The Transonic Flow Through a Plane Turbine Cascade as Measured in Four European Wind Tunnels

Kiock, R.; Lehthaus, F.; Baines, N. C.; Sieverding, C. H.

doi:10.1115/85-igt-44

Cited by 24 publications

(32 citation statements)

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“…At M2 . ; 0, 97 the three models are within the band of the different measurements taken from Kiock et al (1985). However the Lam-Bremhorst model shows the best agreement with the measurements at the trailing edge.…”

Section: Numerical Resultsmentioning

confidence: 59%

Viscous Flow Field Computations for the VKI–1 Turbine Cascade Using Different Turbulence Models

Lenke¹,

Reichert²,

Simon³

1995

Volume 1: Turbomachinery

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The influence of the turbulence modelling on viscous flow field calculation results has often been discussed in the past. For a meaningful comparison of different turbulence models the access to reliable measurement data is necessary. The plane VKI–1 turbine profile has been investigated experimentally in many publications. Therefore this turbine profile is chosen for transonic 2D flow field calculations using three different turbulence models. The algebraic model of Baldwin and Lomax, the Standard k–ϵ model with wall functions and a low–Reynolds number model are considered in this investigation. The main differences between the models become apparent in the trailing edge region. The turbulence modelling influences the boundary layer thickness and the shape of the shear layers and the separation region in the wake flow. For the high Mach numbers appearing in this region, a strong influence on the flow field due to small shear layer changes has been found.

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Section: Numerical Resultsmentioning

confidence: 59%

Viscous Flow Field Computations for the VKI–1 Turbine Cascade Using Different Turbulence Models

Lenke¹,

Reichert²,

Simon³

1995

Volume 1: Turbomachinery

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“…The finite volume approach is used in this code with the volume and area projections in the quadrilateral mesh calculations based on the inverse Jacobian and metric coefficients in body-fitted coordinate system. The computational results are presented for the now field in a transonic turbine cascade which has been experimentally investigated in four European wind tunnels (Kiock et al, 1986). The computed results are compared for two turbulence models and for two different H-type grids (traditional and nonperiodic).…”

Section: The Experimental Results Ofmentioning

confidence: 99%

“…Numerical solutions were obtained for the flow in the transonic turbine cascade for which the experimental results were obtained by Kiock et al (1986), at inlet turbulence level of 1%. The design parameters and flow conditions for this cascade are summarized in Tables (1) and (2).…”

Section: Resultsmentioning

confidence: 99%

Navier-Stokes Computations for Turbulent Flow Predictions in Transonic Turbine Cascade Using a Zonal Approach

1993

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Numerical results are presented for viscous flow through a transonic turbine cascade using different turbulence models and H-type grids. The explicit Navier-Stokes solver used in the solution was developed with an option of conservative zonal approach for interpolation across the periodic boundaries with minimum numerical errors. This approach allows the use of a grid that is more orthogonal and less skewed which leads to higher accuracy in the prediction of turbine blade performance. The results obtained with an algebraic and two equation turbulence models, and with two types of H grids are compared at two different flow conditions.

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“…The experiment was carried out in a linear cascade wind tunnel capable of supersonic inlet flow which is described in detail by Sanz et al (1998). The turbine cascade consists of 7 blades as described by Kiock et al (1986). The most important geometrical characteristics of the blade row and the main flow parameters are summarised in table 1.…”

Section: Experimental Facilitymentioning

confidence: 99%

Numerical and Experimental Investigation of Trailing Edge Vortex Shedding Downstream of a Linear Turbine Cascade

Gehrer

Lang

Mayrhofer

et al. 2000

Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery

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In this study, the evolution of the unsteady trailing edge vortex street downstream a linear turbine cascade is experimentally and computationally investigated. In a transonic cascade test stand, Laser Doppler velocimeter (LDV) measurements were acquired in several axial planes downstream of the blade trailing edge. In addition, direct detection of density changes near the trailing edge provide information about the frequency of a vortex shedding cycle. A two-dimensional upwind-biased Navier-Stokes solver has then been used to perform a series of steady and unsteady cascade simulations, allowing an in-depth study into the mechanisms of the trailing edge vortex shedding. The numerical results are compared with the experimental data to test the quality of the numerical simulations.

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The Transonic Flow Through a Plane Turbine Cascade as Measured in Four European Wind Tunnels

Cited by 24 publications

References 0 publications

Viscous Flow Field Computations for the VKI–1 Turbine Cascade Using Different Turbulence Models

Viscous Flow Field Computations for the VKI–1 Turbine Cascade Using Different Turbulence Models

Navier-Stokes Computations for Turbulent Flow Predictions in Transonic Turbine Cascade Using a Zonal Approach

Numerical and Experimental Investigation of Trailing Edge Vortex Shedding Downstream of a Linear Turbine Cascade

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