FIELD: engines and motors.
SUBSTANCE: invention is referred to gas turbine engines for aviation and terrestrial application. A method of operation of a gas turbine engine with a pivotal guiding device installed at the inlet of a compressor consists in the following: when blades of the compressor along chord are worn to ratio 1.01...1.1 of cord value "B" initial to value "b" of worn profiles of an operating compressor blade along the peripheral section, then blades of inlet directing device are turned to close its flow path area at an angle of 1...6°. The invention increases efficiency and reliability of an engine during operation by means of decreasing flow path area of the inlet directing device.
EFFECT: increasing efficiency and reliability of a gas turbine engine.
2 dwg
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