发明名称 |
ROTOR OF HIGH-TEMPERATURE TURBOMACHINE |
摘要 |
FIELD: engines and pumps.SUBSTANCE: invention relates to rotors of high-temperature turbomachines of gas turbine engines of aviation and ground use. In a rotor (1) of a high-temperature turbomachine between the first (7) and second (8) and the last but one (9) and the last (10) along gas flow (11) sealing combs in a rim (6) of an intermediate disc 5 there are radial channels (13) and (14), connecting an air disc-to-disc cavity (4) with a gas cavity (12) of the turbine. Radial walls (15) and (16) of channels (13) and (14) are made flat, and walls (17) and (18) that connect them are made cylindrical. The ratio of the length L of the channel in circumferential direction to the radius R of the cylindrical wall of the channel is within 2?6.EFFECT: by exclusion of contamination of inner surface of an intermediate disc and reduced concentration of stresses in a disc rim, high-temperature turbomachine rotor reliability increases.2 dwg |
申请公布号 |
RU2532458(C1) |
申请公布日期 |
2014.11.10 |
申请号 |
RU20130141382 |
申请日期 |
2013.09.09 |
申请人 |
OTKRYTOE AKTSIONERNOE OBSHCHESTVO "AVIADVIGATEL'" |
发明人 |
SYCHEV VLADIMIR KONSTANTINOVICH;JAZEV VLADIMIR MIKHAJLOVICH;KUZNETSOV VALERIJ ALEKSEEVICH;KARPMAN IRINA VIKTOROVNA |
分类号 |
F01D5/06;F01D11/02 |
主分类号 |
F01D5/06 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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