RADIAL LOCK FOR FAN BLADE SHEATH

摘要

A turbojet fan blade (132) adapted for securement to an engine rotor (130) includes a titanium sheath (150) that extends continuously over its leading edge (142) from blade tip (148) to blade root (146). The sheath (150) provides impact protection over the leading edge (142) of the blade (132), and also incorporates enhanced radial securement of the sheath (150) to the rotor (130). As such, a radial lock system for the sheath (150) is disclosed that includes a fully integrated sheath portion that extends completely over the frontal face (170) of a fan blade dovetail, providing a radial lock of the sheath (150) to the rotor (130) in the event of failure of any adhesive (158) used to attach the sheath (150) to the leading edge (142). Because the sheath (150) extends continuously from blade tip (148) to the blade root (146), lightning strike protection is enhanced by avoidance of any discontinuities otherwise associated with related art sheaths that typically extend over only a flow path portion of the leading edge.