NDLI: Oxygen-rich combustion experiments in lox/gh2 uni-element rocket

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Oxygen-rich combustion experiments in lox/gh2 uni-element rocket

Content Provider	NASA Technical Reports Server (NTRS)
Author	Santoro, R. J. Ryan, H. M. Rahman, S. A. Pal, S.
Copyright Year	1996
Description	Research 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.
File Size	1071120
Page Count	52
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19960029143
Archival Resource Key	ark:/13960/t6rz46f36
Language	English
Publisher Date	1996-03-01
Access Restriction	Open
Subject Keyword	Inorganic And Physical Chemistry Oxygen Rocket Oxidizers Preburners Combustion Stability Liquid Oxygen Liquid Rocket Propellants Ignition Fuel Injection Liquid Injection Fuel-air Ratio Heat Transfer Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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