Separated Flow in a Low-Speed Two-Dimensional Cascade: Part I—Flow Visualization and Time-Mean Velocity Measurements

Yocum, A. M.; O’Brien, Walter F.

doi:10.1115/1.2929268

Cited by 9 publications

(3 citation statements)

References 11 publications

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“…The stagger angle was kept at 51· and only the incidence angle was varied from -40· to 20· by rotating the turning table. Thus, the effect of the stagger angle was not explored in the present research even though its effect on the performance of a cascade is significant as Yocum and O'Brien (1993) claimed. The blade is a double circular airfoil with blade height of 20 em.…”

Section: Flow Condition and Grid Testmentioning

confidence: 96%

“…Sovran (1959) reported that for conditions when rotating stall occurred, the phenomena closely resemble a Karman vortex street. Yocum and O'Brien (1993) presented flow visualization and time-mean velocity characteristics of stalled flow in a cascade. They suggested that the flow of a larger stagger cascade is more easily diverted around the separation region, resulting in the separated region extending further into the blade passage.…”

Section: Introductionmentioning

confidence: 99%

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Computation of turbulent flows and radiated sound from axial compressor cascade

Lee

Kim

et al. 2004

KSME International Journal

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The losses at off-design points from a compressor cascade occur due to the deviation from a design incidence angle at the inlet of the cascade. The self-noise from the blade cascade at off-design points comes from a separated boundary layer and vortex sheddings. If the incidence angle to the cascade increases, stalling in blades may occur and the noise level increases significantly. This study applied Large-Eddy Simulations (LES) using deductive and deductive dynamic SGS models to low Mach-number, turbulent flow with each incidence angle to the cascade ranging from -40°to +20°, and compared numerical predictions with measured data. It was observed that the oscillating separation bubbles attached to the suction surface do not modify wake flows dynamically for cases of negative incidence angles. However, an incidence angle greater than 8°caused a separated vortex near the leading edge to be shed downstream and created stalling. The computed performance parameters such as drag coefficient and total pressure loss coefficient showed good agreement with experimental results. Noise from the cascade of the compressor is summarized as sound generated by a structure interacting with unsteady, turbulent flows. The hybrid method using acoustic analogy was observed to closely predict the measured overall sound powers and directivity patterns at design and off-design points of blade cascade.

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Section: Flow Condition and Grid Testmentioning

confidence: 96%

Section: Introductionmentioning

confidence: 99%

Computation of turbulent flows and radiated sound from axial compressor cascade

Lee

Kim

et al. 2004

KSME International Journal

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show abstract

“…For a compressor it occurs at the junction of the end-wall and the blade suction side. The corner separation has been investigated experimentally on linear compressor cascades [3,4,2,5], and numerically [6], but its physics is not yet entirely understood.…”

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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An improved prediction model for corner stall in axial compressors with dihedral effect

2020

Chinese Journal of Aeronautics

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Separated Flow in a Low-Speed Two-Dimensional Cascade: Part I—Flow Visualization and Time-Mean Velocity Measurements

Cited by 9 publications

References 11 publications

Computation of turbulent flows and radiated sound from axial compressor cascade

Computation of turbulent flows and radiated sound from axial compressor cascade

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

An improved prediction model for corner stall in axial compressors with dihedral effect

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