| 摘要 |
PROBLEM TO BE SOLVED: To provide a hollow fan blade having internal cavity and rib geometry with improved durability while minimizing weight and cost. SOLUTION: The hollow fan blades for turbo fan gas turbine engines are formed of two separate detail halves 30a. Each detail half 30a has a plurality of cavities 40a-40d machined out to reduce weight and form ribs 42a-42d. The ribs 42a-42d extend continuously and without intersecting each other in order to facilitate machining. The ribs 42a-42d extend in various directions in different regions of the detail half. In at least one region, the ribs 42a-42d extend in a meandering pattern, such that connected rib segments are substantially perpendicular to each other, thereby providing rigidity in multiple directions. COPYRIGHT: (C)2007,JPO&INPIT
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