CONTROL METHOD OF GAS TURBINE ENGINE REVERSING DEVICE DURING AIRCRAFT LANDING AND INTERRUPTED TAKEOFF Russian patent published in 2020 - IPC F02C9/00 

FIELD: engine building.

SUBSTANCE: invention relates to aircraft engine building, particularly, to control methods of gas turbine engine (GTE) reversing device (RD) at aircraft braking under conditions of landing and interrupted take-off. Method consists in the fact that it is determined aircraft landing by the presence of landing gear compression signals, after landing the engine control lever (ECL) is changed to "Minimum reverse thrust" site, control action is generated on transfer of reversing device to "Reverse thrust" position, moving elements RD position is diagnosed by means of at least one position sensor, information signal is generated into electronic controller and "Reversing device is switched on" in crew cabin after RU movable elements are moved to "Reverse thrust" position, ECL is changed to "Maximum reverse thrust" and engine operating mode corresponding to ECL position is automatically set; ECL is switched to "Slow running" site after aircraft speed is decreased, control action is created on transfer of RD into position "Forward thrust", ECL is changed to position for aircraft taxiing. Additionally form a predetermined limit value τ^lim ECL movement time from "Maximum mode" position to RD on position, during run-up of aircraft on flight strip in take-off mode, current time τ of ECL movement is measured from "Maximum mode" position to RD on position, comparing current value τ of ECL movement with limit value of τ^lim, determining presence of information signal "Aircraft speed does not exceed speed of decision making V1"; in case the current value τ of ECL movement is less than the limit value τ^lim, the information signal "Aircraft speed does not exceed the decision speed V1" is present, aircraft landing gear compression signal is present, then RD is moved from "Forward thrust" position to "Reverse thrust" position, note here that reverse thrust is generated in compliance with preset ECL regardless of "RD on" signal. Besides, formation of limit value τ^lim, determination of ECL movement time τ from "Maximum mode" position to RD on position, as well as comparison of τ^lim and τ performed in GTE RED, as limit value is used constant of τ^lim, equal to 2 s. Signal "Aircraft speed does not exceed speed of decision making V1" and signal of landing gear compression is generated and transmitted to electronic controller in aircraft equipment control system.

EFFECT: invention allows improving operating reliability of GTE and flight safety both during braking of aircraft with switching on of RD at normal landing, and in conditions of interrupted take-off based on reliable and automatic identification of emergency shutdown mode.

8 cl, 3 dwg