Parallel Multigrid Unstructured Method for the Solution of the Navier-Stokes Equations

Corral, Roque; Crespo, Javier Lluch; Gisbert, Fernando

doi:10.2514/6.2004-761

Cited by 25 publications

(12 citation statements)

References 12 publications

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“…Steady RANS, Unsteady RANS (RANS) in time domain, Linearized RANS (LRANS) in frequency domain are the Mu 2 s 2 T capabilities of interest for Aeroacoustics computations. Other characteristics of interest are: Time-marching technique with an explicit five-stage Runge-Kutta, Multigrid [11] to accelerate convergence, Message Passing Interface (MPI) and able to run in Graphic Processing Units (GPUs) [10]. Mu 2 s 2 T is currently used for the design of ITP Aero products.…”

Section: Codes and Methodologymentioning

confidence: 99%

Turbine Tone Noise Prediction in High Speed Turbines Using a Linearized CFD Solver: Comparison with Measurements

Aparicio

Serrano

2021

Aiaa Aviation 2021 Forum

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Section: Codes and Methodologymentioning

confidence: 99%

Turbine Tone Noise Prediction in High Speed Turbines Using a Linearized CFD Solver: Comparison with Measurements

Aparicio

Serrano

2021

Aiaa Aviation 2021 Forum

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“…In the linear solver structural displacements are interpolated and imposed on the aerodynamic mesh to determine the work per cycle and the aerodynamic damping. Effectiveness and robustness of the used solver can be found in [16][17][18], where the extended code is explained and the validation of the simulations are proven by comparing the computational results with the experimental ones.…”

Section: Fem and Cfd Simulationsmentioning

confidence: 99%

Design Space Exploration of Turbine Blade Shroud Interlock for Flutter Stability

Larrieta

Alonso

Escobar³

et al. 2020

Volume 10A: Structures and Dynamics

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The geared turbofan engines bring the potential to rotate the fan at lower speed and allow an increase in diameter, which in turn leads to an increase in propulsive efficiency through high by-pass ratio. The low-pressure turbine stages driving the fan can also rotate at high speed resulting in fewer stages when compared to traditional turbofans. However, when operating at high speed, pressure fluctuations due to self-excited vibrations increase and may provoke flutter instabilities. In a geared architecture, to deliver the high power required by the fan and the intermediate-pressure compressor, the low-pressure turbine system operates at higher temperatures compared to its predecessors. This phenomenon requires structural materials with higher heat resistance, which carries the inconvenience of poor welding suitability. That is the reason why alternative non-welded blade shroud joint techniques are so important, techniques as the blade interlock mechanism studied in this work. This manuscript examines the effects of different design parameters of a low-pressure turbine blade shroud interlock on flutter stability, to make future recommendations for geared engines. The shrouded turbine rotor blades feature blade interlocks, which enhances the dynamic stability by providing stiffness to the rotor blade row. To assess the stability of the system, a parametric design of a turbine blade-disk assembly was prepared. In the parametric model the design variables that define the blade interlock are the interlock angle, interlock axial position, interlock contact length and height, knife seal position and pre-twist angle. After parametrization, a finite element model of the turbine blade and disk assembly was prepared with cyclic symmetry boundary condition. The stresses caused by rotation were calculated in a static structural analysis and these were used as pre-stress boundary conditions in modal analysis. The modal results were afterwards exchanged with an aerodynamic model to obtain the aerodynamic damping for different blade interlock design configurations. In the present work, the dynamic response of the first three excitation modes was analyzed. It was found that the third mode was stable for all the design points, whereas first and second modes were unstable at least for the reference design point. Among the considered six different parameters that define the blade interlock geometry, the interlock contact position turned to be the most influential parameter for modal response and for flutter stability. Moving the interlock contact position towards the trailing edge gave the most beneficial results. On the other hand, the interlock angle showed the least influence on both, the modal analysis and flutter behavior. The accomplished Design of Experiments and subsequent optimization process also conclude that there exists an interdependency between the studied parameters.

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“…A FAS multigrid capability has been developed in conjunction with the baseline fully parallel Reynolds averaged Navier-Stokes solution algorithm, capable of efficiently simulating flows with mixed high speed (Mach number > 1) and low speed (Mach number < 0.01) flow regimes. The parallelization of multigrid on unstructured topologies is nontrivial and has only been accomplished by a small number of practitioners [29,30,31,32] . The overall purpose of this research is to enable the baseline parallel unstructured code with multigrid technology that may be applied to any set of governing equations that the host code supports.…”

Section: Fas Multigrid Capabilitymentioning

confidence: 99%

Atmospheric Dispersion at Spatial Resolutions Below Mesoscale for university of Tennessee SimCenter at Chattanooga: Final Report

Whitfield¹,

Hyams²

2009

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Parallel Multigrid Unstructured Method for the Solution of the Navier-Stokes Equations

Cited by 25 publications

References 12 publications

Turbine Tone Noise Prediction in High Speed Turbines Using a Linearized CFD Solver: Comparison with Measurements

Turbine Tone Noise Prediction in High Speed Turbines Using a Linearized CFD Solver: Comparison with Measurements

Design Space Exploration of Turbine Blade Shroud Interlock for Flutter Stability

Atmospheric Dispersion at Spatial Resolutions Below Mesoscale for university of Tennessee SimCenter at Chattanooga: Final Report

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