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- W3140053204 abstract "One of the major challenges in the development of fan and compressor airfoils is high cycle fatigue (HCF) due to flow-induced resonant response. These resonant vibrations occur when a periodic forcing function, with a frequency that coincides with an airfoil natural frequency, acts on a blade row. The most common forcing functions are viscous wakes and shock waves generated by transonic blading. Resonant response is predicted by first determining the natural frequencies of the design rotor. With these airfoil frequencies able to be accurately predicted with finite element models, the Campbell diagram is a key design tool. However, Campbell diagrams provide no measure of the amplitude of the resonant vibration or stress. Thus, the numerous HCF failures in modern and mature aircraft engines have necessitated the development of design analyses that predict the vibration amplitude/stress at the resonant speeds. The driving phenomenon for these flow-induced vibrations is the blade row unsteady aerodynamics. Timeaccurate multi-blade row CFD analyses applied to a sector of the interacting airfoil rows predict the forcing function and the resulting blade row unsteady aerodynamics. Prior to implementing such analyses into the design system, they must first be validated with appropriate data. This is especially true for aggressive designs that feature highlyloaded closely-spaced blade rows as they operate in a highly unsteady flow environment. This paper describes experiments designed to provide benchmark unsteady aerodynamic blade row interaction and rotor response data. Detailed unsteady aerodynamic rotor-IGV and rotor-stator interaction data, as well as rotor response data are obtained in an advanced design transonic research compressor. These detailed data quantify the rotor-generated forcing functions to the upstream IGV and downstream stator vane rows, the resultant IGV and vane row unsteady aerodynamic loading, the vane-to-vane flow fields, as well as the rotor blade vibratory response." @default.
- W3140053204 created "2021-04-13" @default.
- W3140053204 creator A5039408572 @default.
- W3140053204 date "2005-01-10" @default.
- W3140053204 modified "2023-09-26" @default.
- W3140053204 title "Turbomachinery Blade Row Interaction Aerodynamics and Forced Response Experiments" @default.
- W3140053204 cites W2012355073 @default.
- W3140053204 doi "https://doi.org/10.2514/6.2005-15" @default.
- W3140053204 hasPublicationYear "2005" @default.
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