Method and apparatus for controlling a gas turbine engine
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United States of America Patent
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Nov 15, 1983
Grant Date -
N/A
app pub date -
Dec 8, 1980
filing date -
Dec 8, 1980
priority date (Note) -
Expired
status (Latency Note)
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Abstract
A gas turbine engine control for an engine which experiences airflow distortion at the engine inlet face plane uses a static pressure measurement upstream of the face plane along with a corrected rotor speed to generate a signal indicative of the average total pressure at the engine face plane. This signal is combined with a total pressure signal from elsewhere in the engine to generate a pressure ratio signal which is compared to the scheduled pressure ratio for the current operating conditions. Control logic then adjusts either the fuel flow rate to the burners or the area of the exhaust nozzle in response to the difference between these pressure ratios.
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