Controlling Separation on a Simulated Compressor Blade Using Vortex Generator Jets

Evans, Steven W.; Hodson, H. P.; Hynes, T. P.; Wakelam, Christian; Hiller, S.

doi:10.2514/6.2008-4317

Cited by 6 publications

(5 citation statements)

References 16 publications

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“…3,[17][18][19][20] In addition, because of the introduction of unsteady controlling parameters and factors for UPB and USJ (the UFC technique), they have been already proved to be more efficient than steady blowing (the SFC technique) in the control of flow separation. [5][6][7][8][9][10][11] This prompts a question: whether UPS, as a UFC technique, can also obtain a better result in controlling flow separation than SCS? Thus, it is very necessary to further research on the above question.…”

Section: Methodsmentioning

confidence: 99%

“…In addition, UPB and USJ show also good beneficial effects in improving the cascade performance. [5][6][7][8][9][10][11] This inspires great interest and curiosity that which type of UFC techniques is more advantageous in controlling flow separation. Therefore, UPS, UPB, and USJ need to be further analyzed comparatively in detail for getting more insights.…”

Section: The Effect Of Excitation Locationmentioning

confidence: 99%

“…Vortex generator jets were also applied to alleviate the flow separations on the surface of a flat plate representing the suction side of the compressor. 8 The results showed that steady blowing can successfully enhance performance and decrease the loss coefficient. However, when using unsteady pulsed blowing (UPB), the same effects could be achieved with a 40% reduction of injected mass flow rates.…”

Section: Introductionmentioning

confidence: 97%

“…Simultaneously, UPB and USJ show also great advantages over the traditional SFC techniques in improving the cascade performance. [5][6][7][8][9] This inspires interest and curiosity that which type of UFC techniques is more advantageous in suppressing the extent of flow separation and reducing the loss. Thus, the UFC techniques including UPS, UPB, and USJ are analyzed comparatively in detail.…”

Section: Introductionmentioning

confidence: 99%

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A comparison of different unsteady flow control techniques in a highly loaded compressor cascade

Chen

Gong

Wang

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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A numerical research is applied to investigate the effect of controlling the flow separation in a certain highly loaded compressor cascade using different unsteady flow control techniques. Firstly, unsteady pulsed suction as a new novel unsteady flow control technique was proposed and compared to steady constant suction in the control of flow separation. A more exciting effect of controlling the flow separation and enhancing the aerodynamic performance for unsteady pulsed suction was obtained compared to steady constant suction with the same time-averaged suction flow rate. Simultaneously, with the view to further exploring the potential of unsteady flow control technique, unsteady pulsed suction, unsteady pulsed blowing, and unsteady synthetic jet (three unsteady flow control techniques) are analyzed comparatively in detail by the related unsteady aerodynamic parameters such as excitation location, frequency, and amplitude. The results show that unsteady pulsed suction shows greater advantage than unsteady pulsed blowing and unsteady synthetic jet in controlling the flow separation. Unsteady pulsed suction and unsteady synthetic jet have a wider range of excitation location obtaining positive effects than unsteady pulsed blowing. The ranges of excitation frequency and excitation amplitude for unsteady pulsed suction gaining favorable effects are both much wider than that of unsteady pulsed blowing and unsteady synthetic jet. The optimum frequencies of unsteady pulsed suction, unsteady pulsed blowing, and unsteady synthetic jet are found to be different, but these optimum frequencies are all an integer multiple of the natural frequency of vortex shedding. The total pressure loss coefficient is reduced by 16.98%, 16.55%, and 17.38%, respectively, when excitation location, frequency, and amplitude are all their own optimal values for unsteady pulsed suction, unsteady pulsed blowing, and unsteady synthetic jet. The optimum result of unsteady synthetic jet only slightly outperforms that of unsteady pulsed suction and unsteady pulsed blowing. But unfortunately, there is no advantage from the standpoint of overall efficiency for the optimum result of unsteady synthetic jet because the slight improvement has to require a greater power consumption than the unsteady pulsed suction and unsteady pulsed blowing methods.

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Section: Methodsmentioning

confidence: 99%

Section: The Effect Of Excitation Locationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 97%

Section: Introductionmentioning

confidence: 99%

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A comparison of different unsteady flow control techniques in a highly loaded compressor cascade

Chen

Gong

Wang

2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Injection can also be used as a vortex-generator or pulsed vortex-generator to control flow separations, such as the investigation carried out by Evans et al 23,24 which showed that the minimum loss coefficient achieved for a blowing ratio required to just keep the boundary layer attached with vortex generator jets. Hodson et al 25 adopted vortex-generator jets to remove flow separation on the suction surface in a compressor cascade at high incidence.…”

Section: Introductionmentioning

confidence: 99%

Influence of endwall slotted injection on performance and flow physics in a compressor cascade

Cao

Song

Liu

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part A:

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Air injection is an effectively methodology to suppress flow separation and to improve blade loading of airfoils and compressors. In order to remove corner separations in a cascade, investigation of endwall slotted injection was carried out numerically in this study. Based on endwall slot schemes of other flow control methods, six different endwall slots were designed, aiming at revealing the axial location effect and pitchwise location effect. For each endwall slot, numerical simulations were performed with six different injection directions to uncover the injection direction effect. Results showed that endwall slotted injection can effectively remove the corner separation. The overall loss coefficient and endwall loss coefficient of the cascade were reduced by 10.3% and 36.8% at most, respectively. Injection from leading edge and mid-chord can reduce endwall loss; however, the optimal axial location of endwall slot is near the trailing edge, where the corner separation is located. Different with other flow control methods, in general, the optimal pitchwise location of endwall slot is not close to suction surface but 0.16 pitch away from it. Injection near the suction surface is more sensitive to injection direction compared with injection at 0.16 pitch away from suction surface. Injection with velocity components both downstream and toward suction surface promises optimal control effect on corner separation. However, at mid-span, trailing edge separation is deteriorated and the flow turning angle is reduced, the flow mechanism being that the low-momentum fluid migrates along spanwise.

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Aerodynamic Performance Characteristics of NACA 0010 Cascade with Gurney Flaps

Nilavarasan

Joshi

Chandel

2018

International Journal of Turbo &Amp; Jet-Engines

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Computational investigations on the effect of Gurney flaps in a NACA 0010 cascade with a 90o blade angle were carried out using STARCCM+ code. The flaps were positioned at the trailing edge of the blades and were aligned at 45o and 90o to the blade chord. The variations in the lift, drag, aerodynamic efficiency and static pressure distributions were recorded on the blades and were compared with the baseline case. Significant increase in the lift coefficient was observed due to the Gurney flaps accompanied by a small drag penalty. This is achieved by increasing the effective camber of the blade, thereby increasing the pressure difference between the pressure and suction surfaces. The Gurney flaps increased the aerodynamic efficiency of the blade at lower angles of attack, whereas at higher angles a small drop in the value was observed.

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Controlling Separation on a Simulated Compressor Blade Using Vortex Generator Jets

Cited by 6 publications

References 16 publications

A comparison of different unsteady flow control techniques in a highly loaded compressor cascade

A comparison of different unsteady flow control techniques in a highly loaded compressor cascade

Influence of endwall slotted injection on performance and flow physics in a compressor cascade

Aerodynamic Performance Characteristics of NACA 0010 Cascade with Gurney Flaps

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