FIELD: engines and pumps.
SUBSTANCE: oil system of gas-turbine engine (GTE) refers to aircraft engine building industry, and namely to oil system of high-temperature GTE of aircraft. Feature of oil system is use at the bleeder inlet of mixing header with two inlet channels for removal of heterogeneous flows (as to their physical parametres) of bleed air-oil mixture from oil cavities of support bearings of rotor of fan, compressor and turbine.
EFFECT: due to rotational arrangement of removal of bleed air-oil mixture flows from oil cavities and due to their interaction before bleeder inlet, it is possible not only to reduce oil flow in engine, but to prevent locking of bleeder at overpressures in main bleeding lines, which appear during leakage of hot gas and air to oil cavity of support bearing of turbine rotor in increased operating modes of engine.
3 cl, 3 dwg
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