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

FIELD: engines and pumps.

SUBSTANCE: invention relates to aircraft engine building, namely to aircraft gas-turbine engines. A gas-turbine engine is two-stroke and two-shaft. The engine includes a gear box of propulsion units. The engine has been tested for gas-dynamic stability of operation of a compressor. A certain specimen or three to five specimens of a batch of mass-produced engines, which are identical for statistical representation of results, are tested on a test bench. The test bench is provided with an inlet aerodynamic device with a remotely controlled extension-type interceptor that crosses an air flow in an adjustable manner. 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. When necessary, tests are repeated for a certain set of modes as per regulations, which correspond to real operation mode of GTE under flight conditions.

EFFECT: improvement of the main performance data of an engine, volume and reliability of gas-dynamic stability of GTE operation, which is based on high static authenticity of data on allowable boundaries of frequency rotation modes of rotors of a compressor, with simultaneous simplification of the technology and reduction of labour input and power consumption of an engine test process.

8 cl, 4 dwg