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Status on Technology Development of Optic Fiber-Coupled Laser Ignition System for Rocket Engine ApplicationsTo pursue technology developments for future launch vehicles, NASA/Marshall Space Flight Center (MSFC) is examining vortex chamber concepts for liquid rocket engine applications. Past studies indicated that the vortex chamber schemes potentially have a number of advantages over conventional chamber methods. Due to the nature of the vortex flow, relatively cooler propellant streams tend to flow along the chamber wall. Hence, the thruster chamber can be operated without the need of any cooling techniques. This vortex flow also creates strong turbulence, which promotes the propellant mixing process. Consequently, the subject chamber concept: not only offer system simplicity, but also enhance the combustion performance. Test results have shown that chamber performance is markedly high even at a low chamber length-to-diameter ratio. This incentive can be translated to a convenience in the thrust chamber packaging.
Document ID
Document Type
Conference Paper
Trinh, Huu P.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Early, Jim
(Los Alamos National Lab. NM, United States)
Osborne, Robin
(Engineering Research and Consulting, Inc. Edwards AFB, CA, United States)
Thomas, Matthew
(Computational Fluid Dynamics Research Corp. Huntsville, AL, United States)
Bossard, John
(Computational Fluid Dynamics Research Corp. Huntsville, AL, United States)
Date Acquired
August 21, 2013
Publication Date
April 11, 2003
Subject Category
Spacecraft Design, Testing And Performance
Meeting Information
JANNAF CS/APS/PSHS/MSS Meeting(Colorado Springs, CO)
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