| 摘要 |
FIELD: engines and pumps.SUBSTANCE: invention relates to air-engine building, namely to air gas turbine engines. Gas turbine engine is designed as double-circuit, two-shaft. The engine contains at least eight modules mounted, preferably according to modular and nodal system, including the high and low pressure compressor, separated by the intermediate housing, main combustion chamber, air-air heat exchanger, high and low pressure turbines, a mixer, a front device, an afterburner and an all-mode jet nozzle. The engine is tested according to multi-cycle program. When performing the test steps, alteration of the modes, which exceed as to duration the configured flight time, is performed. Typical flight cycles are formed, based on which damageability of the most loaded parts is determined as per the programme. The required number of loading cycles during the test is determined based on the above. Full scope of tests is formed, including a quick change of cycles in the complete register from quick selection of maximum or full augmented power mode till complete stop of the engine, and then, representative cycle of continuous operation with multiple alteration of modes in the whole working spectrum with various span of range of the mode change, which exceeds the flight time at least 5 times. Quick selection of maximum or augmented power mode in some part of the test cycle is performed at the rate of acceleration and discharge.EFFECT: improvement of reliability of tests results and expansion of a representativeness of resource assessment and reliability of operation of the gas-turbine engine in the wide range of regional and seasonal conditions of the subsequent flight operation of engines.7 cl, 1 dwg |
