| 摘要 |
PROBLEM TO BE SOLVED: To provide a fan assembly 32 for gas turbine engines 16. SOLUTION: The fan assembly 32 includes a plurality of fan blades 40 that are connected together so that they are arranged in the form of a row 52 in the circumferential direction extended around a rotor disk 74. Each fan blade includes an airfoil section, having first and second sidewalls that are joined each other at a front end 42 and a rear end 44, and is extended in the radial direction between a root 46 and a tip 48. The fan assembly body also includes at least one shroud 60 that is connected to at least one of the plurality of fan blade tips and is extended in the circumferential direction around the rotor disk, and at least a row of rotor blades 90 extended from at least one shroud to the outside in the radial direction. Each rotor blade includes the airfoil, having the first and second sidewalls that are joined together at a front end 92 and a rear end 94. COPYRIGHT: (C)2006,JPO&NCIPI
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