Transient control system for gas turbine engine
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United States of America Patent
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Mar 7, 1989
Grant Date -
N/A
app pub date -
Feb 3, 1987
filing date -
Feb 3, 1987
priority date (Note) -
Expired
status (Latency Note)
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Abstract
A secondary control for a gas turbine engine powering fighter class of aircraft serves to modify the primary control solely during transient engine operation primarily in the combat box of between approximately 0.4 to 1.2 Mach number at an altitude between 10,000 to 30,000 feet of the flight envelope and does maintain higher compressor rpm, turbine inlet temperature, and engine air flow at the idle or part power thrust settings by concomitantly adjusting fuel flow and engine exhaust nozzle area thereby enhancing thrust response, low cycle fatigue life, and engine stability.
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