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Experimental evaluation of the ignition process of carbon monoxide and oxygen in a rocket engineCarbon monoxide and oxygen ignition boundaries were determined in a spark torch igniter as a function of propellant inlet temperatures. The oxygen temperature was varied from ambient to -258 F, and the carbon monoxide temperature was varied from ambient to -241 F. With the oxygen and carbon monoxide at -253 F and -219 F, respectively, they successfully ignited between mixture ratios of 2.42 and 3.10. Analysis of the results indicated that the lower ignition boundary was more sensitive to oxygen temperature than to carbon monoxide temperature. Another series of tests was performed in a small simulated rocket engine with oxygen at -197 F and carbon monoxide at -193 F. An oxygen/hydrogen flame was used to initiate combustion of the oxygen and carbon monoxide. Tests performed at the optimum operating mixture ratio of 0.55 obtained steady-state combustion in every test.
Document ID
19960045922
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Linne, Diane L. (NASA Lewis Research Center Cleveland,OH United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1996
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA Paper 96-2943
NASA-TM-107267
NAS 1.15:107267
E-10334
Meeting Information
Meeting: Joint Propulsion Conference
Location: Lake Buena Vista, FL
Country: United States
Start Date: July 1, 1996
End Date: July 3, 1996
Sponsors: Society of Automotive Engineers, Inc., American Society for Electrical Engineers, American Society of Mechanical Engineers, American Inst. of Aeronautics and Astronautics
Accession Number
96N32762
Funding Number(s)
PROJECT: RTOP 889-32-73
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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