US 12,215,600 B2
Composite fan blade with leading edge sheath and energy absorbing insert
Larry Foster, South Glastonbury, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX Corporation, Farmington, CT (US)
Filed on Nov. 3, 2017, as Appl. No. 15/803,594.
Prior Publication US 2019/0136697 A1, May 9, 2019
Int. Cl. F01D 5/14 (2006.01); F01D 9/02 (2006.01); F01D 25/00 (2006.01)
CPC F01D 5/147 (2013.01) [F01D 9/02 (2013.01); F01D 25/005 (2013.01); F05D 2220/32 (2013.01); F05D 2220/36 (2013.01); F05D 2230/23 (2013.01); F05D 2230/60 (2013.01); F05D 2240/303 (2013.01); F05D 2300/603 (2013.01)] 10 Claims
OG exemplary drawing
 
1. An airfoil for a gas turbine engine, comprising:
a blade body having a forward face, a pressure side and a suction side, each of the pressure side and the suction side extending between a forward portion and a trailing edge;
a leading edge sheath having a leading edge portion that is spaced apart from the forward portion, a first arm that engages the pressure side, and a second arm that engages the suction side, a cavity being defined between the leading edge portion, the first arm, the second arm, and the forward portion; and
an energy absorbing insert including an insert face, the energy absorbing insert being disposed within the cavity, the energy absorbing insert being made of a non-Newtonian material, wherein the energy absorbing insert is arranged with the blade body such that the insert face extends completely across a width of the forward face, the width extending from the pressure side and the suction side.