Vortex structure for reducing tip leakage flow of linear turbine cascade using dielectric barrier discharge plasma actuator

Matsunuma, Takayuki; Segawa, Takehiko

doi:10.1016/j.ast.2023.108215

Cited by 4 publications

(7 citation statements)

References 60 publications

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“…This was because the PV and TLV became equally strong, thus interfering with and weakening each other. In the previous study for reducing the TLV using a PA conducted by Matsunuma and Segawa [58], as the TLV became weaker and smaller by the drive of the PA, the PV became stronger and larger. This phenomenon is similar to the result of this study.…”

Section: Effects Of Tip Clearance Size Under the Condition Of No Controlmentioning

confidence: 97%

“…The two-dimensional velocity field at the exit of the LTC was recorded using PIV. A detailed description of the PIV system was provided by Matsunuma and Segawa [58]. Atomized dioctyl sebacate (DOS) oil with an average particle diameter of 1 µm was used as the smoke for visualization.…”

Section: Piv Measurements and Data Analysismentioning

confidence: 99%

“…Tip shape [42], squealer tips [43][44][45], stepped squealer tips [46], winglets [47], cavity winglets [48], winglet-cavity tips [49], dual-cavity tips [50], winglet squealer tips [51], and casing grooves [52] have been used as passive control devices. Tip injection [53], blowing jets [54], combined sweeping jet actuators, winglet tips [55], dynamic humps [56], and PAs [57][58][59][60][61] were used as active control devices.…”

Section: Introductionmentioning

confidence: 99%

“…More recently, a turbine blade with 15 PAs arranged at the SS of the blade tip was proposed by a research group led by Chen [59][60][61], and the effect of TLF reduction was examined using both experimental and numerical analysis. In addition, a unique PA in which the electrodes were installed in the static outer casing of the turbine rotor was developed by Matsunuma and Segawa [58].…”

Section: Introductionmentioning

confidence: 99%

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Active Flow Control for Passage Vortex Reduction in a Linear Turbine Cascade with Various Tip Clearance Sizes Using a Dielectric Barrier Discharge Plasma Actuator

Matsunuma

Segawa

2023

Aerospace

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In an axial-flow turbine of a jet engine used for aircraft propulsion, the passage vortex (PV) and tip leakage vortex (TLV) generated inside the blade passage deteriorate the aerodynamic performance. In this study, a dielectric barrier discharge plasma actuator (PA) was installed in the upstream endwall of the turbine cascade to suppress the PV. The effects of the presence or absence of tip clearance and the change in the size of the tip clearance on the vortex structure at the exit of the turbine cascade were observed by recording the flow velocity distributions using particle image velocimetry. In the absence of tip clearance, only the PV existed and was completely suppressed by the PA. By contrast, in the presence of tip clearance, a TLV occurred in addition to the PV. When the input voltage to the PA was varied with various tip clearance sizes, the change in the flow fields where the PV and TLV interfered was clarified. With tip clearance, the PV was suppressed as the input voltage increased; however, the TLV increased considerably. At each tip clearance size, changes in the center positions of the PV and TLV were observed at varying input voltages of the PA. With increasing input voltages of the PA, the center position of the PV moved to the pressure surface side of the tip of the adjacent blade, and the center position of the TLV moved toward the middle of the flow passage. With a larger tip clearance, the amount of movement at the center positions of both the PV and TLV increased.

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Section: Effects Of Tip Clearance Size Under the Condition Of No Controlmentioning

confidence: 97%

Section: Piv Measurements and Data Analysismentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Active Flow Control for Passage Vortex Reduction in a Linear Turbine Cascade with Various Tip Clearance Sizes Using a Dielectric Barrier Discharge Plasma Actuator

Matsunuma

Segawa

2023

Aerospace

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“…As the PA is integrated into the aerodynamic aspects of turbine blades, investigations into mitigating flow separation on the blade suction surface (SS) [27][28][29], blade tip leakage vortex [30][31][32], and PVs [15,16] have been undertaken. This study was conducted as part of a series of experiments to suppress PV using PAs [15,16].…”

Section: Introductionmentioning

confidence: 99%

Effect of Plasma Actuator Layout on the Passage Vortex Reduction in a Linear Turbine Cascade for a Wide Range of Reynolds Numbers

Matsunuma,

Segawa

2023

Actuators

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This study examined how various plasma actuator (PA) configurations affect the passage vortex (PV) reduction in a linear turbine cascade (LTC) utilizing dielectric barrier discharge PAs. The experiments were carried out under three specific layout conditions: axial placement of the PA, slanted placement at the blade inlet, and slanted placement inside the blade. Particle image velocimetry was employed to measure the velocity distribution of the secondary flow at the LTC exit, followed by an analysis of the streamline patterns, turbulence intensity distribution, and vorticity distribution. At a Reynolds number of 3.7 × 104, the PA with an oblique orientation at the blade inlet provided the most effective PV suppression. The average value of the secondary flow velocity and the peak vorticity value at the LTC exit decreased by 59.0% and 68.8%, respectively, compared to the no-control case. Furthermore, the wind tunnel blower’s rotation speed was modified, adjustments were made to the LTC’s mainstream velocity, and the Reynolds number transitioned from 1.0 × 104 to 9.9 × 104, approximately 10 times. When the slanted PA was used at the blade inlet, the PV suppression effect was the highest. The peak vorticity value owing to the PV at the LTC exit decreased by 62.9% at the lowest Reynolds number of 1.0 × 104. The Reynolds number increased with a higher mainstream velocity and decreased flow induced by the PA, consequently reducing the PV suppression effect. However, the drive of the PA was effective even under the most severe conditions (9.9 × 104), and the peak vorticity value was reduced by 20.2%.

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Numerical investigations on film cooling effectiveness and heat transfer performance of inclined film hole on the turbine blade squealer tip with plasma actuation

Zhou,

Zhang,

Huang

et al. 2024

Aerospace Science and Technology

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Vortex structure for reducing tip leakage flow of linear turbine cascade using dielectric barrier discharge plasma actuator

Cited by 4 publications

References 60 publications

Active Flow Control for Passage Vortex Reduction in a Linear Turbine Cascade with Various Tip Clearance Sizes Using a Dielectric Barrier Discharge Plasma Actuator

Active Flow Control for Passage Vortex Reduction in a Linear Turbine Cascade with Various Tip Clearance Sizes Using a Dielectric Barrier Discharge Plasma Actuator

Effect of Plasma Actuator Layout on the Passage Vortex Reduction in a Linear Turbine Cascade for a Wide Range of Reynolds Numbers

Numerical investigations on film cooling effectiveness and heat transfer performance of inclined film hole on the turbine blade squealer tip with plasma actuation

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