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Combustion-wave ignition for rocket enginesThe combustion wave ignition concept was experimentally studied in order to verify its suitability for application in baffled sections of a large booster engine combustion chamber. Gaseous oxygen/gaseous methane (GOX/GH4) and gaseous oxygen/gaseous hydrogen (GOX/GH2) propellant combinations were evaluated in a subscale combustion wave ignition system. The system included four element tubes capable of carrying ignition energy simultaneously to four locations, simulating four baffled sections. Also, direct ignition of a simulated Main Combustion Chamber (MCC) was performed. Tests were conducted over a range of mixture ratios and tube geometries. Ignition was consistently attained over a wide range of mixture ratios. And at every ignition, the flame propagated through all four element tubes. For GOX/GH4, the ignition system ignited the MCC flow at mixture ratios from 2 to 10 and for GOX/GH2 the ratios is from 2 to 13. The ignition timing was found to be rapid and uniform. The total ignition delay when using the MCC was under 11 ms, with the tube-to-tube, as well as the run-to-run, variation under 1 ms. Tube geometries were found to have negligible effect on the ignition outcome and timing.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Liou, Larry C.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1992
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NAS 1.15:105545
Meeting Information
Meeting: 1992 JANNAF Propulsion Meeting
Location: Indianapolis, IN
Country: United States
Start Date: February 24, 1992
End Date: February 26, 1992
Accession Number
Funding Number(s)
PROJECT: RTOP 506-21-11
Distribution Limits
Work of the US Gov. Public Use Permitted.
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