Investigation of Efficient CFD Methods for Rotating Stall Prediction in a Centrifugal Compressor Stage

DeMore, Daniel; Maghsoudi, Elham; Pacheco, Jorge E.; Sorokes, James M.; Hutchinson, Brad; Holmes, William M.; Lobo, Bryan; Vashistha, Vaibhav

doi:10.1115/gt2014-27097

Cited by 3 publications

(2 citation statements)

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“…However, steady calculations were also performed to predict the overall performance and to initialize the unsteady calculations. The steady method uses a mixing plane (MP) type of approach called a "Stage Interface" where momentum and energy are conserved across the interface, but entropy increases as DeMore et al (2014), the number of blades included in the simulation has a significant effect on both the predicted stall inception mass flow rate and the number of stall cells. The Unsteady flow in the considered centrifugal compressor stage was modelled using the TT method based on the time inclining work of Giles (1987Giles ( , 1990.…”

Section: Numerical Modellingmentioning

confidence: 99%

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The Efficient Numerical Simulation of Unsteady Flow in a Centrifugal Compressor Stage Equipped with a Vaned Diffuser

Corneloup¹,

Moyroud²,

Younsi

et al. 2017

European Conference on Turbomachinery Fluid Dynamics and Hermodynamics

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Section: Numerical Modellingmentioning

confidence: 99%

“…Recently, DeMore et al (2014) investigated the Time Transformation (TT) method for a range of configurations to predict the rotating stall. They compared the results from each configuration to steady and transient results on the same mesh.…”

Section: Introductionmentioning

confidence: 99%

The Efficient Numerical Simulation of Unsteady Flow in a Centrifugal Compressor Stage Equipped with a Vaned Diffuser

Corneloup¹,

Moyroud²,

Younsi

et al. 2017

European Conference on Turbomachinery Fluid Dynamics and Hermodynamics

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Numerical and Experimental Study on Rotating Stall in Industrial Centrifugal Compressor

Miura

Yamashita

Takeuchi

et al. 2021

Journal of Turbomachinery

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Centrifugal compressors employed in the oil and gas industry are operated at high gas pressure conditions and are used in a wide operation range. Accurate prediction of the rotating stall and the destabilizing aerodynamic force is one of the key technologies for these compressors. The aim of this study is to establish a method of accurately predicting the inception of rotating stall and its effect on shaft vibration. To achieve this, numerical investigations are carried out by unsteady flow and rotodynamic simulations. To validate the accuracy, an experiment is carried out at relatively high gas pressure conditions. In the first part of the study, the accuracy of compressor performance prediction is studied by steady computational fluid dynamics (CFD) simulation. It is found that by taking the wall roughness effect into account, the predicted performance shows good agreement with the experimental result. In the second part of the study, the accuracy of predicting the rotating stall is studied. In the experiment, two types of rotating stall are measured. One is a multiple-cell stall induced in the vaneless diffuser and the other is a one-cell stall induced in the impeller. It is found that the simulation can predict the inception of the rotating stall with relatively high accuracy as the predicted results show good agreement with the experimental results in terms of cell count, rotation speed, pressure fluctuation level and the effect on shaft vibration. Through this study, the effectiveness of simulation is validated for the stall and vibration prediction.

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Forced Response Excitation due to the Stator Vanes of Two and Three Compressor Stages Away

Miura

Sakai

Kanazawa

et al. 2021

Volume 9A: Structures and Dynamics — Aerodynamics Excitation and Damping; Bearing and Seal Dynamics; Emerging Methods in Design

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State-of-the-art axial compressors of gas turbines employed in power generation plants and aero engines should have both high efficiency and small footprint. Thus, in many cases, axial compressors are designed to have thin rotor blades and stator vanes with short axial distances, and are driven at high rotational speed. Recently, problems of high cycle fatigue (HCF) associated with forced response excitation have gradually increased as a result of these trends. Rotor blade fatigue can be caused not only by the wake and potential effect of the adjacent stator vane, but also by the stator vanes of two, three or four compressor stages away. Thus, accurate prediction and suppression method of them under the resonance condition are necessary in the design process. Concerning the forced response excitation associated with the adjacent stator vanes, there are many previous studies on simulating the vibration by fluid structure interaction (FSI) simulation. In these studies, the aerodynamic force acting on the blade is simulated by an efficient unsteady computational fluid dynamics (CFD) method such as the nonlinear harmonic (NLH) method. These methods can be available in commercial CFD solvers and can significantly reduce computational cost. However, there are few examples of the problems associated with the stator vanes from two and three compressor stages away and no efficient simulation method is available. In this study, the problem of rotor blade vibration caused by the stator vanes of two and three compressor stages away is studied. Ways to accurately predict and effectively control the vibration are also investigated. In the first part of the study, one-way FSI simulation is carried out using a full annulus CFD model. To validate the accuracy of the simulation, experiments are also conducted using a gas turbine test facility. The vibration level of the blade is measured using a blade tip timing (BTT) measurement system and the obtained results are compared with the simulated data. It is found that one-way FSI simulation can accurately predict the order of the vibration level. In the second part of the study, a method of controlling the forced response excitation is investigated by optimizing the clocking of the stator vanes. It is confirmed that by controlling the clocking of the stator vanes, the vibration amplitude can be effectively suppressed without reducing the compressor performance. Through this study, ways to evaluate and control the unsteady pressure force and vibration response of the rotor blade are validated. By optimizing the clocking of stator vanes, the blade vibration level can be effectively reduced.

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Investigation of Efficient CFD Methods for Rotating Stall Prediction in a Centrifugal Compressor Stage

Cited by 3 publications

References 0 publications

The Efficient Numerical Simulation of Unsteady Flow in a Centrifugal Compressor Stage Equipped with a Vaned Diffuser

The Efficient Numerical Simulation of Unsteady Flow in a Centrifugal Compressor Stage Equipped with a Vaned Diffuser

Numerical and Experimental Study on Rotating Stall in Industrial Centrifugal Compressor

Forced Response Excitation due to the Stator Vanes of Two and Three Compressor Stages Away

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