发明名称 |
AIRPLANE TURBOJET FAN BLADE OF CAMBERED PROFILE IN ITS ROOT SECTIONS |
摘要 |
A fan blade for an airplane turbojet, the blade including an airfoil extending axially between a leading edge and a trailing edge and including a plurality of airfoil sections stacked radially between a root section and a tip section. All of the airfoil sections situated between the root section and an airfoil section situated at a radial height corresponding to 30% of a total radial height of the airfoil possess a skeleton curve having a point of inflection. |
申请公布号 |
US2015152880(A1) |
申请公布日期 |
2015.06.04 |
申请号 |
US201314403003 |
申请日期 |
2013.05.23 |
申请人 |
SNECMA |
发明人 |
Reiss Hanna;Biscay Adrien;Fayard Benoit;Jablonski Laurent;Merlot Damien |
分类号 |
F04D29/38;F04D29/32;F04D19/00 |
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 |
Paris FR |