Poststall Behavior of a Multistage High Speed Compressor at Off-Design Conditions

Journal of Turbomachinery - Tập 140 Số 12 - 2018
Fanzhou Zhao1, John A. Dodds2, Mehdi Vahdati1
1Department of Mechanical Engineering, Imperial College London, London SW7 2AZ, UK e-mail:
2Rolls-Royce plc, P.O. Box 31, Derby DE24 8BJ, UK e-mail:

Tóm tắt

Stall followed by surge in a high speed compressor can lead to violent disruption of flow, damage to the blade structures and, eventually, engine shutdown. Knowledge of unsteady blade loading during such events is crucial in determining the aeroelastic stability of blade structures; experimental test of such events is, however, significantly limited by the potential risk and cost associated. Numerical modeling, such as unsteady computational fluid dynamics (CFD) simulations, can provide a more informative understanding of the flow field and blade forcing during poststall events; however, very limited publications, particularly concerning multistage high speed compressors, can be found. The aim of this paper is to demonstrate the possibility of using CFD for modeling full-span rotating stall and surge in a multistage high speed compressor, and, where possible, validate the results against experimental measurements. The paper presents an investigation into the onset and transient behavior of rotating stall and surge in an eight-stage high speed axial compressor at off-design conditions, based on 3D Reynolds-averaged Navier–Stokes (URANS) computations, with the ultimate future goal being aeroelastic modeling of blade forcing and response during such events. By assembling the compressor with a small and a large exit plenum volume, respectively, a full-span rotating stall and a deep surge were modeled. Transient flow solutions obtained from numerical simulations showed trends matching with experimental measurements. Some insights are gained as to the onset, propagation, and merging of stall cells during the development of compressor stall and surge. It is shown that surge is initiated as a result of an increase in the size of the rotating stall disturbance, which grows circumferentially to occupy the full circumference resulting in an axisymmetric flow reversal.

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Tài liệu tham khảo

2015, Stall, Surge, and 75 Years of Research, ASME J. Turbomach., 138, 011001, 10.1115/1.4031473

1995, Prestall Behavior of Several High-Speed Compressors, ASME J. Turbomach., 117, 62, 10.1115/1.2835644

1994, Axial Compressor Performance During Surge, J. Propul. Power, 10, 329, 10.2514/3.23760

1998, A Study of Spike and Modal Stall Phenomena in a Low-Speed Axial Compressor, ASME J. Turbomach., 120, 393, 10.1115/1.2841730

1976, Surge and Rotating Stall in Axial Flow Compressors—Part I: Theoretical Compression System Model, ASME J. Eng. Power, 98, 190, 10.1115/1.3446138

1994, The Unstable Behavior of Low and High-Speed Compressors, ASME J. Turbomach., 116, 194, 10.1115/1.2928353

1980, Surge-Induced Structural Loads in Gas Turbines, ASME J. Eng. Power, 102, 162, 10.1115/1.3230217

2008, Unsteady Flow and Aeroelasticity Behavior of Aeroengine Core Compressors During Rotating Stall and Surge, ASME J. Turbomach., 130, 031017, 10.1115/1.2777188

2012, Validation of Numerical Simulation for Rotating Stall in a Transonic Fan, ASME J. Turbomach., 135, 021004, 10.1115/1.4006641

2014, Numerical Simulation of Aerodynamic Instabilities in a Multistage High-Speed High-Pressure Compressor on Its Test Rig—Part II: Deep Surge, ASME J. Turbomach., 136, 101004, 10.1115/1.4027968

2015, Rotating Stall Observations in a High Speed Compressor—Part II: Numerical Study, ASME J. Turbomach., 137, 051003, 10.1115/1.4028558

2015, Rotating Stall Observations in a High Speed Compressor—Part I: Experimental Study, ASME J. Turbomach., 137, 051002, 10.1115/1.4028557

2000, Modeling of Three-Dimensional Viscous Compressible Turbomachinery Flows Using Unstructured Hybrid Grids, AIAA J., 38, 945, 10.2514/2.1062

2018, Validation of a Numerical Model for Predicting Stalled Flows in a Low-Speed Fan—Part I: Modification of Spalart–Allmaras Turbulence Model, ASME J. Turbomach., 140, 051008, 10.1115/1.4039051

2011, Mechanisms for Wide-Chord Fan Blade Flutter, ASME J. Turbomach., 133, 041029, 10.1115/1.4001233

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Journal of Turbomachinery

Tập 140 Số 12

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