Computation of Turbomachinery Flows with a Parallel Unstructured Mesh Navier-Stokes equations Solver on GPUs

Gisbert, Fernando; Corral, Roque; Pueblas, Jesús

doi:10.2514/6.2013-2864

Cited by 6 publications

(2 citation statements)

References 11 publications

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“…The steady fluid problem is solved with ITP's in-house CFD code Mu²s²t [14], a solver for the fully non-linear RANS equations which counts with a linearised version that allows us to solve the unsteady vibration problem with a pseudo time-marching scheme. The solver, capable of running in GPUs [15], has been well validated over time and is routinely employed at ITP to support its aerodynamic designs and perform either aeroelastic or aeroacoustic simulations. In the work presented here, a two-equations k-w turbulence model has been chosen, with frozen turbulence variables in the unsteady simulation.…”

Section: Methodsmentioning

confidence: 99%

Numerical and Experimental Study of Flutter in a Realistic Labyrinth Seal

Bermejo,

Gallardo,

Sotillo

et al. 2024

IJTPP

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Labyrinth seals are commonly used in turbomachinery in order to control leakage flows. Flutter is one of the most dangerous potential issues for them, leading to High Cycle Fatigue (HCF) life considerations or even mechanical failure. This phenomenon depends on the interaction between aerodynamics and structural dynamics; mainly due to the very high uncertainties regarding the details of the fluid flow through the component, it is very hard to predict accurately. In 2014, as part of the E-Break research project funded by the European Union (EU), an experimental campaign regarding the flutter behaviour of labyrinth seals was conducted at “Centro de Tecnologias Aeronauticas” (CTA). During this campaign, three realistic seals were tested at different rotational speeds, and the pressure ratio where the flutter onset appeared was determined. The test was reproduced using a linearised uncoupled structural-fluid methodology of analysis based on Computational Fluid Dynamics (CFD) simulations, with results only in moderate agreement with experimental data. A procedure to adjust the CFD simulations to the steady flow measurements was developed. Once this method was applied, the matching between flutter predictions and the measured data improved, but some discrepancies could still be found. Finally, a set of simulations to retain the influence of the external cavities was run, which further improved the agreement with the testing data.

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Section: Methodsmentioning

confidence: 99%

Numerical and Experimental Study of Flutter in a Realistic Labyrinth Seal

Bermejo,

Gallardo,

Sotillo

et al. 2024

IJTPP

View full text Add to dashboard Cite

show abstract

“…The steady fluid problem is solved with ITP's CFD code Mu²s²t [13], a solver for the fully non-linear RANS equations which counts with a linearized version that allows to solve the unsteady vibration problem with a pseudo time marching scheme. The solver, capable of running in GPUs [14], has been well validated over time and is routinely employed at ITP to support its aerodynamic designs and perform either aeroelastic or aeroacoustics simulations. In the work presented here, a two equations k-w turbulence model has been chosen, with frozen turbulence variables in the unsteady simulation.…”

Section: Methodsmentioning

confidence: 99%

Numerical and Experimental Study of Flutter in a Realistic Labyrinth Seal

Bermejo,

Gallardo,

Sotillo

et al. 2023

Preprint

View full text Add to dashboard Cite

Labyrinth seals are commonly used in turbomachinery in order to control leakage flows. Flutter is one of the most dangerous potential issues for them, leading to High Cycle Fatigue (HCF) life considerations or even mechanical failure. This phenomenon depends on the interaction between aerodynamics and structural dynamics; mainly due to the very high uncertainties regarding the details of the fluid flow through the component, it is very hard to predict accurately. In 2014, as part of the E-Break research project funded by the European Union (EU), an experimental campaign regarding the flutter behaviour of labyrinth seals was conducted at Centro de Tecnologias Aeronauticas (CTA). During this campaign, three realistic seals were tested at different rotational speeds, and the pressure ratio where the flutter onset appeared was determined. The test was reproduced using a linearized uncoupled structural-fluid methodology of analysis based on Computational Fluid Dynamics (CFD) simulations, with results only in moderate agreement with experimental data. A procedure to adjust the CFD simulations to the steady flow measurements was developed. Once this method was applied, the matching between flutter predictions and the measured data improved, but still some discrepancies could be found. Finally, a set of simulations to retain the influence of the external cavities was run, what further improved the agreement with testing data.

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Space–Time Gradient Method for Unsteady Bladerow Interaction—Part I: Basic Methodology and Verification

2015

Journal of Turbomachinery

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For advanced turbomachinery development, there is increasing interest to carry out unsteady analyses for flows through multiple bladerows during a design stage. Even with the huge increase in computer processing power currently available, direct unsteady calculations in a whole annulus domain are still very time consuming. Efficient alternative methods with truncations in time and/or in space have been developed for unsteady turbomachinery flows in the past 20 years or so, but they all are associated with related limitations. The present development is motivated to maintain as many modeling fidelities of direct unsteady solution methods as possible while still have a significant speed-up. To this end, a new steady-solution-like unsteady time-domain methodology has been developed for bladerow interactions. No circumferential domain truncation is required so that a direct periodic (repeating) condition can be applied. For each mesh cell, the temporal gradient term as required to balance the discretized unsteady flow equation is obtained by specially sequenced spatial variations of corresponding cells in multiple-passages. Consequently, the rotor–stator interface treatment becomes completely compatible to that of a direct unsteady solution. Thus a fully conservative interface is easily achieved, in contrast to existing truncated models where interface treatments tend to be complicated and nonconservative. The simultaneous solution procedure with the space–time gradient (STG) link enables an unsteady flow solution to converge at a rate compatible to a steady solution. The background, motivation/justification, basic methodology, and some preliminary verifications are described in this paper as Part I. Further validations and applications with extension to more complex configurations and flow conditions will be presented in Part II.

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Computation of Turbomachinery Flows with a Parallel Unstructured Mesh Navier-Stokes equations Solver on GPUs

Cited by 6 publications

References 11 publications

Numerical and Experimental Study of Flutter in a Realistic Labyrinth Seal

Numerical and Experimental Study of Flutter in a Realistic Labyrinth Seal

Numerical and Experimental Study of Flutter in a Realistic Labyrinth Seal

Space–Time Gradient Method for Unsteady Bladerow Interaction—Part I: Basic Methodology and Verification

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