Experimental Study of Corner Stall in a Linear Compressor Cascade

Ma, Wei; Ottavy, Xavier; Lu, Lipeng; Leboeuf, Francis; Gao, Feng

doi:10.1016/s1000-9361(11)60028-9

Cited by 40 publications

(45 citation statements)

References 13 publications

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“…It is representative of highly loaded compressor stator blades found in modern jet engine compressors. It consists of NACA65-009 airfoils and was tested experimentally by Wei et al [10]. According to the experimental data, the inlet of the tested domain is located at 2.16 axial chords upstream of the leading edge of the blade and the outlet is at 1.36 axial chords downstream of the trailing edge.…”

Section: Cascade Configuration and Gridmentioning

confidence: 99%

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Numerical investigation of three-dimensional separation control in an axial compressor cascade

Djedai¹,

Mdouki²,

Mansouri³

et al. 2017

IJHT

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The aerodynamic performances of three-dimensional compressor cascade are mainly influenced by secondary flow effects, such as the cross flow on the side wall and the corner separation at the wall-blade junction. Often, these secondary flows can produce a blockage and losses in the blade passage. A numerical study of active flow control using blowing technique in a linear compressor cascade has been carried out, in order to eliminate the 3D boundary layer stall and enhance the aerodynamic performance. The numerical simulation is performed using steady and incompressible RANS (Reynolds averaged Navier-Stokes) equations with Realizable k-ε turbulence model. Good agreement is found between numerical results and experimental data, in particular pressure coefficient (CP) and total pressure loss coefficient (). A detailed flow topology analysis is mentioned and gave the flow structure and the separation zone behavior. It was found that the blowing slot should be located upstream the dual nature critical point which represents the origin of separation. Furthermore, three suction slot configurations are used to control the separation, whereas one configuration on the suction side of the blade and two configurations are on the endwall. The first endwall slot is located parallel to the suction side of the blade and the second one is located perpendicular to the axial chord of the blade. Results indicate that the removal of the corner separation was not achieved using the slots on the blade suction side and on the endwall parallel to the suction side. Contrariwise, the perpendicular endwall slot was found to be most effective and the 3D separation is completely disappeared.

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Section: Cascade Configuration and Gridmentioning

confidence: 99%

“…The experimentally measured inlet velocity profile [10] is considered to define the inlet condition using User-Define Function (UDF technique) with a turbulence intensity I = 0.8%. At the outlet, static pressure is specified with the extrapolating technique from neighboring interior cells.…”

Section: Computational Procedures and Boundary Conditionsmentioning

confidence: 99%

Numerical investigation of three-dimensional separation control in an axial compressor cascade

Djedai¹,

Mdouki²,

Mansouri³

et al. 2017

IJHT

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“…Ma et al [2,5] lead an experimental campaign on the LMFA-NACA65 linear cascade. The sketch of the experimental set-up is given figure 1.…”

Section: Experimental Set-upmentioning

confidence: 99%

“…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%

“…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 [1] using the Shearimproved Smagorinsky model (SISM), and has been validated by comparison with the experimental data obtained by Ma et al [2]. Two steady RANS simulations are carried out using k − ω models: Wilcox 1988 model and Wilcox 1988 model with quadratic constitutive relation.…”

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confidence: 99%

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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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Active Flow Control on a Highly Loaded Compressor Cascade with Non-steady Boundary Conditions

Staats

Nitsche

Peltzer

2015

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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Abstract. This paper discusses the effect of a periodical disturbance in the wake of a highly loaded axial compressor on the pressure distribution and the secondary flow characteristics of the turbo machinery stator blades. A large scale axial compressor cascade, consisting of six two dimensional passages, has been used for this investigation. The test rig is equipped with an active flow control system to enhance the operating range of the compressor. Results that have been achieved by means of side wall actuation are also presented.

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Experimental Study of Corner Stall in a Linear Compressor Cascade

Cited by 40 publications

References 13 publications

Numerical investigation of three-dimensional separation control in an axial compressor cascade

Numerical investigation of three-dimensional separation control in an axial compressor cascade

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

Active Flow Control on a Highly Loaded Compressor Cascade with Non-steady Boundary Conditions

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