Gas turbine engine blade mounting arrangement

A blade root spacer for mounting a gas turbine engine fan blade at a root portion thereof to a hub therefore, said blade root spacer comprising a radially bowed, elongate leaf spring comprising first and second major surfaces adapted to bear against a radially innermost surface of said fan blade root and an opposed radially innermost surface of a mounting slot in an associated fan blade hub, said leaf spring comprising a pair of inner and outer longitudinally extending major surfaces and a pair of generally parallel opposed lateral side edges.

A mounting arrangement for a gas turbine engine blade having a radially directed axis and a radially inner root received within a slot in an associated blade hub, said mounting arrangement including an elongate resilient leaf spring spacer comprising radially inner and outer major surfaces that extend between opposed lateral side edges, wherein said spacer is received within said slot between a radially innermost end of said blade root and a radially innermost surface of said slot by interference fit therebetween such that said radially outer major surface of said spacer exerts a radially outward force on said blade root to reduce radial movement of said blade root within said slot.