Viscous Analysis of Three-Dimensional Rotor Flow Using a Multigrid Method

Arnone, Andrea

doi:10.1115/93-gt-019

Cited by 55 publications

(76 citation statements)

References 21 publications

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“…The TRAF3D solver [3] with an extension to calculate impellers with splitters is used to predict the aerodynamic performance of the radial impellers. Structured H-grids with 2 × 216 × 48 × 52 (1,090,000 cells) are used for all computations to guarantee a comparable accuracy for all the samples stored in the database.…”

Section: Design Conditions and Resultsmentioning

confidence: 99%

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Numerical Optimization for Advanced Turbomachinery Design

Braembussche

2008

Optimization and Computational Fluid Dynamics

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The multilevel-multidisciplinary-multipoint optimization system developed at the von Kármán Institute and its applications to turbomachinery design is presented. To speed up the convergence to the optimum geometry, the method combines an Artificial Neural Network, a Design Of Experiment technique and a Genetic Algorithm. The different components are described, the main requirements are outlined and the basic method is illustrated by the design of an axial turbine blade.A procedure for multipoint optimization, aiming for optimal performance at more than one operating point, is outlined and applied to the optimization of a low solidity diffuser.The extension to a multidisciplinary optimization, by combining a Navier-Stokes solver with a Finite Element Analysis, allows an efficient search for a compromise between the sometimes conflicting demands of high efficiency and respect of mechanical constraints. It is shown that a significant reduction of the stresses is possible with only a small penalty on the performance and that this approach may lead to geometries that would normally be excluded when using less sophisticated methods.

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Section: Design Conditions and Resultsmentioning

confidence: 99%

“…The TRAF3D NS solver [3] is used to predict the aerodynamic performance. Similar grids with the same number of cells are used for all computations to guarantee a comparable accuracy for all the predictions.…”

Section: Two-level Optimizationmentioning

confidence: 99%

Numerical Optimization for Advanced Turbomachinery Design

Braembussche

2008

Optimization and Computational Fluid Dynamics

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“…resulting in a centred O( x 2 H ) scheme for the viscous terms (the derivatives involved in the evaluation of [ 1F V MF ] i, j,k are computed using an O( x 2 H ) scheme [73]). To uncouple the timelinearized time-harmonic mean-flow equations (Equation (5)) from the equations for the unsteady perturbations of the Reynolds-stresses (and thus reduce the number of equations from 12 to only 5), the unsteady perturbations of the Reynolds-stresses and of the turbulent-heat-flux must be modelled using only steady quantities and mean-flow-perturbations.…”

Section: Linearization and Approximation Of The Viscous Fluxes And Ofmentioning

confidence: 99%

Time‐linearized time‐harmonic 3‐D Navier–Stokes shock‐capturing schemes

Chassaing

Gerolymos

2007

Numerical Methods in Fluids

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SUMMARYIn the present paper, a numerical method for the computation of time-harmonic flows, using the timelinearized compressible Reynolds-averaged Navier-Stokes equations is developed and validated. The method is based on the linearization of the discretized nonlinear equations. The convective fluxes are discretized using an O( x 3 H ) MUSCL scheme with van Leer flux-vector-splitting. Unsteady perturbations of the turbulent stresses are linearized using a frozen-turbulence-Reynolds-number hypothesis, to approximate eddy-viscosity perturbations. The resulting linear system is solved using a pseudo-time-marching implicit ADI-AF (alternating-directions-implicit approximate-factorization) procedure with local pseudo-time-steps, corresponding to a matrix-successive-underrelaxation procedure. The stability issues associated with the pseudo-time-marching solution of the time-linearized Navier-Stokes equations are discussed. Comparison of computations with measurements and with time-nonlinear computations for 3-D shock-wave oscillation in a square duct, for various back-pressure fluctuation frequencies (180,80, 20 and 10 Hz), assesses the shock-capturing capability of the time-linearized scheme.

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“…Many computational methods have been developed to avoid detailed computation of the tip-clearance gap, either using simplified models for computing the leakage massflow (Denton (1993), Adamczyk et al (1993), Arnone (1994)) or modifying the blade-tip geometry to a sharp edge, and thus joining together the grid points on either side of the blade (e.g., Hah (1992), Jennions and Turer (1993)). Many computational methods have been developed to avoid detailed computation of the tip-clearance gap, either using simplified models for computing the leakage massflow (Denton (1993), Adamczyk et al (1993), Arnone (1994)) or modifying the blade-tip geometry to a sharp edge, and thus joining together the grid points on either side of the blade (e.g., Hah (1992), Jennions and Turer (1993)).…”

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confidence: 99%

Effects of Shock-Wave on Flow Structure in Tip Region of Transonic Compressor Rotor

Park¹,

Chung²,

Baek³

2003

International Journal of Turbo and Jet Engines

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It is known that tip clearance flows reduce the pressure rise, flow range and efficiency of turbomachinery. So, a clear understanding about flow fields in the tip region is needed to efficiently design the turbomachinery. In the present paper, the Navier-Stokes code with the proper treatment of the boundary conditions has been developed to analyze the threedimensional steady viscous flow fields in the transonic rotating blades and a numerical study has been conducted to investigate the detailed flow physics in the tip region of transonic rotor, NASA Rotor 67. The computational results in the tip region of transonic rotor show the leakage vortices, leakage flow from pressure side to suction side and their interaction with a shock. Depending on the operating conditions, load distributions and the position of shock-wave on the blade surface are very different close to the blade tip of transonic compressor rotor. It is shown that the load distribution and the shock-wave position close to blade tip have great effects on the starting position of leakage vortex and direction of leakage flow. peak efficiency Experiment Calculation choke J I L j L j Ι-Ο.92 0.94 0.96 0.98 Mass flow rate/Mass flow rate at choke 1 ιnear stall Experiment Calculation J I L. J ' ' J_ J I L 0.92 0.94 0.96 0.98

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Viscous Analysis of Three-Dimensional Rotor Flow Using a Multigrid Method

Cited by 55 publications

References 21 publications

Numerical Optimization for Advanced Turbomachinery Design

Numerical Optimization for Advanced Turbomachinery Design

Time‐linearized time‐harmonic 3‐D Navier–Stokes shock‐capturing schemes

Effects of Shock-Wave on Flow Structure in Tip Region of Transonic Compressor Rotor

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