JET TURBINE ENGINE Russian patent published in 2015 - IPC G01M15/14 

FIELD: engines and pumps.

SUBSTANCE: invention relates to air-engine building, namely to air turbojets. The air turbojet is designed as double-circuit, two-shaft one. 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 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 named 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 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 5-6 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 jet turbine engine in the wide range of regional and seasonal conditions of the subsequent flight operation of engines.

9 cl, 1 dwg