发明名称 |
FAN BLADE FOR A TURBOJET OF AN AIRCRAFT HAVING A CAMBERED PROFILE IN THE FOOT 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 |
EP2855847(A1) |
申请公布日期 |
2015.04.08 |
申请号 |
EP20130728469 |
申请日期 |
2013.05.23 |
申请人 |
SNECMA |
发明人 |
REISS, HANNA;BISCAY, ADRIEN;FAYARD, BENOÎT;JABLONSKI, LAURENT;MERLOT, DAMIEN |
分类号 |
F01D5/14;F04D29/32;F04D29/66 |
主分类号 |
F01D5/14 |
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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