U.S. Patent Specifications

Abstract

A gas turbine engine compressor blade, the blade being formed of synthetic, resin‐impregnated, cloth laminations bonded together and having an outwardly divergent root portion extending chord‐wise of the blade, said root portion having the outer divergent faces thereof forming angles of approximately 60 deg. with the base face thereof, the root portion having only six imperforate wedge‐shaped metal inserts of small wedge angle extending chord‐wise of the blade inter‐leaved with groups of said laminations and diverging away from the blade for the sum of their wedge angles to provide the root portion divergence, and means bonding on both sides, in the interior of the root portion, the inserts to adjacent laminations, at least some of the laminations extending spanwise of the blade and forming a part of the air impelling portion of the blade, the angle subtended by each insert being approximately 10 deg.

Citation

(1959), "U.S. Patent Specifications", Aircraft Engineering and Aerospace Technology, Vol. 31 No. 7, pp. 216-216. https://doi.org/10.1108/eb033142