Plasma Actuators for Separation Control of Low Pressure Turbine Blades

Huang, Junhui; Corke, Thomas; Thomas, Flint O.

doi:10.2514/6.2003-1027

Cited by 136 publications

(67 citation statements)

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“…6 Furthermore, the actuator can be operated at atmospheric pressures and does not require a sophisticated power supply. SDBDs have the ability to manipulate the boundary layer, 7-11 film cooling 12 and delaying separation on turbine blades 13 and aerofoils, 14 and manipulate the transition point, 15 control separation on stationary 16 and oscillating aerofoils 17 leading to reduced noise levels. 18 However, to date, they have only been used at micro air vehicle Reynolds numbers (e.g., on small unmanned aircraft 19,20 ).…”

Section: Introductionmentioning

confidence: 99%

Plasma actuator: Influence of dielectric surface temperature

Erfani

Zare‐Behtash

Kontis

2012

Experimental Thermal and Fluid Science

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Plasma actuators have become the topic of interest of many researchers for the purpose of flow control. They have the advantage of manipulating the flow without the need for any moving parts, a small surface profile which does not disturb the free stream flow, and the ability to switch them on or off depending on the particular situation (active flow control). Due to these characteristics they are becoming very popular for flow control over aircraft wings. The objective of the current study is to examine the effect of the actuator surface temperature on its performance. This is an important topic to understand when dealing with real life aircraft equipped with plasma actuators. The temperature variations encountered during a flight envelope may have adverse effects in actuator performance. A peltier heater along with dry ice are used to alter the actuator temperature, while particle image velocimetry (PIV) is utilised to analyse the flow field. The results show a significant change in the induced flow field by the actuator as the surface temperature is varied. It is found that for a constant peak-to-peak voltage the maximum velocity produced by the actuator depends directly on the dielectric surface temperature. The findings suggest that by changing the actuator temperature the performance can be maintained or even altered at different environmental conditions.

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Section: Introductionmentioning

confidence: 99%

Plasma actuator: Influence of dielectric surface temperature

Erfani

Zare‐Behtash

Kontis

2012

Experimental Thermal and Fluid Science

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“…To compare with the experiment results, the airfoil parameters are the same as that provided by Huang et al (2006). As shown in Fig.…”

Section: Structure Parameters Of Airfoilmentioning

confidence: 99%

“…The experiment carried out by Hao and Qiao (2006) illustrated that the stall performance and maximal lift coefficient of YLSG107 airfoil were improved by synthetic jets and the performance was influenced by maximal velocity of jets outlet, the form of airfoil, the location of synthetic jets and the angle of injects. Huang et al (2006) used the plasma actuators to control the separation of LPT blade. In their experiments, the actuators located on the suction surface of LPT blade were designed to produce steady jets to reduce the separation.…”

Section: Introductionmentioning

confidence: 99%

Performance Improvement of Low Pressure Turbine Blade by Using Synthetic Jets

Liu

Wang

2011

Engineering Applications of Computational Fluid Mechanics

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ABSTRACT:In order to investigate the effect of flow separation control using synthetic jets on the performance of a low pressure turbine (LPT) blade, the three-dimensional viscous unsteady Reynolds-averaged Navier-Stokes equations are solved to predict the unsteady flow characteristics of the LPT Pak-B blade with and without synthetic jets. For turbulent flow, shear stress transport (SST) turbulence model coupled with Langtry-Menter transition model is adopted. The numerical results show that the turbulence simulations can describe the flow structure effectively and capture the flow separation and reattachment locations on the suction surface of the Pak-B blade. At low Reynolds numbers, using synthetic jet can effectively suppress or even eliminate the flow separation on the blade suction surface. At Re =25,000 and freestream turbulence intensity FSTI =0.08%, there is a synthetic jet frequency in the range from 0Hz to 50Hz for optimal flow control of the LPT blade. The total pressure loss of the LPT blade decreases by 59%, compared with that of non-synthetic jet blade at the blowing ratio B=2.0 and the optimal jet frequency f=20Hz. In addition, the flow control mechanism of synthetic jets is revealed in detail. A hysteresis is observed in the process of flow control by using synthetic jets to reattach the blade boundary layer flow separation. The hysteresis in the blowing process of synthetic jets and the acquirement of enough time to restrain the separation in the sucking process are the main factors which affect the selection of synthetic jet frequency.

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“…Huang et al [41] conducted experiments on the PAK-B blade cascade for a range of Reynolds numbers and turbulence intensities. The experiments were performed at the design incidence angle for Reynolds numbers of 50,000, 75,000, and 100,000 based on inlet velocity and axial chord length, with turbulence intensities of 0.08%, 2.35% and 6.0% (which corresponded to values of 0.08%, 1.6%, and 2.85% at the leading edge of the blade).…”

Section: Turbomachinery Test Casesmentioning

confidence: 99%