FIELD: mechanical engineering; gas-turbine engines.
SUBSTANCE: proposed gas-turbine engine contains compressor section for compressing intake air into high-pressure air and intermediate pressure air, combustion chamber section for combustion of fuel with compressed air, communicating with compressor section, turbine section connected with said combustion chamber section for receiving gaseous combustion products from combustion chamber. Turbine section contains turbine blade with head in area of pressure lower than intermediate pressure indicated above. Ring space arranged higher than compressor section in direction of flow and it contains branch for intermediate pressure air. Partition is installed in ring space to transform dynamic head of intermediate pressure air into higher static pressure air. Gas-turbine engine is provided with channel having inlet hole for communicating with space and outlet hole communicating with turbine blade to direct intermediate pressure air at higher pressure to turbine blade, thus cooling the blade.
EFFECT: improved efficiency of cooling of high-pressure turbine.
10 cl, 3 dwg
