| 摘要 |
FIELD: engines and pumps.SUBSTANCE: invention relates to aircraft engineering, particularly, to small-size gas turbine engines with lubrication and cooling systems of bearings. Small-sized gas turbine engine comprises fuel feed system and system of lubrication of bearings of rotor with mixer, creating working medium by mixing of fuel-grease mix with air, derived from annular manifold of compressor via inclined slots, direction of which coincides with direction of air flow at its extraction. Mixer is composed of t-joint with compressed air feed inlet channel, fuel-grease feed inlet channel, mixing chamber and outlet channel of working medium supply to bearings. Bearings are installed with preload in axial direction, secured by spring.EFFECT: such design of lubrication system will allow to reduce gas dynamic losses at withdrawal of air from compressor, reducing heat generation on bearings due to elimination of slippage of balls, reducing wear and heating of bearings, increase efficiency of lubrication and cooling systems.1 cl, 8 dwg |
