Three-dimensional through-flow modelling of axial flow compressor rotating stall and surge

Righi, Mauro; Pachidis, Vassilios; Könözsy, László; Pawsey, Lucas

doi:10.1016/j.ast.2018.04.021

Cited by 49 publications

(39 citation statements)

References 18 publications

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“…A three-dimensional, through-flow code has been developed at Cranfield University called ACRoSS, Axial Compressor Rotating Stall and Surge simulator. The code has been validated for the modelling of rotating stall and surge in low-speed compressors (Righi et al, 2018) and has also been further developed to be applicable to high-speed modern compressors (Righi et al, 2019). This paper describes the validation of the surge modelling capability of ACRoSS for a modern, high-speed, aero-engine compressor, comparing results against high-fidelity simulations carried out by Imperial College using their in-house code AU3D.…”

Section: Figure 1 -Example Of Rotating Stall and Deep Surge Trajectormentioning

confidence: 99%

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Three-dimensional low-order surge model for high-speed axial compressors

Righi¹,

Pachidis²,

Könözsy³

et al. 2020

Proceedings of Global Power &Amp; Propulsion Society

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Surge in modern aero-engines can lead to violent disruption of the flow, damage to the blade structures and eventually engine shutdown. Knowledge of unsteady performance and loading during surge is crucial for compressor design, however, the understanding and prediction capability for this phenomenon is still very limited. While useful for the investigation of specific cases, costly experimental tests and high-fidelity CFD simulations cannot be used routinely in the design process of compressor systems. There is therefore an interest in developing a low-order model which can predict compressor performance during surge with sufficient accuracy at significantly reduced computational cost. This paper describes the validation of an unsteady 3D through-flow code developed at Cranfield University for the low-order modelling of surge in axial compressors. The geometry investigated is an 8-stage rig representative of a modern aero-engine IP compressor. Two deep surge events are modelled at part speed and full speed respectively. The results are compared against high-fidelity, full annulus, URANS simulations conducted at Imperial College. Comparison of massflow, pressure and temperature time histories shows a close match between the low-order and the higher-fidelity methods. The low-order model is shown capable of predicting many transient flow features which were observed in the high-fidelity simulations, while reducing the computational cost by up to two orders of magnitude.

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Section: Figure 1 -Example Of Rotating Stall and Deep Surge Trajectormentioning

confidence: 99%

“…For stalled and reverse flow conditions instead algorithms specifically developed are used which modify the body force application. These have been developed from the theory proposed by Longley (Longley, 2007), a description is given in (Righi et al, 2018).…”

Section: Through-flow Code -Acrossmentioning

confidence: 99%

Three-dimensional low-order surge model for high-speed axial compressors

Righi¹,

Pachidis²,

Könözsy³

et al. 2020

Proceedings of Global Power &Amp; Propulsion Society

Self Cite

View full text Add to dashboard Cite

show abstract

“…Application. The results of using the model within ACRoSS (Axial Compressor Rotating Stall and Surge), a 3D Euler code [31], and a 1D mean-line tool are shown and compared against 3D CFD and experiment in Figs. 18 and 19.…”

Section: Resultsmentioning

confidence: 99%

A Loss and Deflection Model for Compressor Blading at High Negative Incidence

Ferrer-Vidal

Schneider

Allegretti

et al. 2019

Journal of Turbomachinery

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While significant advances have come about for turbomachinery off-design performance characterization using computational fluid dynamics (CFD), the need for quick performance estimates at challenging off-design conditions still requires the use of lower-order models, such as mean-line analyses and through-flow tools. These inviscid tools require blade performance correlations formulated in terms of loss and turning angle as a function of blade geometric and aerodynamic parameters. Traditionally, such correlations have relied on the empirical data from blade cascade tests at nominal incidence conditions. This limitation on the applicability of the blade correlations has caused performance modeling of the sub-idle regime to be off-limits to this type of correlation-based approaches. This paper addresses the development of blade loss and deviation models applicable to the sub-idle regime using a parametric numerical approach. 2D CFD results are used to generate a model that is then applied to mean-line and through-flow analyses aimed at predicting the sub-idle map of an axial flow compressor. The model proves to be a valuable tool for quick sub-idle performance estimates and allows existing correlation-based performance prediction methods to be extended into the sub-idle regime.

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“…Low-frequency noise from the impeller was found to be relative to the rotating stall. Currently, researchers still focus on the rotating stall phenomenon in turbomachinery, which has complicated flow characteristics [27][28][29]. In pumps which usually transport incompressible Many researchers studied the rotation stall mechanism and influences [14][15][16][17].…”

Section: Introductionmentioning

confidence: 99%

Influence of Blade Leading-Edge Shape on Rotating-Stalled Flow Characteristics in a Centrifugal Pump Impeller

et al. 2020

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Rotating stall, which is a common phenomenon in turbomachinery, strongly relates to the flow rate condition. In centrifugal impellers, rotating stall was induced by the incidence angle on blade leading-edge at partial-load. The blade leading-edge shape also influences the rotating stall because of the subtle change of local flow-field. In this study, the influence of blade leading-edge shape on rotating-stalled flow characteristics was studied in a six-blade centrifugal pump impeller. The stall pattern was “alternating”: Three passages were stalled, three passages were well-behaved, and the stalled and well-behaved passages occurred alternately. The stalled flow characteristics can be studied without the interruption of stall cell movement. Four types of blade leading-edge (blunt, sharp, ellipse, and round) were numerically compared based on the initial typical impeller and the numerical–experimental verification. The numerical comparison shows that the leading-edge shape has a strong influence on the stalled flow pattern, velocity, pressure, turbulence kinetic energy, and flow-induced noise inside impellers. The blunt and sharp leading-edge impellers had a similar internal pattern; the ellipse and round leading-edge impellers were also similar in the internal flow-field. Pressure pulsation analysis showed more obvious differences among these impellers. The main frequency and the pulsation peak–peak values were completely different because of the slight leading-edge shape differences. It revealed the impact of leading-edge geometry on the transient flow-field change under the same incidence angle conditions. It also provided reference for influencing or controlling the rotating stall by blade profile design.

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Three-dimensional through-flow modelling of axial flow compressor rotating stall and surge

Cited by 49 publications

References 18 publications

Three-dimensional low-order surge model for high-speed axial compressors

Three-dimensional low-order surge model for high-speed axial compressors

A Loss and Deflection Model for Compressor Blading at High Negative Incidence

Influence of Blade Leading-Edge Shape on Rotating-Stalled Flow Characteristics in a Centrifugal Pump Impeller

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