Higher efficiency and higher pressure ratios are required for compressors of aircraft turbo-fan engines in order to achieve a fuel burn reduction. In addition, technical issues related to a smaller core size must be overcome to realize a higher overall pressure ratio and higher bypass ratio of an engine. This paper summarizes the development of axial compressor aerodynamic design technologies that address these subjects, including validation through rig testing. The development of some key structural design technologies to realize the original intent of an aerodynamic design is also described, including higher accuracy variable stator vane actuation, tip clearance reduction, and blade forced response prediction.
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