Boundary Layer Measurements on the Pressure and Suction Sides of a Turbine Inlet Guide Vane

Bario, F.; Beral, C.

doi:10.1016/b978-0-444-82463-9.50079-4

Cited by 3 publications

(2 citation statements)

References 9 publications

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“…As the birth of turbulence, the precise prediction of transition is critical for accurate loss predictions of turbomachinery. However, the transition process is complicated when taking pressure gradients, Reynolds number, curvature and nonstationarity into account (Bario and Beral, 1998). In past years, abundant research results were obtained on the flat plate (Roberts and Yaras, 2006; Lardeau et al , 2012; Keller and Wang, 1994), whereas few on the blade (Zaki et al , 2006) because complicated shape requires high-fidelity simulation method.…”

Section: Introductionmentioning

confidence: 99%

Accelerating unstructured large eddy simulation solver with GPU

Liu

Chen

Yuan

2018

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Purpose Adopting large eddy simulation (LES) to simulate the complex flow in turbomachinery is appropriate to overcome the limitation of current Reynolds-Averaged Navier–Stokes modelling and it provides a deeper understanding of the complicated transitional and turbulent flow mechanism; however, the large computational cost limits its application in high Reynolds number flow. This study aims to develop a three-dimensional GPU-enabled parallel-unstructured solver to speed up the high-fidelity LES simulation. Design/methodology/approach Compared to the central processing units (CPUs), graphics processing units (GPUs) can provide higher computational speed. This work aims to develop a three-dimensional GPU-enabled parallel-unstructured solver to speed up the high-fidelity LES simulation. A set of low-dissipation schemes designed for unstructured mesh is implemented with compute unified device architecture programming model. Several key parameters affecting the performance of the GPU code are discussed and further speed-up can be obtained by analysing the underlying finite volume-based numerical scheme. Findings The results show that an acceleration ratio of approximately 84 (on a single GPU) for double precision algorithm can be achieved with this unstructured GPU code. The transitional flow inside a compressor is simulated and the computational efficiency has been improved greatly. The transition process is discussed and the role of K-H instability playing in the transition mechanism is verified. Practical/implications The speed-up gained from GPU-enabled solver reaches 84 compared to original code running on CPU and the vast speed-up enables the fast-turnaround high-fidelity LES simulation. Originality/value The GPU-enabled flow solver is implemented and optimized according to the feature of finite volume scheme. The solving time is reduced remarkably and the detail structures including vortices are captured.

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Section: Introductionmentioning

confidence: 99%

Accelerating unstructured large eddy simulation solver with GPU

Liu

Chen

Yuan

2018

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“…In studies of turbine flows, there have been numerous experimental and numerical measurements used to investigate the flow field through turbine blade cascades to find the optimum design conditions which involve a large number of shape parameters and the operating conditions governed by high level of turbulence. Bario and Beral (1998) conducted experimental measurements for the evolution of the boundary layer on the pressure and suction sides of a turbine inlet guide vane for different upstream turbulent conditions. Arts et al (1990) conducted experimental measurements for an aero‐thermal investigation of a highly loaded transonic linear turbine guide vane cascade at design conditions.…”

Section: Introductionmentioning

confidence: 99%

Computational modelling of inflow turbulence effects on transitional flow in a highly transonic linear turbine

Tutar

Sönmez²

2012

International Journal of Numerical Methods for Heat &Amp; Fluid Flow

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PurposeThe purpose of this paper is to numerically study inflow turbulence effects on the transitional flow in a high pressure linear transonic turbine at the design incidence.Design/methodology/approachThe three‐dimensional (3‐D) compressible turbulent flow in a turbine inlet guide vane is simulated using a finite volume based fluid solver coupled with dynamic large eddy simulation (LES) computations to investigate the effects of varying inflow turbulence length scale and the turbulence intensity on the aero‐thermal flow characteristics and the laminar‐turbulent transition phenomena. The computational analyses are extended to very high exit Reynolds number flow conditions to further study the effect of high exit Reynolds numbers on the transitional behavior of the present flow around the inlet guide vane cascades of the turbine. The calculations are performed with varying degree of inflow turbulence intensity values ranging from 0.8 to 6 percent and the inflow turbulence length scales ranging from one to five percent of pitch for different exit isentropic Mach and Reynolds numbers.FindingsThe numerical predictions in comparison with the experimental data demonstrate that the level of inflow turbulence closure provided by the present LES computations offers a reliable framework to predict complex turbulent flow and transition phenomena in high free‐stream turbulence environments of high pressure linear turbines.Originality/valueThis is the first instance in which both artificially modified random flow generation method in association with the dynamic procedure of LES application is employed to represent the realistic inflow turbulence conditions in the high pressure turbine and to resolve the transitional flow in a dynamic approach.

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Experimental Investigation of Film Cooling Flow Induced by Shaped Holes on a Turbine Blade

Barthet¹,

Bario²

2001

Annals of the New York Academy of Sciences

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The present study is the second half of a piece of work carried out in collaboration with SNECMA. It investigates shaped hole film cooling, numerically and experimentally. The aim of this paper is the experimental analysis of shaped hole film cooling on a large scale turbine blade (1.4 m chord). The test section is a large scale turbine inlet guide vane cascade. The test airfoil is equipped with a row of nine 50° sloped shaped holes. They are located on the suction side at 20% of the curvilinear length of the blade from the stagnation point. The inlet film cooling hole diameter is 12 mm. The test jet flow is heated to 55°C above the crossflow temperature. Velocity and temperature field measurements have been done to obtain mean and fluctuating values. The results are compared to those obtained by Béral1 on the same experimental apparatus and in the same test conditions, for a row of cylindrical holes.

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Boundary Layer Measurements on the Pressure and Suction Sides of a Turbine Inlet Guide Vane

Cited by 3 publications

References 9 publications

Accelerating unstructured large eddy simulation solver with GPU

Accelerating unstructured large eddy simulation solver with GPU

Computational modelling of inflow turbulence effects on transitional flow in a highly transonic linear turbine

Experimental Investigation of Film Cooling Flow Induced by Shaped Holes on a Turbine Blade

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