FIELD: machine building.
SUBSTANCE: disclosed is a helicopter gas turbine engine with air cleaning from foreign particles, including particles of sand and dust, having a multi-stage axial compressor. It is assumed that the engine operates as a part of a helicopter power plant, in which an air cleaning device is installed at the inlet in front of the engine, but the cleaning characteristics of the input cleaner are insufficient to ensure overhaul lifetime of the engine when operating in hard dust conditions. In order to reduce intensive abrasive wear of blades of small-size high-pressure steps of the compressor and increase engine overhaul life, it is proposed to perform additional air cleaning in the engine itself, using separation capabilities of front axial stages of compressor, concentration of separated foreign particles at periphery of flow channel of compressor and available on engine air bleed system, modified for removal from compressor of separated foreign particles before their arrival to stages of high pressure.
EFFECT: reduction of intensive abrasive wear of blades of small-size stages of high pressure of compressor and increase of overhaul lifetime of engine.
1 cl, 3 dwg
