Start system for expendable gas turbine engine
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United States of America Patent
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Sep 13, 2005
Grant Date -
N/A
app pub date -
Mar 19, 2003
filing date -
Mar 19, 2003
priority date (Note) -
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Abstract
A start system for an expendable gas turbine engine includes a pressurized oxygen source and a pyroflare igniter. The pressure source communicates oxygen to a compressor through a first passage to spin-up a rotor and communicates oxygen to a combustor through a second passage to provide light-off oxygen for the atomized fuel within the combustor. A pressure regulator shuts off the impingement flow at a predetermined pressure and blow down of combustor flow continues for an enhancement period to assure continued operation of the gas turbine even at high altitudes.
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