A control system for an aircraft gas turbine propulsion engine includes an engine control that is adapted to receive at least engine inlet temperature data and aircraft altitude data. The engine control is configured to determine the availability of the engine inlet temperature data and implements a measured temperature engine thrust setting schedule when the engine inlet temperature data is available, and a default temperature engine thrust setting schedule when the engine inlet temperature data is unavailable. The default temperature engine thrust setting schedule ensures that the gas turbine propulsion engine will generate at least 90% of rated engine thrust at all actual engine inlet temperatures at the sensed aircraft altitude.
Aircraft gas turbine propulsion engine control without aircraft total air temperature sensors
2017-11-28
Patent
Electronic Resource
English
AIRCRAFT GAS TURBINE PROPULSION ENGINE CONTROL WITHOUT AIRCRAFT TOTAL AIR TEMPERATURE SENSORS
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