TURBOJET ENGINE CONTROL METHOD Russian patent published in 2020 - IPC F02C9/28 F02C9/00 

FIELD: control methods; engine building.

SUBSTANCE: invention relates to in-flight control methods by turbojet engine with afterburner and adjustable jet nozzle. Method for controlling a turbojet with an afterburner and an adjustable jet nozzle in an aircraft power plant comprises: in stationary operating modes, including in "maximum forced" and "cruise" modes, and in transient operating modes, external parameters of working process of turbojet engine and aircraft flight are measured, according to measured values of external parameters, internal parameters of working process of turbojet engine which are not available for measurement are calculated, and real operating values of thrust are determined as performance characteristics for specific mode of turbojet engine operation and the value of the gas-dynamic stability of the fan, comparing the obtained operational characteristics values with the predetermined reference thrust values and the gas-dynamic stability margin value for the specific operating mode, based on the results of comparing operational characteristics, determining the standard values of the effect of control factors, such as fuel consumption in the main combustion chamber, fuel consumption in afterburner, guide vanes installation angle, jet nozzle critical section area, and depending on them generating a control signal based on the priority of control factors determined for each stationary and transient operation mode based on the results of preliminary tests of turbojet engine, and taking into account correcting corrections, the value of which depends on the change of external conditions of flight of the aircraft. At "maximum forced" and "cruising" operating modes, additional correction of control signal is introduced with simultaneous determination of aircraft flight acceleration. Introduction of additional correction is started at steady-state operating mode, continued in presence of positive value of acceleration of flight of aircraft and ending when this value reaches zero value. At "maximum forced" mode of operation additional correction is introduced by changing area of critical section of jet nozzle, and at cruise operating mode - by at least single change of area of critical section of jet nozzle and subsequent reduction of fuel consumption in main combustion chamber with reduction of speed of flight of aircraft to optimum value in this mode.

EFFECT: higher effective thrust of engine in power plant on "maximum forced" mode of operation and reduction of effective specific fuel consumption (id est increase in fuel efficiency) at cruise operating mode of engine due to optimization of control signal formed with due allowance for additional correction, taking into account operational state of turbojet engine.

1 cl, 1 dwg