Gas turbine engine

FIELD: engines and pumps. SUBSTANCE: invention relates to power engineering. A gas-turbine engine is double-flow and two-shaft; with that, it includes at least eight modules, including high and low pressure compressors separated with an intermediate housing, the main combustion chamber, an air-to-air heat exchanger, high and low pressure turbines, a mixer, the front device, an afterburner and a turning jet nozzle, including a turning device and an adjustable jet nozzle. The rotation axis of the turning device relative to the horizontal axis is turned through an angle of at least 30° in a clockwise direction for the right-hand engine and through an angle of at least 30° in a counter-clockwise direction for the left-hand direction. An engine test bench is provided with an inlet aerodynamic device with a remotely controlled retractable interceptor. The interceptor includes a calibrated scale of interceptor positions, which has a fixed critical point separating the engine by 2-5% from transition to surging. EFFECT: invention allows improving reliability of the data on allowable limits of frequency modes of rotation of the rotor so that gas-dynamic stability of engines is provided. 16 cl, 4 dwg