초록 ▼

A fan section for a gas turbine engine includes a fan hub having a slot. A platform is supported by the fan hub. A fan blade has a root that is received in the slot. A wear pad is provided between the fan hub and the root and includes a flap integral with the wear pad to provide a seal relative to t

A fan section for a gas turbine engine includes a fan hub having a slot. A platform is supported by the fan hub. A fan blade has a root that is received in the slot. A wear pad is provided between the fan hub and the root and includes a flap integral with the wear pad to provide a seal relative to the platform. A fan blade for a gas turbine engine includes an airfoil extending from a root. A wear pad is secured to the root and has a free end providing a flap canted toward the root.

대표청구항 ▼

1. A fan section for a gas turbine engine comprising; a fan hub having a slot;a platform supported by the fan hub;a fan blade having a root received in the slot; anda wear pad provided between the fan hub and the root and adhered to the root, and including a flap integral with the wear pad to provid

1. A fan section for a gas turbine engine comprising; a fan hub having a slot;a platform supported by the fan hub;a fan blade having a root received in the slot; anda wear pad provided between the fan hub and the root and adhered to the root, and including a flap integral with the wear pad to provide a seal relative to the platform; anda secondary flap adhered to the fan blade and adjoining the flap, the secondary flap sealing against the platform. 2. The fan section according to claim 1, wherein the flap seals against the platform. 3. The fan section according to claim 1, wherein a coating provided on the airfoil adjoins the secondary flap. 4. The fan section according to claim 1, wherein the wear pad and flap are an elastomeric material. 5. The fan section according to claim 4, wherein the wear pad is provided by a fabric weave. 6. The fan section according to claim 5, wherein the fabric weave is provided by a meta-aramid modified nylon material. 7. The fan section according to claim 1, wherein the fan blade is an aluminum alloy. 8. The fan section according to claim 7, wherein the fan hub is a titanium alloy. 9. The fan section according to claim 1, comprising an epoxy adhesive securing the wear pad to the fan blade. 10. The fan section according to claim 1, wherein a fold joins the flap and the secondary flap. 11. A fan blade for a gas turbine engine comprising: an airfoil extending from a root;a wear pad adhered the root and having a free end providing a flap canted toward the root; anda secondary flap adhered to the fan blade and adjoining the flap. 12. The fan blade according to claim 11, wherein a coating provided on the airfoil adjoins the secondary flap. 13. The fan blade according to claim 11, wherein the wear pad and flap are an elastomeric material. 14. The fan blade according to claim 13, wherein the wear pad is provided by a fabric weave. 15. The fan blade according to claim 14, wherein the fabric weave is provided by a meta-aramid modified nylon material. 16. The fan blade according to claim 11, wherein the fan blade is an aluminum alloy. 17. The fan blade according to claim 11, comprising an epoxy adhesive securing the wear pad to the fan blade. 18. The fan blade according to claim 11, wherein a fold joins the flap and the secondary flap.