Parameter study on numerical simulation of corner separation in LMFA-NACA65 linear compressor cascade

Gao, Feng; Ma, Wei; Sun, Jie; Boudet, Jérôme; Ottavy, Xavier; Liu, Yangwei; Lu, Lipeng; Shao, Lei

doi:10.1016/j.cja.2016.09.015

Cited by 17 publications

(12 citation statements)

References 49 publications

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“…However, as shown in Figure 4 (c) ~ (d), for the separation area, the SAS-SST numerical simulation results deviate from the experimental results. Although there is a deviation from the experimental results, the SAS-SST is a compromise scheme: The more accurate method, LES, is more expensive [13] ; The less costly URANS method cannot distinguish the vortex structures of corner separation well and deviate from the experimental results significantly [11] . [7] .…”

Section: Verification Of Numerical Simulationmentioning

confidence: 99%

Numerical investigation on corner separation control in a linear compressor cascade by synthetic jet

Liu¹,

Wang²,

Huang³

et al. 2020

Proceedings of Global Power &Amp; Propulsion Society

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Corner separation is a kind of three-dimensional separation which occurs commonly in the junction of the endwall and blade corner region of high-loaded compressor. The increases of flow losses and the blockage associated with the corner separation have negative effect on the efficiency and stability of compressor. In this paper the flow control of corner separation by a synthetic jet is numerically investigated with the Reynolds Averaged Navier-Stokes/Large Eddy Simulation (RANS/LES) hybrid method to improve the cascade performance under the design condition. The synthetic jet is mounted on the blade suction side of a subsonic linear compressor cascade using NACA65 blade profiles. The influence of the synthetic jet on the vortex structures and unsteady characteristics in the cascade is investigated. The results indicate that, with the presence of synthetic jet, the passage vortex is weakened, and the corner vortex is receded indirectly. The intensity and range of the concentrated shedding vortex of the suction surface boundary layer are reduced. The total pressure loss coefficient is decreased by 25.8% at the design operating condition. Through calculating the entropy generation rate in the cascade, it is found that the blade profile loss is responsible for the additional flow losses. The synthetic jet significantly reduces the irreversible losses in the blade passage and wake region. From the perspective of the bimodal distributions of corner separation, the parameters increase first and then decrease, and the bimodal points appear in the abrupt velocity zone rather than at the separation points only.

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Section: Verification Of Numerical Simulationmentioning

confidence: 99%

Numerical investigation on corner separation control in a linear compressor cascade by synthetic jet

Liu¹,

Wang²,

Huang³

et al. 2020

Proceedings of Global Power &Amp; Propulsion Society

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“…The corner separation case has been numerically studied by Gao [19] (see also [11,20,27]). The LES simulation (in ref [19]) is used as a reference database for the present work.…”

Section: Test-case and Solvermentioning

confidence: 99%

Turbulence modelling analysis in a corner separation flow

et al. 2020

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This paper studies RANS turbulence modelling for a linear compressor cascade corner separation flow, using large-eddy simulation results as reference. The Boussinesq and the quadratic constitutive relations are investigated with two versions of Wilcox's k − ω turbulence model through a priori and a posteriori analyses. In the a priori analysis the quadratic constitutive relation shows improvement on the alignment between the rate-of-strain tensor and the Reynolds stress tensor for the inlet region, compared to the Boussinesq constitutive relation. But the improvement is less significant in the highly vortical region. Using the turbulent kinetic energy and the specific dissipation rate provides a fairly good estimate of the turbulent viscosity. The turbulent kinetic energy budget is also investigated. Large-eddy simulation results present non-equilibrium turbulence, i.e. the production and dissipation are not balanced, whereas the RANS models predicts equilibrium turbulence.

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“…A Reynolds stress budget can be extracted, following the method of Gao [20]. The turbulent kinetic energy budget (referred to as TKE budget) is then deduced from the Reynolds stress budget diagonal terms addition (k = 1 2 u i u i ).…”

Section: Large-eddy Simulationmentioning

confidence: 99%

“…Reynolds-averaged Navier-Stokes (RANS) simulations are commonly used by industries. In the case of corner separation, RANS simulations tend to over-predict its size and intensity [7,8,9]. Bordji et al [10] found that using a nonBoussinesq constitutive relation (the quadratic constitutive relation, referred to as QCR [11]) yields better results for external flows.…”

Section: Introductionmentioning

confidence: 99%

Budget Analysis of Turbulent Kinetic Energy in Corner Separation : Rans vs Les

Monier¹,

Gao²,

Boudet³

et al. 2016

Proceedings of the VII European Congress on Computational Methods in Applied Sciences and Engineering (ECCOMAS Congress 2016)

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Abstract. The aim of the study is to compare the LES of corner separation, considered as a reference, in the LMFA-NACA65 linear compressor cascade to RANS simulations using Wilcox two-equation models (k − ω). The LES was carried-out by Gao et al. First, the analysis will consider the total pressure losses on a two-dimensional section downstream of the cascade. The Reynolds stresses and the turbulent kinetic energy budget are analysed within the separation region, on a two-dimensional section at the trailing edge of the blade. The RANS simulations mostly overestimate the total pressure losses and the size of the corner separation, compared to the LES and the experiment. The RANS simulations also overestimate the level of the Reynolds stresses and the terms of the turbulent kinetic energy budget, compared to the LES. The quadratic constitutive relation yields some modifications, but not significant enough to have results comparable to LES.

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Parameter study on numerical simulation of corner separation in LMFA-NACA65 linear compressor cascade

Cited by 17 publications

References 49 publications

Numerical investigation on corner separation control in a linear compressor cascade by synthetic jet

Numerical investigation on corner separation control in a linear compressor cascade by synthetic jet

Turbulence modelling analysis in a corner separation flow

Budget Analysis of Turbulent Kinetic Energy in Corner Separation : Rans vs Les

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