Classical flutter study in turbomachinery cascade using boundary element method for incompressible flows

Prasad, Chandra Shekhar; Pešek, Luděk

doi:10.1007/978-3-030-20131-9_404

Cited by 5 publications

(3 citation statements)

References 11 publications

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“…play their role, and so far it is impossible to numerically calculate the non-stacionary fluid-structure interaction on a full scale model. In the Institute of Thermomechanics of the CAS we have used reduced order structure models with Van der Pol model to describe the instabilities (Pešek et al, 2023a,b) and also the reduced order flow models (Prasad and Pešek, 2019;Prasad et al, 2023). In order to study the aeroelasticity in a blade cascade experimentally, simplifications have to be made in order to make any measurements possible.…”

Section: Introductionmentioning

confidence: 99%

Investigation of 3D Flow Structures in a Linear Blade Cascade with Stereo Particle Image Velocimetry

Šnábl,

Procházka,

Uruba

et al. 2024

Engineering Mechanics

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In most experiments and numerical calculations of flow through blade cascades, there is a tendency to reduce the problem to 2D. This is understandable due to the design of the experimental rigs and measurement methods, as well as the very long computation times of 3D numerical flow simulations. In reality, however, 3D flow structures such as streamwise vortices begin to appear in wakes behind profiles even for 2D geometry even at low Reynolds nubers. They can create force variations acting along the blade span, which can be represented on average by the 2D measurement and simulation and give a correct result, e.g. for the total lift and drag of the profile. However, when investigating dynamic aeroelastic instabilities such as flutter, local variations in aerodynamic forces can greatly influence the overall behaviour, e.g. by inducing stall flutter.

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Section: Introductionmentioning

confidence: 99%

Investigation of 3D Flow Structures in a Linear Blade Cascade with Stereo Particle Image Velocimetry

Šnábl,

Procházka,

Uruba

et al. 2024

Engineering Mechanics

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“…For example, some issues related to the stable operation of a rotating machine under atypical conditions are still relevant today. It is worth noting, for example, the papers written by T. Szolc [1,2], J. Zapoměl [3,4], and M. Klanner [5] or papers in the fields such as model-based diagnostics and defect identification written by T. Choudhury [6], papers in the field of flutter and vibrations in turbine sets written by C. Prasad [7] and those related to the influence of gyroscopic effects written by R.S. Schittenhelm [8].…”

Section: Introductory Remarksmentioning

confidence: 99%

Bulletin of the Polish Academy of Sciences: Technical Sciences

Kiciński

2021

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Despite many years of development in the field of rotor dynamics, many issues still need to be resolved. This is due to the fact that turbomachines, even those with low output power, have a very complex design. The author of this article would like to signal these issues in the form of several questions, to which there are no precise answers. The questions are as follows: How can we build a coherent dynamic model of a turbomachine whose some subsystems have non-linear characteristics? How can we consider the so-called prehistory in our analysis, namely, the relation between future dynamic states and previous ones? Is heuristic modelling the future of rotor dynamics? What phenomena may occur when the stability limit of the system is exceeded? The attempt to find answers to these questions constitutes the subject of this article. There are obviously more similar questions, which encourage researchers from all over the world to further their research.

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“…Moreover, the equivalent technique is also adopted for aeroelastic modeling of wind turbines [12][13][14], helicopter rotors, and aircraft aeroelasticity problems [10,15]. Also the classical BEM-PM was used by the author to model 2D classical flutter analysis in the past [16,17]. The AD for different Inter blade phase angle (IBPA) for traveling wave mode oscillation is estimated using the proposed hybrid BEM-based flow model.…”

Section: Introductionmentioning

confidence: 99%

Bulletin of the Polish Academy of Sciences: Technical Sciences

Prasad,

Šnábl,

Pešek

2021

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The analysis of subsonic stall flutter in turbomachinery blade cascade is carried out using a medium-fidelity reduced-order aeroelastic numerical model. The model is a type of field mesh-free approach and based on a hybrid boundary element method. The medium-fidelity flow solver is developed on the principle of viscous-inviscid two-way weak-coupling approach. The hybrid flow solver is employed to model separated flow and stall flutter in the 3D blade cascade at subsonic speed. The aerodynamic damping coefficient w.r.t. inter blade phase angle in traveling-wave mode is estimated along with other parameters. The same stability parameter is used to analyze the cascade flutter resistance regime. The estimated results are validated against experimental measurements as well as Navier-Stokes based high fidelity CFD model. The simulated results show good agreement with experimental data. Furthermore, the hybrid flow solver has managed to bring down the computational cost significantly as compared to mesh-based CFD models. Therefore, all the prime objectives of the research have been successfully achieved.

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Classical flutter study in turbomachinery cascade using boundary element method for incompressible flows

Cited by 5 publications

References 11 publications

Investigation of 3D Flow Structures in a Linear Blade Cascade with Stereo Particle Image Velocimetry

Investigation of 3D Flow Structures in a Linear Blade Cascade with Stereo Particle Image Velocimetry

Bulletin of the Polish Academy of Sciences: Technical Sciences

Bulletin of the Polish Academy of Sciences: Technical Sciences

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