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

Herbertz, Armin and Selzer, Markus (2014) Analysis of Coolant Mass Flow Requirements for Transpiration Cooled Ceramic Thrust Chambers. Transactions of the Japan Society for Aeronautical and Space Sciences, Space Technology Japan, 12 (ists29), Pa_31-Pa_39. ISSN 1347-3840.

Full text not available from this repository.

Official URL: https://www.jstage.jst.go.jp/article/tastj/12/ists29/12_Pa_31/_pdf

Abstract

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%.

Document Type:Article
Title:Analysis of Coolant Mass Flow Requirements for Transpiration Cooled Ceramic Thrust Chambers
Authors:
AuthorsInstitution or Email of Authors
Herbertz, ArminArmin.Herbertz@dlr.de
Selzer, Markusmarkus.selzer@dlr.de
Date:June 2014
Journal or Publication Title:Transactions of the Japan Society for Aeronautical and Space Sciences, Space Technology Japan
Refereed publication:Yes
In SCOPUS:No
In ISI Web of Science:No
Volume:12
Page Range:Pa_31-Pa_39
ISSN:1347-3840
Status:Published
Keywords:Keramische Schubkammer, Transpirationskühlung, Effusionskühlung, Systemanalyse
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 - Proj. KERBEROS
Location: Stuttgart
Institutes and Institutions:Institute of Structures and Design > Space System Integration
Deposited By: Dr. Armin Herbertz
Deposited On:20 Aug 2014 11:14
Last Modified:20 Aug 2014 11:14

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