Active geometry control system for gas turbine engines
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United States of America Patent
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Aug 14, 1990
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N/A
app pub date -
Sep 20, 1988
filing date -
Sep 20, 1988
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Expired
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Abstract
An active control system for use in gas turbine engines synchronizes exhaust nozzle area and burner fuel flow together with pas path variable engine parameters, such as fan variable vane and high compressor variable vane positions. As a result, extremely fast thrust transients are possible with optimized compression system stability, since fan and compressor rotor speeds are held high, allowing total engine power to be controlled by air flow and fuel flows directly.
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