METHOD TO CONTROL AIRCRAFT TURBOJET ENGINE THRUST DISTURBANCE Russian patent published in 2017 - IPC F02C9/28 

FIELD: engines and pumps.

SUBSTANCE: method is carried out by means of a computer placed on said apparatus, in case of change of target thrust value (N1_CONS) of said turbojet engine, the actual thrust (N1_EFF) of the turbojet engine changes during the transition phase to achieve the desired thrust (N1_CONS), the method comprises the step of processing of given thrust value (N1_CONS) by the filtering function and transition phase model in such a way as to obtain a simulated thrust (N1_MOD), the step of measuring the actual phase (N1_EFF), the step of comparing said modelled thrust (N1_MOD) with said actual thrust (N1_EFF) to determine the deflection of the thrust (Δ), a step of comparing of said deflection (Δ) of the thrust threshold (S) of the signalling and the step of transmitting an alarm signal if the threshold (S) of the signalling is exceeded, a method where in this iteration, the previously modelled thrust is known, the transient phase model provides a time constant based on the previously modelled thrust, the filtering function provides a simulated thrust (N1_MOD) based on the obtained constant time modelled before the thrust and given thrust value (N1_CONS).

EFFECT: method improvement.

8 cl, 8 dwg