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On porous liquid propellant rocket engine injectors

Lux, Johannes and Suslov, Dmitry and Haidn, Oskar (2008) On porous liquid propellant rocket engine injectors. Aerospace Science and Technology, 12 (6). Elsevier. DOI: 10.1016/j.ast.2007.11.004

Full text not available from this repository.

Abstract

A novel injection concept for cryogenic liquid propellant rocket engines has been tested and verified successfully using an optically accessible combustion chamber. The injector consists of a porous faceplate made from sinter metal and five LOX posts arranged in a classical parallel showerhead configuration. While liquid oxygen is injected at similar velocities known from typical coaxial injector elements, the fuel enters the combustion chamber at much lower velocities. The flame stabilization for both LOX/H2 and LOX/CH4 propellant combination has been investigated at sub-, near-, and supercritical pressures.

Item URL in elib:https://elib.dlr.de/52370/
Document Type:Article
Title:On porous liquid propellant rocket engine injectors
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Lux, JohannesUNSPECIFIEDUNSPECIFIED
Suslov, DmitryUNSPECIFIEDUNSPECIFIED
Haidn, OskarUNSPECIFIEDUNSPECIFIED
Date:2008
Journal or Publication Title:Aerospace Science and Technology
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:Yes
Volume:12
DOI :10.1016/j.ast.2007.11.004
Publisher:Elsevier
Status:Published
Keywords:high pressure, liquid propellant rocket engines, LOX methane hydrogen combustion, porous injection, subcritical supercritical
HGF - Research field:Aeronautics, Space and Transport (old)
HGF - Program:Space (old)
HGF - Program Themes:W - no assignment
DLR - Research area:Space
DLR - Program:W - no assignment
DLR - Research theme (Project):W - no assignment (old)
Location: Lampoldshausen
Institutes and Institutions:Institute of Space Propulsion > Technologie
Deposited By: Lux, Dr. Johannes
Deposited On:15 Aug 2008
Last Modified:27 Apr 2009 14:34

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