| 摘要 |
A gas turbine engine fan blade 26 e.g.of titanium or titanium alloy, comprises a root portion (40, Fig.2) and an aerofoil portion 42 having a leading edge 44 and a trailing edge 46 and concave and convex sides 50, 52. The aerofoil portion has a hollow interior 54 at least partially filled with a vibration damping material 56 having viscoelasticity. The vibration damping material may be formed by mixing an amine terminated polymer and bisphenol a-epichlorohydrin epoxy resin, and may contain glass and/or polymer microspheres. The root portion may be a dovetail or firtree root or may be welded or bonded to a rotor. A method of manufacturing the blade is disclosed. |
