发明名称 |
Gas turbine engine cooling apparatus |
摘要 |
A gas turbine engine has an assembly of circumferentially spaced rotor blades each having a radial tip. A plurality of seal segments mounted for radial movement circumscribe the rotor blades. Each segment is connected to the casing through a seal carrier provided with a flexible membrane which divides high pressure air from low pressure into two channels.
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申请公布号 |
US6089821(A) |
申请公布日期 |
2000.07.18 |
申请号 |
US19980072043 |
申请日期 |
1998.05.05 |
申请人 |
ROLLS-ROYCE PLC |
发明人 |
MAGUIRE, ALAN R;RICHARDS, MARTYN |
分类号 |
F01D11/24;F01D25/12;(IPC1-7):F01D11/08 |
主分类号 |
F01D11/24 |
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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