| 摘要 |
FIELD: aircraft industry; gas-turbine engines. ^ SUBSTANCE: invention relates to gas-turbine engine with axis X, having from input of output, high-pressure compressor whose rotor contains outlet fairing 4, diffuser 3, extended at the rear from side of axis X by inner casing arranged radially outside from indicated outlet fairing of compressor, combustion chamber arranged radially outside from said inner casing of diffuser and high-pressure turbine whose rotor is connected with outlet fairing of compressor by mans of coupling. Under chamber space is formed between inner casing of diffuser and outlet fairing of compressor which is located at outlet of unloading labyrinth 13 and in which cooling air circulates from inlet to outlet. Gas-turbine engine contains additionally fairing of stator 20 installed under inner casing of diffuser at outlet of unloading labyrinth 13. ^ EFFECT: reduced loads in annular space and temperature of cooling air in space. ^ 2 cl, 1 dwg
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