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Catalytic ignition of hydrogen and oxygen propellantsAn experimental program was conducted to evaluate the catalytic ignition of gaseous hydrogen and oxygen propellants. Shell 405 granular catalyst and a monolithic sponge catalyst were tested. Mixture ratio, mass flow rate, propellant temperature, and back pressure were varied parametrically in testing to determine the operational limits of the catalytic igniter. The test results show that the gaseous hydrogen and oxygen propellant combination can be ignited catalytically using Shell 405 catalyst over a wide range of mixture ratios, mass flow rates, and propellant injection temperatures. These operating conditions must be optimized to ensure reliable ignition for an extended period of time. A cyclic life of nearly 2000, 2 sec pulses at nominal operating conditions was demonstrated with the catalytic igniter. The results of the experimental program and the established operational limits for a catalytic igniter using the Shell 405 catalyst are presented.
Document ID
19880015305
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Zurawski, Robert L.
(NASA Lewis Research Center Cleveland, OH, United States)
Green, James M.
(Sverdrup Technology, Inc. Arnold Air Force Station, Tenn., United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1988
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
E-4104
NAS 1.15:100957
NASA-TM-100957
AIAA PAPER 88-3300
Accession Number
88N24689
Funding Number(s)
PROJECT: RTOP 506-42-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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