Active Flow Control Concepts on a Highly Loaded Subsonic Compressor Cascade: Résumé of Experimental and Numerical Results

Gmelin, Christoph; Zander, Vincent; Hecklau, Martin; Thiele, Frank; Nitsche, W.; Huppertz, André; Swoboda, M.

doi:10.1115/1.4006308

Cited by 35 publications

(23 citation statements)

References 14 publications

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“…Zaki et al [7] used direct numerical simulation methods to research bypass transition and separation-induced transition in compressor cascades, showing the flow mechanism of bypass transition which appeared on the pressure surfaces of blades and explaining the effect of the pressure gradient on blade surfaces on the start and reattachment in the transition process. Gmelin et al [8] experimentally and numerically studied the effect of three active flow control methods including a stable jet, pulsed jet and zero mass jet on the flow and performance of the compressor and compared the methods' transition locations and geometry on the suction surface. Gbadebo et al [9] researched the effect of boundary layer suction on three-dimensional separation.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Positively Curved Blade in Compressor Cascade Based on Transition Model

Chen

Lan

Zhou

et al. 2016

International Journal of Turbo &Amp; Jet-Engines

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Experiment and numerical simulation of flow transition in a compressor cascade with positively curved blade is carried out in a low speed. In the experimental investigation, the outlet aerodynamic parameters are measured using a five-hole aerodynamic probe, and an ink-trace flow visualization is applied to the cascade surface. The effects of transition flow on the boundary layer development, three-dimensional flow separation and aerodynamic performance are studied. The feasibility of a commercial computational fluid dynamic code is validated and the numerical results show a good agreement with experimental data. The blade-positive curving intensifies the radial force from the endwalls to the mid-span near the suction surface, which leads to the smaller scope of the intermittent region, the lesser extents of turbulence intensity and the shorter radial height of the separation bubble near the endwalls, but has little influence on the flow near the mid-span. The large passage vortex is divided into two smaller shedding vortexes under the impact of the radial pressure gradient due to the positively curved blade. The new concentrated shedding vortex results in an increase in the turbulence intensity and secondary flow loss of the corresponding region.

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Section: Introductionmentioning

confidence: 99%

Investigation of Positively Curved Blade in Compressor Cascade Based on Transition Model

Chen

Lan

Zhou

et al. 2016

International Journal of Turbo &Amp; Jet-Engines

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“…It was shown that passive flow control using vortex generators can reduce total pressure losses by affecting the corner separation at the crossing of the wall and blade [2,3]. It was reported also that active flow control using blowing, suction or synthetic jets can decrease greatly the total pressure losses by removing the corner separation [4][5][6][7][8][9].…”

Section: Introductionmentioning

confidence: 99%

“…In addition, this combination of blowing becomes more efficient when changing the blowing mass flow rate. Gmelin et al [6] investigated active flow control on a highly loaded subsonic compressor cascade using both numerical and experimental approaches. The active flow technique consists of three concepts of steady jets, pulsed jets, and zero mass flow jets (synthetic jets), in two different locations: at the endwall and the blade suction side.…”

Section: Introductionmentioning

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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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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“…Just to name a few among the numerous works, typical flow control applications include boundarylayer blowing or suction to suppress the separation [20], trailing-edge blowing [21], shockwave/boundary-layer interaction control [22], circulation control for lift enhancement [23], etc. Also, optimizations have been applied to FC designs by a number of researchers.…”

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confidence: 99%

Combining Shaping and Flow Control for Aerodynamic Optimization

Zhang

2015

AIAA Journal

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Shape optimization and flow control have been extensively studied in the past to improve the performance of wings and blades. However, they are commonly applied as two separate disciplines, with their interactions being rarely studied. The present work aims to examine and identify the potential to explore the interactions between the two disciplines and is chiefly concerned about two related issues: 1) how much more performance improvement can be obtained by combining the shape optimization with the flow control optimization, and 2) the effects of the sequencing of the disciplines when the optimizations are combined. To address these issues, five optimization approaches have been studied, representing the shaping only, the flow control optimization only, and three different sequencings of the disciplines in the combined optimizations. All the optimization approaches are applied consistently by using the same optimization system developed in this research. The system uses the Kriging surrogate method as the optimization algorithm, and it incorporates a standard computational fluid dynamics solver for which the validity and numerical sensitivities have been assessed. The developed methodology is applied to two optimization cases of practical interest: a compressor blade and a circulation controlled airfoil. The results of both cases show that, when shaping and flow control optimizations are combined, the performance enhancement is considerably higher than when the two disciplines are applied separately. Furthermore, in the combined optimizations for the airfoil, it is observed that the concurrent optimization leads to the highest performance, whereas the sequential optimizations tend to be "stuck" at less optimal solutions. Nomenclaturechord length in the x direction c 0 = chord length of the baseline airfoil L = lift Ma = Mach number _ m = mass flow rate N s = number of samples N v = number of design variables P j = power required by blade flow control p = static pressure p 0 = total pressure Re = Reynolds number t = blade cascade pitch length V = velocity magnitude x co;cc = chordwise position of the start of a Coanda surface sector x s;cc = chordwise position of the slot for circulation control x s1 = chordwise position of the blowing slot on the blade x s2 = chordwise position of the suction slot on the blade β = blade inlet flow angle β max = maximum operating inlet flow angle γ = blade stagger angle δ = direction normal to the blade chord η = efficiency ξ = direction along the blade chord Subscripts d = condition at the design inlet flow angle eq= equivalent quantity j = jet parameter s = slot parameter 0 = stagnation/baseline parameter 1 = condition of inlet-mass-averaged (blade), freestream (airfoil), or blowing (slot) 2 = condition of outlet-mass-averaged (blade) or suction (slot)

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Active Flow Control Concepts on a Highly Loaded Subsonic Compressor Cascade: Résumé of Experimental and Numerical Results

Cited by 35 publications

References 14 publications

Investigation of Positively Curved Blade in Compressor Cascade Based on Transition Model

Investigation of Positively Curved Blade in Compressor Cascade Based on Transition Model

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

Combining Shaping and Flow Control for Aerodynamic Optimization

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