Experimental Investigation of the Three-Dimensional Flow in an Annular Compressor Cascade

Schulz, Henrik; Gallus, H. E.

doi:10.1115/1.3262220

Cited by 79 publications

(57 citation statements)

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“…The RGW annular compressor [25] features a fully three-dimensional flow, including sidewall boundary layers originating upstream of the blade. This flow topology poses a major challenge to standard correlation-based transition models, as complex logic would be required to distinguish between the different boundary layers.…”

Section: Rgw Compressor Cascadementioning

confidence: 99%

Transition Modelling for General Purpose CFD Codes

Menter

Langtry

Völker

2006

Flow Turbulence Combust

643

201

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The paper addresses modelling concepts based on the RANS equations for laminar-turbulent transition prediction in general-purpose CFD codes. Available models are reviewed, with emphasis on their compatibility with modern CFD methods. Requirements for engineering transition models suitable for industrial CFD codes are specified. A new concept for transition modeling is introduced. It is based on the combination of experimental correlations with locally formulated transport equations. The concept is termed LCTM -Local Correlation-based Transition Model. An LCTM model, which satisfies most of the specified requirements is described, including results for a variety of different complex applications. An incremental approach was used to validate the model, first on 2D flat plates and airfoils and then on to progressively more complicated test cases such as a threeelement flap, a 3D transonic wing and a full helicopter configuration. In all cases good agreement with the available experimental data was observed. The authors believe that the current formulation is a significant step forward in engineering transition modeling, as it allows the combination of transition correlations with general purpose CFD codes. There is a strong potential that the model will allow the 1st order effects of transition to be included in everyday industrial CFD simulations.

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Section: Rgw Compressor Cascadementioning

confidence: 99%

Transition Modelling for General Purpose CFD Codes

Menter

Langtry

Völker

2006

Flow Turbulence Combust

643

201

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“…Hence, in the past few decades, it was always a key flow phenomenon concerned by compressor aerodynamicists. Great amount of researches were conducted for clarifying the flow mechanisms and aerodynamic features in turbomachinery by experimental, theoretical, and numerical methods [4][5][6][7][8][9][10].…”

Section: Introductionmentioning

confidence: 99%

The evolution of the flow topologies of 3D separations in the stator passage of an axial compressor stage

Zhang

Liu

2013

Experimental Thermal and Fluid Science

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“…When examined in the same way as the surface flow visualization from the NRC cascade, two results from compressor blading (Schulz and Gallus 19 , and Weber at al.…”

Section: Figure 8 Measurements Of Wavelength and Comparison With Kesmentioning

confidence: 99%

Organized Streamwise Vorticity on Convex Surfaces With Particular Reference to Turbine Blades

Gostelow

Mahallati

Carscallen

et al. 2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Experiments were conducted on the flow through a transonic turbine cascade and at subsonic speeds past a circular cylinder in cross-flow. These followed extensive work on vortex shedding behind these bodies, displaying the phenomena of energy separation at subsonic speeds; the turbine blades also exhibited exotic vortex-shedding modes in transonic flow. Surface flow visualization was undertaken on the suction surface of the turbine blade and on the circular cylinder. This was effective in providing a time-average mapping of the vortical structures within the blade passage and around the cylinder. The usual phenomena of horseshoe vortices, secondary flows, passage vortices and wall and corner vortices were observed. In addition, and more surprisingly, organized systems of fine-scale streamwise vortices were observed for both cases. Under the influence of the strong favorable pressure gradients on the turbine blade suction surface, the vortices persisted to the trailing edge. For the circular cylinder work, undertaken at an inlet Mach number of 0.5, the streamwise vortices occupied the forward portion of the cylinder, almost to the 83 degree azimuth, and re-appeared after laminar separation. This streamwise vorticity had been predicted and observed previously for low speed flows, with attendant theories for wavelength. The present results have been compared with the predictions giving reasonable agreement.

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Experimental Investigation of the Three-Dimensional Flow in an Annular Compressor Cascade

Cited by 79 publications

References 0 publications

Transition Modelling for General Purpose CFD Codes

Transition Modelling for General Purpose CFD Codes

The evolution of the flow topologies of 3D separations in the stator passage of an axial compressor stage

Organized Streamwise Vorticity on Convex Surfaces With Particular Reference to Turbine Blades

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