发明名称 |
GAS TURBINE ENGINE WITH COMPRESSOR DISK DEFLECTORS |
摘要 |
A compressor section for use in a gas turbine engine is comprised of a plurality of compressor stages, with each stage including a disk having an inner periphery defining a bore that faces a shaft. A flow path flows in a generally axial direction between the shaft and the bores of each disk. At least one deflector is positioned between a pair of adjacent bores to direct the air flow radially outwardly into a cavity formed between an associated pair of adjacent disks. |
申请公布号 |
EP3058176(A1) |
申请公布日期 |
2016.08.24 |
申请号 |
EP20140850225 |
申请日期 |
2014.09.10 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
HIESTER, PAUL J. |
分类号 |
F01D5/08;F01D25/12;F02C7/18;F04D29/26;F04D29/58 |
主分类号 |
F01D5/08 |
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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