A Study on Fluid Self-Excited Flutter and Forced Response of Turbomachinery Rotor Blade

Hsu, Chih Neng

doi:10.1155/2014/437158

Cited by 3 publications

(3 citation statements)

References 42 publications

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“…In working turbine machines, blades are forced to vibrate by the periodic wakes of rotating upstream blades. 1 This forced vibration is considered to be one of the critical reasons for the blade fatigue. [2][3][4] Experiments also show that the aeroelastic stability of rotor blades are influenced by the wakes.…”

Section: Introductionmentioning

confidence: 99%

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An aerodynamic ROM of the blade subjected to wake based on Fourier method for flow

Zhang²,

Xiao

et al. 2018

Numerical Methods in Fluids

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Summary A reduced‐order model (ROM) is presented based on Fourier method for flow to predict aerodynamic forces of blades subjected to periodic time‐varying upstream wakes. In the method, a time‐varying wake is decomposed into harmonic waves by fast Fourier transformation. Using the Fourier method for flow and neglecting the cross‐coupling between harmonics, the aerodynamic forces caused by the wake are represented by a linear combination of harmonics with the same frequencies as the wake. The coefficients of the aerodynamic force harmonics are interpolated at the per‐fitted curves of the normalized Fourier coefficients (coefficients of aerodynamic forces harmonics corresponding to a unit simple harmonic excitation)–frequency relationship. A blade example is used to show the ability of the proposed method. The results indicate that the ROM method can predict the aerodynamic forces of blades caused by wakes efficiently and accurately. The amplitude levels of wakes have a linear impact on the accuracy of the ROM. Neglecting the higher‐order cross‐coupling between the harmonics in the ROM method is acceptable.

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Section: Introductionmentioning

confidence: 99%

“…In working turbine machines, blades are forced to vibrate by the periodic wakes of rotating upstream blades . This forced vibration is considered to be one of the critical reasons for the blade fatigue .…”

Section: Introductionmentioning

confidence: 99%

An aerodynamic ROM of the blade subjected to wake based on Fourier method for flow

Zhang²,

Xiao

et al. 2018

Numerical Methods in Fluids

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“…Existing test and data processing methods are a workable foundation for further theoretical development hypersonic aircraft simulation techniques. "Flutter" is a phenomenon characterized by system instability due to structural modal coupling [14][15][16] as evidenced by the structural response of undamped oscillation. In a hypersonic flutter test, structural responses directly reflect the process of modal change and energy alternation; the responses provide useful indicators of various flutter trends.…”

Section: Introductionmentioning

confidence: 99%

Novel Nonstationarity Assessment Method for Hypersonic Flutter Flight Tests

Zheng

Liu

Duan

2018

Mathematical Problems in Engineering

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Hypersonic aircraft have been rapidly developed in recent years both theoretically and experimentally. Aerothermoelastic simulation is very challenging due to its inherent complexity, but physical tests are a workable approach. Flutter tests with variable speed are a popular alternative to hypersonic tests which provide nonstationary structural response data. This paper proposes a nonstationarity assessment method based on energy distribution in the time-frequency domain. The proposed method reveals the nonstationarity level corresponding to the appropriate modal identification algorithm or flutter boundary prediction (FBP) method. Several classic flutter criteria are utilized to build a hypersonic aircraft FBP framework. Numerical simulation and experimental applications demonstrate the effectiveness and feasibility of the proposed method, which facilitates accurate flutter predictions for the subcritical turbulence response during hypersonic flutter flight.

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Flutter Analysis of Last Stage Steam Turbine Power Plant Blade Through Transient Blade Row Simulation

Laksana¹,

Kokong²,

Sigit³

et al. 2021

IOP Conf. Ser.: Mater. Sci. Eng.

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Flutter phenomena becomes significant in response with turbomachinery design trends that prioritize efficiency. Especially in later stages of steam turbines, the slender profile of the blade becomes more prone to unstable dynamic aeroelasticity. Predicting the potential of flutter on a turbine blade can be done by constructing aeroelastic stability curve with evaluation of aerodynamic damping value under different rotor blade position, relative to the stator blade (inter blade phase angle). In this study, combination of steady Computational Fluid Dynamics (CFD), structural Finite Element Analysis (FEA) and transient blade row CFD was carried out using ANSYS 2019 R2 with the end goal of constructing aeroelastic stability curve and analysing the flutter risk of a 350 MW last stage steam turbine blade. At inter blade phase angle position of -180°, -70°, 0°, 77° and 180°, the system are exhibits positive aerodynamic damping values which indicates low to none flutter potential.

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A Study on Fluid Self-Excited Flutter and Forced Response of Turbomachinery Rotor Blade

Cited by 3 publications

References 42 publications

An aerodynamic ROM of the blade subjected to wake based on Fourier method for flow

An aerodynamic ROM of the blade subjected to wake based on Fourier method for flow

Novel Nonstationarity Assessment Method for Hypersonic Flutter Flight Tests

Flutter Analysis of Last Stage Steam Turbine Power Plant Blade Through Transient Blade Row Simulation

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