发明名称 |
Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge |
摘要 |
A blade of an axial compressor comprising: an airfoil is disclosed that has a leading edge and a root; a platform attached to the root of the airfoil; a dovetail attached to a side of the platform opposite to the airfoil; a neck of the dovetail adjacent the platform, and a slot in the neck and generally parallel to the platform, and the slot extends from a front of the neck to position in the neck beyond a line formed by the leading edge of the blade.
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申请公布号 |
US2005249592(A1) |
申请公布日期 |
2005.11.10 |
申请号 |
US20050038038 |
申请日期 |
2005.01.21 |
申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
GAUTREAU JAMES C.;MARTIN NICHOLAS F.;RICKERT CHRIS A. |
分类号 |
F04D29/38;F01D5/16;F01D5/30;F04D29/32;F04D29/34;(IPC1-7):B63H1/34 |
主分类号 |
F04D29/38 |
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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