发明名称 |
Gas turbine engine blade tip clearance apparatus and method |
摘要 |
A zero running clearance system for gas turbine engines includes a gas turbine engine compressor having one or more first rotor assemblies and one or more first stator assemblies disposed adjacent the one or more first rotor assemblies; a gas turbine engine turbine having one or more second rotor assemblies and one or more second stator assemblies disposed adjacent the one or more second rotor assemblies; one or more shroud segments having blade seal surfaces disposed radially outside of the tips of blades of both the first and second rotor assemblies and a clearance distance extending between the blade tips and blade seal surfaces; and, an actuator selectively operable to axially move the first and said second rotor assemblies to alter the clearance distance.
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申请公布号 |
US7407369(B2) |
申请公布日期 |
2008.08.05 |
申请号 |
US20050253235 |
申请日期 |
2005.10.17 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
SCHWARZ FREDERICK M.;SMITH J. WALTER |
分类号 |
F01D11/08 |
主分类号 |
F01D11/08 |
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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