Pressure based close loop thrust control in a turbofan engine
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United States of America Patent
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Apr 19, 1994
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N/A
app pub date -
Oct 5, 1992
filing date -
Oct 5, 1992
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Abstract
Fuel flow and nozzle area are controlled by a multi-variable control. A requested fan speed is compared with measured fan speed, producing an error signal which is translated in a proportional-integral inner control loop into a requested compressor pressure signal that represents an acceptable rate of change in compressor pressure for difference between requested and measured fan speed. The error signal is compared with measured compressor pressure; the difference being used in a multi-variable control to adjust fuel flow and turbine exhaust area to achieve the requested compressor pressure.
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