FIELD: mechanical engineering; aircraft industry.
SUBSTANCE: invention relates to gas-turbine engines of aircraft and ground application. Proposed turbocompressor of gas-turbine engine is provided with rear support with bearing arranged under combustion chamber. In shaft of turbocompressor and in adjoining to shaft parts, such as labyrinths and flanges, holes are made. Air intake holes are located before bearing and cooling air outlet holes, after bearing. Intake holes are connected with outlet holes through bypass holes. Invention improved reliability and economy of engine owing to reduction of losses in duct by excluding special air supply main line through gas-air duct between compressor and combustion chamber.
EFFECT: improved reliability and economy of engine owing to reduction of losses in duct.
3 cl, 2 dwg
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