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Ignition System for Gaseous PropellantsInstallation of spark plug in fuel-injection manifold of coaxial injector promotes more efficient cooling of combustor walls in rocket and turbine engines. After ignition occurs in fuel injector, combustion maintained in cooled main combustor leaving spark-plug tip in cool, clean environment. Eighteen tests have proven this injector design; no ignition failures occurred in 8,000 seconds of operation with gaseous oxygen and hydrogen. System also used with other propellants gaseous in ignition phase.
Document ID
19860000279
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Pieron, R. A. (Rockwell International Corp.)
Date Acquired
August 12, 2013
Publication Date
May 1, 1986
Publication Information
Publication: NASA Tech Briefs
Volume: 10
Issue: 3
ISSN: 0145-319X
Subject Category
Machinery
Report/Patent Number
MFS-29125
ISSN: 0145-319X
Report Number: MFS-29125
Accession Number
86B10279
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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