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Experimental Investigation of Porous Injectors for Liquid Propellant Rocket Engines

Lux, Johannes and Suslov, Dmitry and Haidn, Oskar (2008) Experimental Investigation of Porous Injectors for Liquid Propellant Rocket Engines. 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 2008-07-21 - 2008-07-23, Hartford, CT (USA).

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Three different injector heads have been tested using a LOX/H<sub>2</sub> subscale combustion chamber at the European High Pressure Research and Technology Test Facility P8. For reference purposes, a first configuration based on a classical shear coaxial injector head with 13 elements has been investigated. The second configuration consists of a planar porous faceplate made from sinter bronze and 68 implemented single LOX tubes. Hydrogen was injected through the porous faceplate whereas liquid oxygen enters the combustion chamber in a classical parallel showerhead configuration at moderate injection velocities. With the third configuration, a hemispherical shaped faceplate has been used in order to increase both the mechanical strength and the hydrogen injection area. In addition, the LOX tubes have been modified from a parallel to a far downstream impinging arrangement in order to enhance the combustor wall compatibility. Liquid oxygen was injected at 120 K whereas the hydrogen injection temperature was about 50 K with the porous configurations and about 90 K with the coaxial injector head. c*-efficiency data have been gathered as well as some basic information on the axial heat flux distribution during steady state operation. All three configurations have been operated at combustion chamber pressures up to 80 bar and propellant mixture ratios between 1.5 and 6. In addition to steady states, ramp-tests have been performed in order to investigate the throttling capabilities of the porous injectors.

Item URL in elib:https://elib.dlr.de/54888/
Document Type:Conference or Workshop Item (Speech, Paper)
Title:Experimental Investigation of Porous Injectors for Liquid Propellant Rocket Engines
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Date:July 2008
Refereed publication:No
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Keywords:high pressure, liquid propellant, rocket engine, injection, injector, porous, cryogenic, lox, hydrogen
Event Title:44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
Event Location:Hartford, CT (USA)
Event Type:international Conference
Event Dates:2008-07-21 - 2008-07-23
Organizer:American Institute of Aeronautics and Astronautics
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Space (old)
HGF - Program Themes:W RP - Raumtransport
DLR - Research area:Space
DLR - Program:W RP - Raumtransport
DLR - Research theme (Project):W - Antriebsystemtechnik - Schubkammertechnologie und Hochdruckverbrennung (old)
Location: Lampoldshausen
Institutes and Institutions:Institute of Space Propulsion > Technologie
Deposited By: Lux, Dr. Johannes
Deposited On:04 Aug 2008
Last Modified:27 Apr 2009 15:08

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