FIELD: gas-turbine engines for aerospace and ground applications.
SUBSTANCE: proposed gas-turbine engine turbocompressor provided with rear support disposed under combustion chamber has two inner air-cooling cavities, first one being disposed in front part of compressor rotor between shafts and second cavity, under first one around turbocompressor rear support between inner and outer flanges; turbocompressor shaft has bypass holes. Air discharge cavity is formed by shells within second inner air-cooling cavity.
EFFECT: enhanced reliability and economic efficiency of engine due to reduced loss in cooling circuit.
2 cl, 1 dwg
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