Blade excitation reduction method and arrangement
作者： Xiaolan Hu , Loc Quang Duong
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摘要: An impeller shroud is configured to receive an impeller. The establishes a plurality of air-bleed holes communicate air with are circumferentially distributed about the shroud. circumferential spacing between some adjacent within different than other holes. A diffuser vane direct pressurized combustor, vanes blade exducer. vanes.
lens.org 参考文章(25)
Meherwan P Boyce, Method and apparatus for compressor surge control ,(1973)
Timothy E. Dejoris, Robert M. Zacharias, Donald Kasperski, Steven Mark Schirle, Nick Martin, Asymmetric compressor air extraction method ,(2006)
Anthony B. Parry, GAS TURBINE ENGINE ,(2017)
Karl-Heinz Rohne, Device for extending the performances of a radial compressor ,(1989)
William J Caruso, Boris M Wundt, Turbo-machine blade spacing with modulated pitch ,(1954)
Wei-Shing Chaing, Shioping Oyoung, Frank Lin, Robert Chen, Radial turbine wheel with locally curved trailing edge tip ,(2006)
Daniel L. Gysling, Jonathan S. Simon, Apparatus for the dynamic control of rotating stall and surge in turbo machines and the like ,(1994)
Eric Seinturier, Marc Berthillier, Yvon Cloarec, Structure comprising a rotor and fixed perturbation sources and method for reducing vibrations in said structure ,(2002)
John R. Louie, Donald W. Burns, Method for designing a cyclic symmetric structure ,(2000)
I-Yeu Shen, Jr-Yi Shen, Chaw-Wu Tseng, Method for predicting vibrational characteristics of rotating structures ,(2004)