| 摘要 |
FIELD: engines and pumps.SUBSTANCE: jet turbine engine is double-flow, two-shaft one, it contains minimum eight modules mounted according to modular and unit system comprising high and low pressure compressors separated by an intermediate housing, a main combustion chamber, an air-to-air heat exchanger, high and low pressure turbines, a mixer, a front device, an afterburner and a rotary jet nozzle comprising a rotary device and an adjustable jet nozzle. The rotation axis of the rotary device with reference to the horizontal axis is turned to the minimum angle 30° clockwise for the right engine and to the minimum angle 30° counterclockwise for the left engine. The inlet guiding device of the low pressure compressor is fitted with radial racks.EFFECT: invention allows to provide traction improvement, and also to improve reliability of operational characteristics of the gas-turbine engine and representativeness of results of tests for various gas-dynamic situations of engine operation, with simultaneous simplification of technology and reduction of labour and power consumption of test procedures.13 cl, 2 dwg |
