METHOD OF AVIATION BYPASS TURBOJET ENGINE WITH FLOWS MIXING IN-FLIGHT DIAGNOSTICS Russian patent published in 2018 - IPC G01M15/14 

FIELD: engines and pumps.

SUBSTANCE: invention relates to aircraft engine building, refers the determination of bypass turbojet with mixing of flows parameters in flight and can be used for diagnostics of its state under operating conditions. Preliminary measuring the degree of the total airflow pressure unevenness at the engine inlet at all stationary flight modes of its operation, to determine the engine thrust value in a specific stationary flight mode, using the corrected value of the air flow at the engine inlet and the averaged value of the total pressure behind the low pressure compressor, calculated taking into account of the air flow total pressure unevenness degree at the engine inlet for a particular stationary flight operating mode of the engine, and the technical state of the engine is estimated by the certain engine thrust value deviation from the reference value for the specified flight mode.

EFFECT: invention makes it possible to increase the in-flight diagnosis reliability of the turbojet engine state by increasing the accuracy of determining of the engine thrust value and in its values changes range caused by the influence of external conditions, taking into account of the total air pressure unevenness degree at the engine inlet.

1 cl, 2 dwg