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

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 contains a gear box of drives of engine units. After assembly the engine is tested for influence of climatic conditions at the main characteristics of the compressor operation. Tests are performed with measurements of engine parameters at various operating conditions within programmed range of flight modes for particular engine range to reference measured parameters to standard atmospheric conditions with due allowance for variation of working body properties and geometric characteristics of engine air-gas channel.

EFFECT: improvement of quality of operational characteristics and reliability of GTE due to implementation in the engine of set of main modules and assembly units with the technical solutions developed in the invention, parameters and at the expense of less energy and labour consuming obtaining and more correct reduction of experimentally received engine parameters to the parameters, corresponding to standard atmospheric conditions, and also in increase of representativeness of results of tests for the full range of flight cycles in various climatic conditions.

7 cl, 2 dwg, 4 tbl