发明名称 |
Fan blade platform feature for improved blade-off performance |
摘要 |
A fan blade for a gas turbine engine having an airfoil with a leading edge; a trailing edge; a concave side; and a convex side. The blade has an integral platform with: a convex fillet merging with the airfoil; a forward edge; an aft edge; and a thickness defined between a top surface and an underside surface. The platform includes a stiffener on the underside surface adjacent the convex side of the blade, such that the stiffener defines a blade-off event platform fracture path on a second side of the platform adjacent the following blade and adjacent the convex side of the airfoil.
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申请公布号 |
US6991428(B2) |
申请公布日期 |
2006.01.31 |
申请号 |
US20030461520 |
申请日期 |
2003.06.12 |
申请人 |
PRATT & WHITNEY CANADA CORP. |
发明人 |
CRANE NATHAN BRAD |
分类号 |
F01D21/00;F01D5/14;F01D21/04;F04D29/32 |
主分类号 |
F01D21/00 |
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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