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Analysis of Coolant Mass Flow Requirements for Transpiration Cooled Ceramic Thrust Chambers

Herbertz, Armin and Selzer, Markus (2013) Analysis of Coolant Mass Flow Requirements for Transpiration Cooled Ceramic Thrust Chambers. 29th International Symposium on Space Technology and Science, 03.-06 Jun. 2013, Nagoya.

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The long-term development of ceramic rocket engine thrust chambers at the German Aerospace Center (DLR) culminates in compact designs of transpiration-cooled fibre-reinforced ceramic rocket engine chamber structures. Achievable benefits of the transpiration cooled ceramic thrust chamber are the reduction of engine mass and manufacturing cost, as well as an increased reliability and higher lifetime due to thermal cycle stability. The transpiration cooling principle however reduces the engine performance. Due to the transpiration cooling the characteristic velocity decreases with increasing coolant ratio. The goal of the chamber development is therefore to minimize the required coolant mass flow. The wall temperature can be calculated using known heat transfer correlations, for example given by Bartz, and employing a model given in literature for the reduction of the heat transfer coefficient based on coolant mass flow. By this method the required coolant mass flow ratio for different chamber diameters and pressure levels can be calculated. This paper discusses the application potential of DLR's ceramic thrust chamber technology for high performance engines. Parametric variations of engine sizing (such as chamber pressure and diameter) are performed. For large diameters and high chamber pressures the required coolant ratio is below 1%.

Item URL in elib:https://elib.dlr.de/84421/
Document Type:Conference or Workshop Item (Speech)
Title:Analysis of Coolant Mass Flow Requirements for Transpiration Cooled Ceramic Thrust Chambers
AuthorsInstitution or Email of AuthorsAuthor's ORCID iD
Herbertz, ArminArmin.Herbertz (at) dlr.deUNSPECIFIED
Selzer, Markusmarkus.selzer (at) dlr.deUNSPECIFIED
Date:June 2013
Refereed publication:No
Open Access:No
Gold Open Access:No
In ISI Web of Science:No
Keywords:Ceramic Thrust Chamber, Chemical Propulsion, Transpiration Cooling, Systems Study
Event Title:29th International Symposium on Space Technology and Science
Event Location:Nagoya
Event Type:international Conference
Event Dates:03.-06 Jun. 2013
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transportation
DLR - Research area:Raumfahrt
DLR - Program:R RP - Space Transportation
DLR - Research theme (Project):R - Proj. KERBEROS (old)
Location: Stuttgart
Institutes and Institutions:Institute of Structures and Design > Space Structural Components
Deposited By: Herbertz, Dr. Armin
Deposited On:22 Nov 2013 10:57
Last Modified:08 May 2014 23:18

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