发明名称 |
Fan blade interplatform seal |
摘要 |
The present invention relates to a seal interposed between platforms of blades for a fan in an axial gas turbine engine. Modern impact resistant fan blades have larger interplatform gaps. As a result, the interplatform seals have to seal a large gap. The seal is stiffened such that it can withstand centrifugal forces due to fan operation. In addition, various construction derails are developed for the stiffened seal.
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申请公布号 |
US5820338(A) |
申请公布日期 |
1998.10.13 |
申请号 |
US19970839999 |
申请日期 |
1997.04.24 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
KASPROW, ROBERT F.;KURZ, PHYLLIS L.;LESHANE, JEFFREY S. |
分类号 |
F01D11/00;F02C7/28;F02K3/06;F04D29/08;F04D29/32;F04D29/34;(IPC1-7):F01D25/26 |
主分类号 |
F01D11/00 |
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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