发明名称 |
Methods and apparatus for controlling gas turbine engine rotor tip clearances |
摘要 |
A method enables a gas turbine engine compressor including a stator assembly and a rotor assembly to be assembled. The method comprises providing a casing formed from a plurality of rings, and coupling a first of the casing rings around the rotor assembly such that a radially inner surface of the first casing ring is axially aligned with, and radially outward from, a row of rotor blades extending from the rotor assembly. The method also comprises coupling a second of the casing rings to the first casing ring with a fastener assembly, such that the first casing ring radially inner surface facilitates insulating the fastener assembly from the compressor flowpath.
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申请公布号 |
US2004223846(A1) |
申请公布日期 |
2004.11.11 |
申请号 |
US20030430485 |
申请日期 |
2003.05.06 |
申请人 |
TAYLOR STEVEN MITCHELL;SPENCER CHRISTINA MARIE;LICU DRAGOS NICOLAE |
发明人 |
TAYLOR STEVEN MITCHELL;SPENCER CHRISTINA MARIE;LICU DRAGOS NICOLAE |
分类号 |
F04D29/32;F01D1/02;F01D11/14;F01D25/24;F02C3/04;F02C6/12;F04D29/52;F04D29/58;F04D29/64;(IPC1-7):F01D1/02 |
主分类号 |
F04D29/32 |
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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