| 摘要 |
PROBLEM TO BE SOLVED: To provide a light weight and impact resistant fan rotor. SOLUTION: A rotor assembly or "blisk" for a gas turbine engine includes a metallic hub (12) having an annular flowpath surface (14), and at least one of blades (16, 16 and 216) extending outwardly from the flowpath surface (14). The blade includes metallic bodies (18, 118 and 218) having first density. The metallic bodies (18, 118 and 218) define shank portions (22, 122 and 222) and airfoil portions (20, 120 and 220) having opposed pressure and negative pressure faces, and is integral with the hub 12. Inserts (36, 136 and 236) having second density lower than the first density is carried by bodies (18, 118 and 218), and the inserts (36, 136 and 236) and the bodies (18, 118 and 218) collectively define an airfoil shape. A method is also provided for manufacturing a rotor assembly. COPYRIGHT: (C)2007,JPO&INPIT
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