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Background <p>Aeroelastic couplings in bladed wheels such as turbines, compressors and fans remain an active area of investigation. This paper presents a comprehensive experimental study of a linear blade cascade supported by a new analytical model and numerical simulations.</p> Methods <p>The cascade consists of five elastically mounted NACA 0010 blades, each restricted to a single torsional degree of freedom and equipped with electromagnetic actuators capable of both harmonic and short duration pulse excitation. Controlled flutter experiments using both the Travelling Wave Mode and the Aerodynamic Influence Coefficient approaches are performed and compared.</p> Results <p>The aerodynamic damping curve exhibits a sinusoidal dependence on the inter-blade phase angle with a minimum near -90°, and cascade stability decreases with increasing flow velocity while increasing with oscillation frequency. Pulse excitation experiments at flow velocities of 35 m s<InlineEquation ID="IEq1"> <EquationSource Format="TEX">\(^{-1}\)</EquationSource> </InlineEquation> and 40 m s <InlineEquation ID="IEq2"> <EquationSource Format="TEX">\(^{-1}\)</EquationSource> </InlineEquation> reveal transient vibration transmission through aeroelastic couplings, frequency locking among structurally mistuned blades, IBPA evolution, and the development of limit-cycle oscillations. Results obtained with excitation applied to a non central blade further demonstrate the extreme sensitivity of flutter onset to initial conditions when the cascade operates near the stability boundary.</p> Model <p>The experimental findings form the basis for tuning a new phenomenological aeroelastic coupling model embedded within the multi-blade equations of motion. Simulations using the proposed model successfully reproduce the transition between stable and unstable post-pulse behaviour, validating the analytical approach.</p> Conclusions <p>The experimental and modelling framework presented here advances the understanding of aeroelastic instability mechanisms in blade cascades operating near the stability boundary.</p>

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Flutter Onset and Aeroelastic Coupling in a Five-Blade Cascade: From Pulse Excitation Experiments to Analytical Prediction

  • 期刊论文

  • 发表日期：

    2026年6月15日

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  • Pavel Šnábl,
  • Luděk Pešek,
  • Chandra Shekhar Prasad,
  • Pavel Procházka,
  • Vladislav Skála,
  • Sony Chindada

摘要

Background

Aeroelastic couplings in bladed wheels such as turbines, compressors and fans remain an active area of investigation. This paper presents a comprehensive experimental study of a linear blade cascade supported by a new analytical model and numerical simulations.

Methods

The cascade consists of five elastically mounted NACA 0010 blades, each restricted to a single torsional degree of freedom and equipped with electromagnetic actuators capable of both harmonic and short duration pulse excitation. Controlled flutter experiments using both the Travelling Wave Mode and the Aerodynamic Influence Coefficient approaches are performed and compared.

Results

The aerodynamic damping curve exhibits a sinusoidal dependence on the inter-blade phase angle with a minimum near -90°, and cascade stability decreases with increasing flow velocity while increasing with oscillation frequency. Pulse excitation experiments at flow velocities of 35 m s \(^{-1}\) and 40 m s \(^{-1}\) reveal transient vibration transmission through aeroelastic couplings, frequency locking among structurally mistuned blades, IBPA evolution, and the development of limit-cycle oscillations. Results obtained with excitation applied to a non central blade further demonstrate the extreme sensitivity of flutter onset to initial conditions when the cascade operates near the stability boundary.

Model

The experimental findings form the basis for tuning a new phenomenological aeroelastic coupling model embedded within the multi-blade equations of motion. Simulations using the proposed model successfully reproduce the transition between stable and unstable post-pulse behaviour, validating the analytical approach.

Conclusions

The experimental and modelling framework presented here advances the understanding of aeroelastic instability mechanisms in blade cascades operating near the stability boundary.