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Oxygen-Rich Combustion Experiments in LOX/GH2 Uni-Element RocketResearch efforts are directed towards understanding specific technical issues that must be resolved to minimize the risk and cost associated with developing oxygen-rich rocket preburners. The experiments concentrate on hot-fire uni-element tests to demonstrate concepts which can be incorporated into hardware design and development. Two concepts under consideration are direct injection of propellants at high O/F (oxidizer/fuel ratio), and stoichiometric injection followed by downstream injection of LOX to achieve the high O/F. The specific results given here address the performance, ignition, combustion stability, and wall heat transfer aspects of a direct-injection swirl coaxial element design operating at high O/F.
Document ID
19960029143
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Rahman, S. A.
(Pennsylvania State Univ. University Park, PA United States)
Ryan, H. M.
(Pennsylvania State Univ. University Park, PA United States)
Pal, S.
(Pennsylvania State Univ. University Park, PA United States)
Santoro, R. J.
(Pennsylvania State Univ. University Park, PA United States)
Date Acquired
September 6, 2013
Publication Date
March 1, 1996
Publication Information
Publication: Thirteenth Workshop for Computational Fluid Dynamic Applications in Rocket Propulsion and Launch Vehicle Technology
Subject Category
Inorganic And Physical Chemistry
Accession Number
96N29673
Funding Number(s)
CONTRACT_GRANT: F49620-93-1-0365
CONTRACT_GRANT: NCC8-46
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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