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A mounting arrangement for a gas turbine engine blade having a root employs a lightweight, simple and economical leaf spring spacer which biases the blade root in a radially outward direction to minimize unwanted movement of the root within a conforming slot in a blade hub under conditions such as w

A mounting arrangement for a gas turbine engine blade having a root employs a lightweight, simple and economical leaf spring spacer which biases the blade root in a radially outward direction to minimize unwanted movement of the root within a conforming slot in a blade hub under conditions such as windmilling when centrifugal force alone is inadequate to tightly seal the root within the slot.

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1. 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 received within said slot between a radially innermost en

1. 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 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 spacer exerts a radially outward force on said blade root to reduce radial movement of said blade root within said slot. 2. The mounting arrangement of claim 1 wherein said leaf spring spacer is radially bowed. 3. The mounting arrangement of claim 1 wherein said blade comprises a fan blade. 4. The mounting arrangement of claim 1 wherein said hub comprises a disk. 5. The mounting arrangement of claim 1 wherein said radially innermost end of said blade root and said radially innermost surface of said slot comprise a pair of opposed longitudinally extending surfaces generally normal to said blade axis. 6. The mounting arrangement of claim 1 wherein said blade root is dovetail shaped including a pair of radially inner and outer angularly offset, longitudinally extending side surfaces and said slot includes a pair of radially inner and outer angularly offset longitudinally extending side surfaces opposed to said radially inner and outer side surfaces of said blade root, said radially outward force exerted by said leaf spring spacer causing said radially outer side surface of said blade root to bear against said radially outer side surface of said slot. 7. The mounting arrangement of claim 1 wherein said leaf spring spacer includes a longitudinal axis generally parallel to said axis of said gas turbine engine, a pair of opposed, radially inner and outer longitudinally extending major surfaces and a pair of opposed lateral side edges, each of said side edges including at least one tab extending outwardly therefrom. 8. The mounting arrangement of claim 7 wherein said tab bears against said radially innermost end of said blade root. 9. The mounting arrangement of claim 7 wherein said blade root is dovetail shaped including a pair of radially inner and outer angularly offset longitudinally extending side surfaces, and wherein said tab includes an outer end portion which bears against said radially inner side surface of said dovetail shaped blade root. 10. The mounting arrangement of claim 1 wherein said leaf spring spacer is formed from a thermoplastic. 11. 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. 12. The blade root spacer of claim 11 wherein said lateral side edges are thickened for filling a clearance between a beveled edge of said fan blade root portion and an adjacent portion of a mating slot in said hub. 13. The blade root spacer of claim 12 wherein each of said side edges includes at least one tab extending outwardly therefrom. 14. The blade root spacer of claim 11 wherein said blade root spacer is apertured along at least a portion of the length thereof. 15. The blade root spacer of claim 11 wherein said blade root spacer comprises a thermoplastic. 16. 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. 17. The mounting arrangement of claim 16, wherein said spacer includes a longitudinal axis generally parallel to said axis of said gas turbine engine, and wherein said radially inner and outer major surfaces extend longitudinally. 18. The mounting arrangement of claim 16 wherein each of said side edges including at least one tab extending outwardly therefrom. 19. The mounting arrangement of claim 18 wherein said tab bears against said radially innermost end of said blade root. 20. The mounting arrangement of claim 18 wherein said blade root is dovetail shaped including a pair of radially inner and outer angularly offset longitudinally extending side surfaces, and wherein said tab includes an outer end portion which bears against said radially inner side surface of said dovetail shaped blade root.