ADJUSTMENT METHOD OF TEST 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 test GTE made as two-stroke and two-shaft is subject to adjustment. GTE adjustment is performed in stages. One to five GTE are subject to tests for compliance with the specified parameters at each stage. Any module of those damaged during tests or those that do not correspond to the required parameters is tested and when necessary replaced with adjusted ones - from a low pressure compressor to an all-mode turning jet nozzle including a controlled jet nozzle and a turning device attached to the afterburner in a detachable manner and the rotation axis of which is turned relative to the horizontal axis through an angle of at least 30°. The programme of adjustment tests with further adjustment operation includes tests of the engine for gas-dynamic stability of operation of the compressor. The test engine is tested on the 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: simplification of a technology and reduction of labour costs and energy intensity of a GTE test process at the GTE adjustment stage at improvement of reliable determination of boundaries of the allowable thrust variation range.

6 cl, 4 dwg