Radial compressor of asymmetric cyclic sector with coupled blades tuned at anti-nodes
作者： Xiaolan Hu , Loc Q. Duong , Shiv C. Gupta
DOI:
关键词: Gas compressor 、 Leading edge 、 Range (aeronautics) 、 Engineering 、 Gas turbines 、 Operating speed 、 Structural engineering 、 Natural frequency 、 Blade (geometry) 、 Acoustics
摘要: A gas turbine engine includes a radial compressor having first and second blades. The blade has tuned leading edge that prevents either from exciting at natural frequency speeds within an expected operating speed range.
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