Transpiration Cooling Appllied to C/C Liners of Cryogenic Liquid Rocket Engines-Reference-Cited by-同舟云学术

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Transpiration Cooling Appllied to C/C Liners of Cryogenic Liquid Rocket Engines

Published:2004-06-26 Issue: Volume: Page:
ISSN:
Container-title:40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
language:
Short-container-title:

Author:

Haidn Oskar¹,Greuel Dirk¹,Herbertz Armin¹,Ortelt Markus¹,Hald Hermann²

Affiliation:

1. DLR, German Aerospace Research Center

2. DLR

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2004-3682

Reference27 articles.

1. [2]Schmidt, S., Beyer, S., Knabe, H., Immich, H., Meistring, R., Gessler, A. "Advanced Ceramic Matrix Composite Materials for Current andFuturePropulsionTechnologyApplications,"IAC-03-S.3.03,September29-October3rd2003,54thInt.AstronauticalCongress.

2. Lightweight chambers for thrust cell applications

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1. Numerical investigation on structural optimization for porous plate in transpiration cooling with phase change;Applied Thermal Engineering;2024-11

2. Numerical Investigation on Transpiration Cooling Performance of Oriented Porous Structure Under Local Block Conditions;Journal of Thermophysics and Heat Transfer;2024-07

3. Research on head cooling of high-speed aircraft by liquid nitrogen;The Aeronautical Journal;2020-12-02

4. Numerical simulation of transpiration cooling experiments in supersonic flow using OpenFOAM;CEAS Space Journal;2019-12-18

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