FIELD: engines and pumps.
SUBSTANCE: proposed method consists in varying gas turbine engine rpm neng according to program neng prog=f(Lmeng-cont, Tin, Pin), where: Leng-cont is engine control lever turn angle, Tin is air temperature at gas turbine engine inlet, Pin is air pressure at gas turbine engine inlet. Beforehand, programmed rpm limits, nin 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, neng prog-lim, are generated to allow for said flight conditions. During each flight stage, rpm correction signal limiting value, ∂neng cor, is limited subject to the following condition, i.e. neng prog=f(Leng-cont, Tin, Pin) + ∂neng cor≤neng prog-lim .
EFFECT: ruling out of engine overheating, higher reliability.
2 dwg
Authors
Dates
2010-12-20—Published
2009-03-23—Filed