CONTROL METHOD OF AERONAUTIC GAS TURBINE ENGINE WITH A VARIABLE GEOMETRY OF OUTPUT DEVICE Russian patent published in 2019 - IPC F02C9/26 

FIELD: engines and pumps.

SUBSTANCE: control method of aeronautic turbojet engine (TJE) with a variable geometry of output device relates to control methods that optimize the operation of TJE depending on the flight conditions. When implementing the method, conditions are created at the entrance to the engine and at the exit from it, corresponding to different flight conditions in height and speed, values of thrust and fuel consumption are measured and the fuel consumption dependences are built on the thrust. According to the invention, tests with a different diameter of critical section of propelling nozzle are carried out, at each diameter create at the entrance to the engine and at the exit from it pressure and temperature of air corresponding to the conditions of cruising flights and the conditions of the maximum range mode, determine the diameter of critical section of propelling nozzle corresponding to the minimum specific fuel consumption in the selected flight mode, then, at the signal from an aircraft when cruising and best-range flights, the diameter of critical section of propelling nozzle is changed to a diameter that provides a minimum specific fuel consumption.

EFFECT: implementation of the invention allows to increase the efficiency of engine on cruising flight modes of an aircraft while maintaining the specified diameter of critical section of a propelling nozzle.

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