Deficiencies in Turbulence Modelling for the Prediction of the Stability Boundary in Highly Loaded Compressors

Moreno, José Manuel Díaz; Dodds, John A.; Vahdati, Mehdi; Stapelfeldt, Sina

doi:10.1115/gt2019-91227

Cited by 6 publications

(3 citation statements)

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“…The parameters in Spalart-Allmaras have been adjusted on previous fans to get good agreement near the stability limit; the parameters are held constant in all the present work. Some recent publications regarding the improvements can be found in Lee et al (2018) and Moreno et al (2019). The resulting CFD code has been used over the past 20 years for flows at off-design conditions with a good degree of success; see, for example, Vahdati et al (2011), Choi et al (2012) and Dodds and Vahdati (2015).…”

Section: Flow Solvermentioning

confidence: 99%

An Overview of Time-Domain Computational Methods for Aeroelastic Instabilities of Multi-Stage Compressor

Vahdati

Zhao

Sureshkumar

2020

J. Glob. Power Propuls. Soc.

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Modern gas turbine design continues to move towards improved performance, reduced weight and reduced cost. As turbomachinery blade aerofoils are thinned to improve performance and reduce weight, aeroelastic issues such as flutter, forced response and stall driven vibrations become more predominant. Moreover, as the use of blisks (blade-integrated-disks) with very low mechanical damping becomes more common in modern compressor designs, accurate prediction of compressor aeroelastic stability in a multi-row environment becomes vital. This paper presents a review of aeroelasticity research carried out at Rolls-Royce Vibration University Technology Centre (VUTC) at Imperial College over the past 20 years. The aim is to summarise the unusual aeroelastic issues observed in multi-stage compressors into one document so that it can be used by other researchers in the field. Blade passing forced response is not addressed here as their existence can be detected by a Campbell diagram. The results presented here are based on numerical methods but where possible data from experiments are used to verify the numerical findings.

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Section: Flow Solvermentioning

confidence: 99%

An Overview of Time-Domain Computational Methods for Aeroelastic Instabilities of Multi-Stage Compressor

Vahdati

Zhao

Sureshkumar

2020

J. Glob. Power Propuls. Soc.

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Section: Flow Solvermentioning

confidence: 99%

A Review of Computational Methods for Aeroelastic Instabilities of Multi-Stage Compressor

Vahdati¹,

Zhao²,

Sureshkumar³

2019

Proceedings of Global Power &Amp; Propulsion Society

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Modern gas turbine design continues to move towards improved performance, reduced weight and reduced cost. As turbomachinery blade aerofoils are thinned to improve performance and reduce weight, aeroelastic issues such as flutter, forced response and stall driven vibrations become more predominant. Moreover, as the use of blisks (bladeintegrated-disks) with very low mechanical damping becomes more common in modern compressor designs, accurate prediction of compressor aeroelastic stability in a multi-row environment becomes vital. This paper presents a review of aeroelasticity research carried out at Rolls-Royce Vibration University Technology Centre (VUTC) at Imperial College over the past 20 years. The aim is to summarise the unusual aeroelastic issues observed in multi-stage compressors into one document so that it can be used by other researchers in the field. Blade passing forced response is not addressed here as their existence can be detected by a Campbell diagram. The results presented here are based on numerical methods but where possible data from experiments are used to verify the numerical findings.

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“…They found that the SST turbulence model was better at predicting the stall region while the SST−CC turbulence model was better at predicting the compressor machine performance curve. Using the Spalart-Allmaras turbulence model, Moreno et al [12] carried out numerical simulations on an axial compressor and assessed the variables influencing the numerical results. It was shown that the destruction term in the SA model can have an impact on the stall margin loss.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Transonic Compressors with Different Turbulence Models

Yan,

Sun,

Zhou

et al. 2023

Aerospace

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One of the most commonly used techniques in aerospace engineering is the RANS (Reynolds average Navier–Stokes) approach for calculating the transonic compressor flow field, where the accuracy of the computation is significantly affected by the turbulence model used. In this work, we use SA, SST, k-ɛ, and the PAFV turbulence model developed based on the side-biased mean fluctuations velocity and the mean strain rate tensor to numerically simulate the transonic compressor NASA Rotor 67 to evaluate the accuracy of turbulence modeling in numerical calculations of transonic compressors. The simulation results demonstrate that the four turbulence models are generally superior in the numerical computation of NASA Rotor 67, which essentially satisfies the requirements of the accuracy of engineering calculations; by comparing and analyzing the ability of the four turbulence models to predict the aerodynamic performance of transonic compressors and to capture the details of the flow inside the rotor. The errors of the Rotor 67 clogging flow rate calculated by the SA, SST, k-ɛ, and PAFV turbulence models with the experimental data are 0.9%, 0.8%, 0.7%, and 0.6%, respectively. The errors of the calculated peak efficiencies are 2.2%, 1.6%, 0.9%, and 4.9%. The SA and SST turbulence models were developed for the computational characteristics of the aerospace industry. Their computational stability is better and their outputs for Rotor 67 are comparable. The k-ɛ turbulence model calculates the pressure ratio and efficiency that are closest to the experimental data, but the computation of its details of the flow field near the wall surface is not ideal because the k-ɛ turbulence model cannot accurately capture the flow characteristics of the region of high shear stresses. The PAFV turbulence model has a better prediction of complex phenomena such as rotor internal shock wave location, shock–boundary layer interaction, etc., due to the use of a turbulent velocity scale in vector form, but the calculated rotor efficiency is small.

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Deficiencies in Turbulence Modelling for the Prediction of the Stability Boundary in Highly Loaded Compressors

Cited by 6 publications

References 0 publications

An Overview of Time-Domain Computational Methods for Aeroelastic Instabilities of Multi-Stage Compressor

An Overview of Time-Domain Computational Methods for Aeroelastic Instabilities of Multi-Stage Compressor

A Review of Computational Methods for Aeroelastic Instabilities of Multi-Stage Compressor

Numerical Simulation of Transonic Compressors with Different Turbulence Models

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