发明名称 |
GAS TURBINE ENGINE SEALING BUSHING |
摘要 |
FIELD: mechanical engineering; gas turbine engines. SUBSTANCE: proposed sealing bushing of gas turbine engine has axial projections with labyrinth strips and uniformly arranged channels to deliver cooling air. Ratio of length L of channel inlet hole to channel width b is 1-3. Ratio of size of land m between near inlet holes to width b inlet hole is 0.6 - 1.1. Ratio of minimum length n of channel to width b of channel inlet hole is within 0.6 and 3. EFFECT: enhanced reliability of engine in operation owing to reduction of thermal stresses, prevention of cracking and provision of cleaning of cooling air. 4 dwg
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申请公布号 |
RU2147690(C1) |
申请公布日期 |
2000.04.20 |
申请号 |
RU19980102622 |
申请日期 |
1998.02.02 |
申请人 |
OTKRYTOE AKTSIONERNOE OBSHCHESTVO "AVIADVIGATEL'" |
发明人 |
IVANOV V.V.;KUZNETSOV V.A.;FADEEV S.I. |
分类号 |
F01D11/02;(IPC1-7):F01D11/02 |
主分类号 |
F01D11/02 |
代理机构 |
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主权项 |
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地址 |
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