| Over the past 20-30 years, the thrust to weight ratio of aircraft engines has increased and specific fuel consumption has been substantially reduced. At the same time, the advance in aircraft propulsion performance has stimulated progress in structure and material technology. The weight reduction is the most effective measures for increasing the thrust to weight ratios of areoengines. A significant factor in promoting this trend is to reduce the fan blade weight of turbofan engines. The fan blade of a high bypass ratio engine provides a challenging design task, requiring a compromise among the conflicting demands of aerodynamic performance, weight, vibration, noise, structural integrity and reliability, all for an acceptable production cost. The development of hollow titanium wide chord fan blade (WCFB) for turbofan engines is an important example of a significant factor toward achieving the goal. The development of hollow wide chord fan blades is described in this paper. The mechanical design of the fan blades, its manufacturing method (SPF/DB)with particular reference to structural and metallurgical characteristics are discussed. Comparing with the others, the SPF/DB fabrication process is an outstanding candidate for manufacturing advanced hollow blades. Structural parameters analysis is presented for the hollow modal fan blades. The fan blade is modeled and analyzed using the ANSYS software. The structural performances of fan blades are compared with the different hollow section parameters of the fan blades. The result shows that the different hollow sections can be selected (designed) to substantially modify the mechanical performance of the hollow fan blades. The stress and vibration analysis is taken for the typical hollows titanium fan blade. The result shows that the data is very useful for the hollow fan blade design in future. A kind of the mechanical design and the structural analysis methods of wide chord hollow fan blades are developed in this paper.
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