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Technology Status of an Effusion Cooled CMC Rocket Combustion Chamber

Hald, Hermann and Ortelt, Markus and Fischer, Ingo and Greuel, Dirk (2005) Technology Status of an Effusion Cooled CMC Rocket Combustion Chamber. 6th International Symposium on Launcher Technologies, 2005-11-08 - 2005-11-11, München.

Full text not available from this repository.

Abstract

Propulsion systems are an essential key for efficient future space transportation systems (STS) and the feasibility of advanced vehicle design concepts. Beside efficiency, safe and reliable operations at significant reduced costs are a fundamental request to any kind of future propulsion system and STS, respectively. Today’s regenerative cooled cryogenic thrust chambers rely on a metallic design and they are highly optimized thus showing only minor improvement potential. An approach followed by DLR since some years is the realization of a revolutionary thrust chamber concept based on effusion cooling and use of high performance composites and porous ceramic matrix composites (CMC). Various functional demonstrators named V01-V03 were tested at the M3 test facility of DLR at the site of Lampoldshausen at typical combustion pressure levels of approximately 1MPa. A recent test campaign of an entire effusion cooled C/C thrust chamber contour at the European high-pressure H2/O2 test facility P8 in Lampoldshausen demonstrated successfully the functionality of this technology approach at relevant pressure levels up to 8 MPa and typical hot run test durations of 60 seconds. Summarizing the results achieved so far throughout this campaign an important development milestone and breakthrough of this new thrust chamber concept could be reached.

Item URL in elib:https://elib.dlr.de/20405/
Document Type:Conference or Workshop Item (Speech)
Title:Technology Status of an Effusion Cooled CMC Rocket Combustion Chamber
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Hald, HermannUNSPECIFIEDUNSPECIFIED
Ortelt, MarkusUNSPECIFIEDUNSPECIFIED
Fischer, IngoUNSPECIFIEDUNSPECIFIED
Greuel, DirkUNSPECIFIEDUNSPECIFIED
Date:October 2005
Refereed publication:No
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:rocket propulsion system, combustion chamber, H2/O2, cryogenic, effusion cooling, CMC, porous ceramic matrix composite, thrust chamber, composites, P8 test facility, Lampoldshausen
Event Title:6th International Symposium on Launcher Technologies
Event Location:München
Event Type:international Conference
Event Dates:2005-11-08 - 2005-11-11
Organizer:DLR-CNES
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 - Faserkeramische Brennkammer (old)
Location: Lampoldshausen , Stuttgart
Institutes and Institutions:Institute of Space Propulsion > Technologie
Institute of Structures and Design > Space Structural Components
Deposited By: Hald, Dr.-Ing. Hermann
Deposited On:15 Dec 2005
Last Modified:11 Dec 2017 11:20

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