Explicit Navier-Stokes computation of cascade flows using the k-epsilon turbulence model

Kunz, Robert F.; Lakshminarayana, B.

doi:10.2514/3.10876

Cited by 35 publications

(19 citation statements)

References 9 publications

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“…Birmingham, United Kingdom, June 1(3- 13,1996 The flow through the tip clearance region of a transonic compressor rotor (NASA rotor 37) was computed and compared to aerodynamic probe and laser anemometer data. Tip clearance effects were modeled both by gridding the clearance gap and by using a simple periodicity model across the ungridded gap.…”

Section: Prepared For the 41st Gas Turbine And Aeroenginc Congress Spmentioning

confidence: 99%

Calculation of Tip Clearance Effects in a Transonic Compressor Rotor

Chima

1996

Volume 1: Turbomachinery

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The flow through the tip clearance region of a transonic compressor rotor (NASA rotor 37) was computed and compared to aerodynamic probe and laser anemometer data. Tip clearance effects were modeled both by gridding the clearance gap and by using a simple periodicity model across the ungridded gap. The simple model was run with both the full gap height, and with half the gap height to simulate a vena-contracta effect. Comparisons between computed and measured performance maps and downstream profiles were used to validate the models and to assess the effects of gap height on the simple clearance model. Recommendations were made concerning the use of the simple clearance model. Detailed comparisons were made between the gridded clearance gap solution and the laser anemometer data near the tip at two operating points. The computed results agreed fairly well with the data but overpredicted the extent of the casing separation and underpredieted the wake decay rate. The computations were then used to describe the interaction of the tip vortex, the passage shock, and the casing boundary layer.

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Section: Prepared For the 41st Gas Turbine And Aeroenginc Congress Spmentioning

confidence: 99%

Calculation of Tip Clearance Effects in a Transonic Compressor Rotor

Chima

1996

Volume 1: Turbomachinery

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“…The k-m turbulence model of Launder and Spalding [17] is chosen because of its capability to describe accurately and efficiently a variety of flows [23,25]. The momentum equations for k and m can be written …”

Section: Turbulence Equations K-m and The Law Of The Wallmentioning

confidence: 99%

“…The time integration is obtained by a multistage (fourth-order) Runge-Kutta scheme [24,25], and, for faster convergence to the steady state solution, a mesh-sequencing scheme is used.…”

Section: Introductionmentioning

confidence: 99%

A characteristic based method for the calculation of three-dimensional incompressible, turbulent and steady flows in hydraulic turbomachines and installations

Govatsos

Papantonis

2000

Int. J. Numer. Meth. Fluids

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The present algorithm is developed to calculate three‐dimensional incompressible, turbulent and steady flows in hydraulic turbomachines and installations. The code is based on a characteristic based method for the solution of the incompressible Navier–Stokes equations, coupling the continuity and momentum equations after the introduction of the artificial compressibility formulation. The primitive variables, pressure and velocity components are defined as functions of their values on the characteristics. The primitive variables on the characteristics are calculated by an upwind differencing scheme based on the sign of the local eigenvalue of the Jacobian matrix of the convective fluxes. The upwind scheme uses interpolation formulas of third‐order accuracy. The standard k–ε model is applied for the description of turbulence effects. The time discretization is obtained by the explicit Runge–Kutta method. For faster convergences to the steady state solution, a local time stepping and a mesh‐sequencing scheme are used. Validation of the algorithm is performed on many two‐ and three‐dimensional laminar and turbulent flow cases, while in the present work, the three‐dimensional flow (laminar and turbulent) through a square duct with a 90° bend is presented. Finally, the code is applied for the prediction of the relative flow through the impeller of the Societe Hydrotechnique de France (SHF) water pump. The numerical results are compared with the corresponding experimental measurements. Copyright © 2000 John Wiley & Sons, Ltd.

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“…Eigenvalue scaling [23] was used to scale the artificial dissipation directionally on the highly stretched grids.…”

Section: Swift Codementioning

confidence: 99%

Calculation of multistage turbomachinery using steady characteristic boundary conditions

Chima

1998

36th AIAA Aerospace Sciences Meeting and Exhibit

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Explicit Navier-Stokes computation of cascade flows using the k-epsilon turbulence model

Cited by 35 publications

References 9 publications

Calculation of Tip Clearance Effects in a Transonic Compressor Rotor

Calculation of Tip Clearance Effects in a Transonic Compressor Rotor

A characteristic based method for the calculation of three-dimensional incompressible, turbulent and steady flows in hydraulic turbomachines and installations

Calculation of multistage turbomachinery using steady characteristic boundary conditions

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