发明名称 Turbofan gas turbine engine fan blade and a turbofan gas turbine fan rotor arrangement
摘要 A fan blade comprises a root portion and an aerofoil portion. The aerofoil portion has a leading edge, a trailing edge and a tip remote from the root portion. A concave pressure surface extends from the leading edge to the trailing edge and a convex suction surface extends from the leading edge to the trailing edge. A portion of the tip of the aerofoil portion between the leading edge and the trailing edge of the aerofoil portion is thinner than the remainder of the tip. The portion of the tip of the aerofoil portion is spaced from the leading edge and is spaced from the trailing edge. The portion of the tip of the aerofoil portion has a recess such that the portion of the tip of the aerofoil portion is thinner than the remainder of the tip. The recess is arranged on the concave pressure surface of the aerofoil portion. This reduces vibrations of the fan blade.
申请公布号 US2010014984(A1) 申请公布日期 2010.01.21
申请号 US20090585777 申请日期 2009.09.24
申请人 ROLLS-ROYCE PLC 发明人 TUDOR DAVID J.
分类号 F01D5/14;F04D29/38;F04D29/66 主分类号 F01D5/14
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