Vortex Thrust Chamber Testing and Analysis for O2-H2 Propulsion Applications-Reference-Cited by-同舟云学术

Vortex Thrust Chamber Testing and Analysis for O2-H2 Propulsion Applications

Published:2003-06-26 Issue: Volume: Page:
ISSN:
Container-title:39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
language:
Short-container-title:

Author:

Chiaverini Martin¹,Malecki Matthew¹,Sauer J¹,Knuth William¹,Majdalani Joseph²

Affiliation:

1. Orbital Technologies Corporation

2. Marquette University

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2003-4473

Reference30 articles.

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2. 2,2

3. 888-2.053loglot,t>0.75 b 1.10 t1.4

4. Figure21 indicatesthat the number of injectionports in the GH2 had the most significant effect faceplate heating, while the GOX splitratio phad nodiscernible effect, as for the Isp,eesults. Statistical analysis indicated the following trends toward lower heating rates: fewer GHZ ports, lower swirl GOX injector pressure drop, higher auxiliary GOX injector pressure drop, lower GH2 injector pressure drop, and longer chamberlength.

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