elib
DLR-Header
DLR-Logo -> http://www.dlr.de
DLR Portal Home | Imprint | Privacy Policy | Contact | Deutsch
Fontsize: [-] Text [+]

Combustion Performance and Stability of a Porous Injector Compared with a State-of-the-Art Coaxial Injector

Deeken, J. and Suslov, D. and Rackemann, N. and Preuss, A. (2014) Combustion Performance and Stability of a Porous Injector Compared with a State-of-the-Art Coaxial Injector. Space Propulsion 2014, 19. - 22. Mai 2014, Cologne, Germany.

Full text not available from this repository.

Abstract

Injector behavior is of utmost importance for the performance and stability of liquid rocket engines. The injection system has to provide for a highly e�cient mixing and consequent chemical reaction of the propellants at a minimum chamber length. This article presents results of the experimental investigation for a new injection concept based on the application of porous materials. Porous Injectors represent a novel method of propellant injection in liquid propellant rocket engines. Earlier investigations revealed their high potential for gas/liquid propellant combi- nations, e.g. LOX/H2. The simple and low-cost manufacturing process and the good behavior during throttling of this class of injectors are signi�cant advantages compared with coaxial injectors commonly employed for this propellant combination. The present study focusses on a direct experimental comparison of a 168-element porous injector (API) with an injector head equipped with 19 state-of-the-art coaxial injector elements comparable to Ariane 5`s Vulcain II engine. The hot �re tests were conducted at the P8 test bench in Lampoldshausen. An 80 mm diameter calorimeter combustion chamber built by Airbus DS and identical measurement equipment were used with both injector head con�gurations, allowing a direct comparison of the test data. The combustion performance, stability, the wall heat �ux and the axial pressure pro�le were determined for operating conditions typical of the operating regime of Vulcain II. This included combustion chamber pressures of up to 115 bar and oxidizer to fuel mixture ratios of 5.4 up to 7.2.

Item URL in elib:https://elib.dlr.de/91648/
Document Type:Conference or Workshop Item (Speech)
Title:Combustion Performance and Stability of a Porous Injector Compared with a State-of-the-Art Coaxial Injector
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Deeken, J.RA-RAK LAUNSPECIFIED
Suslov, D.RA-RAK LAUNSPECIFIED
Rackemann, N.Airbus, OttobrunnUNSPECIFIED
Preuss, A.Airbus, OttobrunnUNSPECIFIED
Date:2014
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:injector; liquid rocket engine
Event Title:Space Propulsion 2014
Event Location:Cologne, Germany
Event Type:international Conference
Event Dates:19. - 22. Mai 2014
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transport
DLR - Research area:Raumfahrt
DLR - Program:R RP - Raumtransport
DLR - Research theme (Project):R - Antriebsystemtechnik - Schubkammertechnologie
Location: Lampoldshausen
Institutes and Institutions:Institute of Space Propulsion > Rocket Propulsion
Deposited By: Hanke, Michaela
Deposited On:10 Nov 2014 08:48
Last Modified:10 Nov 2014 08:48

Repository Staff Only: item control page

Browse
Search
Help & Contact
Information
electronic library is running on EPrints 3.3.12
Copyright © 2008-2017 German Aerospace Center (DLR). All rights reserved.