| 摘要 |
PROBLEM TO BE SOLVED: To provide a method and a device for assembling a gas turbine engine nozzle. SOLUTION: The turbine nozzle 50 of a gas turbine engine 10 includes an outside band 54, an inside band 56 and a plurality of wing-shape vanes 52 mutually connected by the outside band and the inside band. The vanes include, at least, a first wing-shape vane 114 and a second wing-shape vane 110. The first wing-shape vane includes a composite radial fillet 140 extending between the first vane and the outside band. The vanes are connected to the outside band by a single radial fillet 132 alone. COPYRIGHT: (C)2004,JPO&NCIPI
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