发明名称 |
TURBINE TIP CLEARANCE MEASUREMENT |
摘要 |
A measuring assembly for use in a gas turbine engine includes an indicia portion that extends radially inwardly from an inner surface of a ring seal structure to a location radially inwardly from tips of blades mounted on a rotor. The indicia portion of the measuring assembly comprises a section that is abraded by the blades during rotational movement of the rotor to provide a visual indication of a distance between the tips of the blades and the inner surface.
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申请公布号 |
US2012207586(A1) |
申请公布日期 |
2012.08.16 |
申请号 |
US201113027354 |
申请日期 |
2011.02.15 |
申请人 |
CHEHAB ABDULLATIF M.;HINES KEVIN L.;PEPPERMAN BARTON M.;BOGDAN MATTHEW D. |
发明人 |
CHEHAB ABDULLATIF M.;HINES KEVIN L.;PEPPERMAN BARTON M.;BOGDAN MATTHEW D. |
分类号 |
F01D25/00;G01B1/00;G01M15/14 |
主分类号 |
F01D25/00 |
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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