METHOD OF AUTOMATIC CONTROL OF GAS TURBINE ENGINE THRUST Russian patent published in 2010 - IPC F02C9/00 

FIELD: engines and pumps.

SUBSTANCE: proposed method consists in varying gas turbine engine rpm n_eng according to program n_eng ^prog=f(Lm_eng-cont, T_in, P_in), where: L_eng-cont is engine control lever turn angle, T_in is air temperature at gas turbine engine inlet, P_in is air pressure at gas turbine engine inlet. Beforehand, programmed rpm limits, n_in ^prog-lim are set in electronic controller of each engine for various flight conditions of the aircraft (take-off, climb, cruising regime). Thrust control computation system is used to generate data on flight stage and transmission of said data into said electronic controller of each engine. Programmed rpm limits, n_eng ^prog-lim, are generated to allow for said flight conditions. During each flight stage, rpm correction signal limiting value, ∂n_eng ^cor, is limited subject to the following condition, i.e. n_eng ^prog=f(L_eng-cont, T_in, P_in) + ∂n_eng ^cor≤n_eng ^prog-lim _.

EFFECT: ruling out of engine overheating, higher reliability.

2 dwg