Study of Secondary Flows in Blade Cascades of Turbomachines

Bario, F.; Leboeuf, Francis; Papailiou, K. D.

doi:10.1115/1.3227305

Cited by 11 publications

(6 citation statements)

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“…Sharma and Bulter (1987) and Yamamoto (1987) proposed some numerical schemes to predict endwall losses and secondary flows in turbine cascades. Detailed experimental investigations of the production and development of the secondary flows were presented in studies by Yamamoto (1987) and Bario et al (1982). Sonoda (1985) used kerosene vapor to visualize the flow field in the blade passages.…”

Section: Introductionmentioning

confidence: 99%

Convective Transport Phenomena on the Suction Surface of a Turbine Blade Including the Influence of Secondary Flows Near the Endwall

Chen

Goldstein

1991

Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration

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A naphthalene sublimation technique is employed to study the mass transfer distribution on the suction (convex) surface of a simulated turbine blade. Comparison with a heat transfer study shows good agreement in the general trends in the region of two-dimensional flow on the blade. Near the endwall, local convective coefficients on the suction surface are obtained at 4608 locations from two separate runs. The secondary flows in the passage significantly affect the mass transfer rate on the suction surface and their influence extends to a height of 75% of the chord length, from the endwall, in the trailing edge region. The mass transfer rate in the region near the endwall is extremely high due to small but intense vortices. Thus, a large variation in the mass transfer distribution occurs on the suction surface, from a mass transfer Stanton number of 0.0005 to a maximum of 0.01. In the two-dimensional flow region, the mass transfer distributions at two different Reynolds number are presented.

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Section: Introductionmentioning

confidence: 99%

Convective Transport Phenomena on the Suction Surface of a Turbine Blade Including the Influence of Secondary Flows Near the Endwall

Chen

Goldstein

1991

Volume 4: Heat Transfer; Electric Power; Industrial and Cogeneration

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“…SECONDARY FLOW DEVELOPMENT IN A LINEAR CASCADE OF COMPRESSOR BLADESExtensive tests were carried out on a linear cascade of DCA-type highly loaded compressor blades at the Ecole Centrale de Lyons[10]. The main parameters are…”

mentioning

confidence: 99%

Development of a 3D Navier Stokes Solver for Application to all Types of Turbomachinery

Dawes

1988

Volume 1: Turbomachinery

133

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This paper describes the current stage of development of a code aimed at solving the 3D Navier-Stokes equations in any type of turbomachinery geometry. The basic algorithm time marches the fully 3D unsteady equations of motion expressed in finite volume form with a two step explicit / one step implicit method. Full multigrid acceleration is used to reduce solution time and maintain code performance on fine meshes. Turbulence modelling is via mixing-length closure and the widely used Baldwin-Lomax model. The generality and robustness of the code is demonstrated by application to five different test cases, three axial and two radial configurations. Also included is a grid independence study which demonstrates near grid independent solutions for transonic compressor cascade flow (albeit with the actual result subject to transition modelling constraints). For two of the axial cases (transonic compressor in cascade, secondary flow in a high speed compressor) and one radial case (Eckardt high speed impellor) sufficient mesh is employed for the predictions to be essentially quantitative. The other two cases (radial inflow turbine with clearance and compressor stator with hub clearance) are really simulations rather than predictions, but are included as the flows are novel and provide much physical insight.

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“…The final mesh, Figure 18, contains 30521 nodes and 162303 cells and was arrived at by flagging every face with a fractional variation of entropy of more than 10% and every face with a mean Mach number in the the range 0. to 0.20. The final solution is shown in Figures 19 and 20 together with the measured loss distributions published by Bario et al (1982). The corner stall and resulting wake and secondary flow are much stronger and more extensive than in the case without inlet boundary layer profile.…”

Section: (I) Without Inlet Endwall Boundary Layer Profilementioning

confidence: 92%

“…Extensive tests were carried out on a linear cascade of DCAtype highly loaded compressor blades at the Ecole Centrale de Lyons (Bario et al (1982)). The main parameters were: pitch/chord ratio Two set of calculations were carried out, without and with the inlet endwall boundary layer profile.…”

Section: Secondary Now In a Transonic Compressor Cascadementioning

confidence: 99%

The Simulation of Three-Dimensional Viscous Flow in Turbomachinery Geometries Using a Solution-Adaptive Unstructured Mesh Methodology

Dawes

1991

Volume 1: Turbomachinery

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This paper presents a numerical method for the simulation of flow in turbomachinery blade rows using a solution-adaptive mesh methodolgy. The fully three dimensional, compressible, Reynolds averaged Navier-Stokes equations with k-ε turbulence modelling (and low Reynolds number damping terms) are solved on an unstructured mesh formed from tetrahedral finite volumes. At stages in the solution, mesh refinement is carried out based on flagging cell faces with either a fractional variation of a chosen variable (like Mach number) greater than a given threshold or with a mean value of the chosen variable within a given range. Several solutions are presented, including that for the highly three-dimensional flow associated with the corner stall and secondary flow in a transonic compressor cascade, to demonstrate the potential of the new method.

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Study of Secondary Flows in Blade Cascades of Turbomachines

Cited by 11 publications

References 0 publications

Convective Transport Phenomena on the Suction Surface of a Turbine Blade Including the Influence of Secondary Flows Near the Endwall

Convective Transport Phenomena on the Suction Surface of a Turbine Blade Including the Influence of Secondary Flows Near the Endwall

Development of a 3D Navier Stokes Solver for Application to all Types of Turbomachinery

The Simulation of Three-Dimensional Viscous Flow in Turbomachinery Geometries Using a Solution-Adaptive Unstructured Mesh Methodology

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