization for porous injectors

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