A New Linear High Speed Compressor Stator Cascade for Active Flow Control Investigations

Tiedemann, Christine; Heinrich, Alexander; Peitsch, Dieter

doi:10.2514/6.2012-3251

Cited by 12 publications

(10 citation statements)

References 2 publications

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“…As found in the series research of Ref. 17 , a transfer of findings of low-speed case to realistic Mach numbers of a real compressor cannot be easily done. Under the real work conditions, compressor blades are more likely to encounter high subsonic fluid, and research groups of German Aerospace Center Deutsches Zentrum fu¨r Luft-und Raumfahrt (DLR), [22][23][24][25][26] Tiedemann 17 and Zhang et al 20 have carried out some trial study to control the corner separation with the inlet Mach number around 0.7.…”

Section: Introductionmentioning

confidence: 95%

“…[1][2][3][4][5][6][7][8][9][10][11] Compressor cascade is a simplified model of real axial compressor stator blade and has been widely applied to researching the mechanism and control of corner separation, as well as the compressor tip clearance flow structures and effects of threedimensional compressor blades. 12,13 Active flow control methods, such as boundary layer suction, [14][15][16] flow blowing, 17,18 plasma flow control 19,21 etc, have been applied to the control of compressor cascade corner separations over years. Meanwhile, the application of passive flow control methods, such as vortex generator, [22][23][24] endwall contouring 25 etc, as well as combination of passive and active control methods, 26 for corner separation control have been investigated with great efforts.…”

Section: Introductionmentioning

confidence: 99%

“…To control the corner separation effectively, the design of both active and passive methods should be based on the in-depth understanding of flow structures in the compressor cascade flow passage and various efforts have been spared. [1][2][3][4][5][6][7][8][9][10][11][14][15][16][17][18][19][20][21][22][23][24][25][26][27] In low speed flow, with inlet Mach number under 0.3, detailed researches on the flow structures in the compressor cascade flow passage have been launched. 3,[7][8][9][10] When inlet Mach number increases to be bigger than 0.3, the flow becomes more unsteady and compressible.…”

Section: Introductionmentioning

confidence: 99%

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Experimental investigation on a high subsonic compressor cascade flow

Zhang

et al. 2015

Chinese Journal of Aeronautics

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With the aim of deepening the understanding of high-speed compressor cascade flow, this paper reports an experimental study on NACA-65 K48 compressor cascade with high subsonic inlet flow. With the increase of passage pressurizing ability, endwall boundary layer behavior is deteriorated, and the transition zone is extended from suction surface to the endwall as the adverse pressure gradient increases. Cross flow from endwall to midspan, mixing of corner boundary layer and the main stream, and reversal flow on the suction surface are caused by corner separation vortex structures. Passage vortex is the main corner separation vortex. During its movement downstream, the size grows bigger while the rotating direction changes, forming a limiting circle. With higher incidence, corner separation is further deteriorated, leading to higher flow loss. Meanwhile, corner separation structure, flow mixing characteristics and flow loss distribution vary a lot with the change of incidence. Compared with low aspect-ratio model, corner separation of high aspect-ratio model moves away from the endwall and is more sufficiently developed downstream the cascade. Results obtained present details of high-speed compressor cascade flow, which is rare in the relating research fields and is beneficial to mechanism analysis, aerodynamic optimization and flow control design.

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Section: Introductionmentioning

confidence: 95%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Experimental investigation on a high subsonic compressor cascade flow

Zhang

et al. 2015

Chinese Journal of Aeronautics

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“…Several active flow control solutions have been proposed to optimize the aerodynamic response of heavily loaded blades. Tiedemann et al [5] investigated experimentally the effect of steady and pulsed blowing through side wall actuators on a linear compressor cascade. They showed that both steady and pulsed jets are effective in suppressing three-dimensional secondary flow phenomena occurring on critically loaded blades.…”

Section: Introductionmentioning

confidence: 99%

Numerical Assessment of Virtual Control Surfaces for Load Alleviation on Compressor Blades

2018

Self Cite

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Virtual control surfaces for the optimization of steady and unsteady airloads on a compressor cascade are assessed numerically. The effects of mechanical surfaces are realized with plasma actuators, located both on the pressure and on the suction side of the blade trailing edge. Suction side plasma actuation is thought to reproduce the effects of mechanical wing spoilers, whereas pressure side plasma actuation is meant to act as a mechanical Gurney flap. Indeed, actuators are operated to generate an induced velocity field that is opposite relative to the direction of the freestream velocity. As a consequence, controlled recirculating flow areas are generated, which modify the effective mean line shape, as well as the position of the Kutta condition application point-and in turn the developed airloads. Proper triggering of pressure/suction side actuation is found to be effective in altering the blade loading, with effects comparable to those of mechanical control surfaces. Traveling wave mode simulations show that significant reductions in the peaks of the blade pitching moment can be achieved on the whole spectrum of interblade phase angles. It is proved that virtual control surfaces can provide effective load alleviation on the cascade, with potential remarkable reduction of fatigue phenomena.

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“…However, it is not always easy to transfer these research results to engineering applications of high-speed flow (Tiedemann, Heinrich, & Peitsch, 2012). CFD application to a highspeed compressor cascade is more difficult because of the more severe corner separations and fully developed flow unsteadiness.…”

Section: Introductionmentioning

confidence: 99%

Evaluation of RANS turbulence models in simulating the corner separation of a high-speed compressor cascade

Zhang

2015

Engineering Applications of Computational Fluid Mechanics

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A typical high-speed compressor cascade flow is simulated using an eddy viscosity model and a Reynolds stress model. Based on comparisons with experimental results, the simulation accuracies of the two turbulence models are evaluated, and some recommendations are provided for further research. Inside the cascade flow passage, the simulation accuracies of both turbulence models decrease because of the corner effect. Downstream of the blade, the wake mixing influence, and thus the flow loss, is under-predicted by both turbulence models. Compared with the linear eddy viscosity model, the modification of the simulation accuracy with regard to endwall flow prediction using the Reynolds stress model is limited, which only occurs at a highly positive incidence angle. The corner separation strength and wake mixing influence predicted by the eddy viscosity model are surpassed by those of the Reynolds stress model. At a negative incidence angle, the simulation result of the Reynolds stress model is proved to be physically unreasonable according to the flow loss prediction.

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A New Linear High Speed Compressor Stator Cascade for Active Flow Control Investigations

Cited by 12 publications

References 2 publications

Experimental investigation on a high subsonic compressor cascade flow

Experimental investigation on a high subsonic compressor cascade flow

Numerical Assessment of Virtual Control Surfaces for Load Alleviation on Compressor Blades

Evaluation of RANS turbulence models in simulating the corner separation of a high-speed compressor cascade

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