Blade Design with Passive Flow Control Technologies

González-Salcedo, Álvaro; Croce, Alessandro; León, Carlos Arce; Nayeri, Christian Navid; Baldacchino, Daniel; Vimalakanthan, Kisorthman; Barlas, Thanasis K.

doi:10.1007/978-3-030-05455-7_6-1

Cited by 5 publications

(2 citation statements)

References 72 publications

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“…Passive GFs are categorized as static miniflaps or miniature trailing edge devices (MiniTEDs), as described by González-Salcedo et al (2020). Hence, they are different to the concept of flexible trailing edge (TE) flaps that are integrated into the very TE section, see Barlas and van Kuik (2010).…”

Section: Gurney Flapsmentioning

confidence: 99%

Experimental investigation of Mini Gurney Flaps in combination with vortex generators for improved wind turbine blade performance

Alber

Μανωλέσος

Weinzierl-Dlugosch³

et al. 2021

Preprint

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Abstract. This wind tunnel study investigates the aerodynamic effects of Mini Gurney flaps (MGFs) and their combination with vortex generators (VGs) on the performance of airfoils and wind turbine rotor blades. VGs are installed on the suction side aiming at stall delay and increased maximum lift. MGFs are thin angle profiles that are attached at the trailing edge in order to increase lift at pre-stall operation. The implementation of both these passive flow control devices is accompanied by a certain drag penalty. The wind tunnel tests are conducted at the Hermann- Föttinger Institut of the Technische Universität Berlin. Lift is determined with a force balance and drag with a wake rake for static angles of attack from −5° to 17° at a constant Reynolds number of 1.5 million. The impact of different MGF heights including 0.25 %, 0.5 % and 1.0 % and an uniform VG height of 1.1 % of the chord length are tested on three airfoils that are characteristic for different sections of large rotor blades. Furthermore, the clean and the tripped baseline cases are considered. In the latter, leading edge transition is forced by means of Zig Zag (ZZ) turbulator tape. The preferred configurations are the smallest MGF on the NACA63(3)618 and the AH93W174 (mid to tip blade region) and the medium sized MGF combined with VGs on the DU97W300 (root to mid region). Next, the experimental lift and drag polar data is imported into the software QBlade in order to design a generic rotor blade. The blade performance is simulated with and without the add-ons based on two case studies. In the first case, the retrofit application on an existing blade mitigates the adverse effects of the ZZ tape. Stall is delayed and the aerodynamic efficiency is partly recovered leading to an improvement of the power curve. In the second case, the new design application allows for the design of a more slender blade while maintaining the power output. Moreover, the alternative blade appears to be more resistant against forced leading edge transition.

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Section: Gurney Flapsmentioning

confidence: 99%

Experimental investigation of Mini Gurney Flaps in combination with vortex generators for improved wind turbine blade performance

Alber

Μανωλέσος

Weinzierl-Dlugosch³

et al. 2021

Preprint

Self Cite

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“…With that objective, active and passive flow control devices have been introduced in wind turbine blades with the intention of enhancing or optimizing their performance. Aramendia-Iradi et al [2] comprehensively reviewed the available active and passive flow control devices for wind turbine blades, while González-Salcedo et al [3] only studied the passive flow control devices.…”

Section: Introductionmentioning

confidence: 99%

Rotating Microtab Implementation on a DU91W250 Airfoil Based on the Cell-Set Model

et al. 2021

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Flow control device modeling is an engaging research field for wind turbine optimization, since in recent years wind turbines have grown in proportions and weight. The purpose of the present work was to study the performance and effects generated by a rotating microtab (MT) implemented on the trailing edge of a DU91W250 airfoil through the novel cell-set (CS) model for the first time via CFD techniques. The CS method is based on the reutilization of an already calculated mesh for the addition of new geometries on it. To accomplish that objective, the required region is split from the main domain, and new boundaries are assigned to the mentioned construction. Three different MT lengths were considered: h = 1%, 1.5% and 2% of the airfoil chord length, as well as seven MT orientations (β): from 0° to −90° regarding the horizontal axis, for five angles of attack: 0°, 2°, 4°, 6° and 9°. The numerical results showed that the increases of the β rotating angle and the MT length (h) led to higher aerodynamic performance of the airfoil, CL/CD = 164.10 being the maximum ratio obtained. All the performance curves showed an asymptotic trend as the β angle reduced. Qualitatively, the model behaved as expected, proving the relationship between velocity and pressure. Taking into consideration resulting data, the cell-set method is appropriate for computational testing of trailing edge rotating microtab geometry.

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Research Progress of hypersonic boundary layer transition control experiments

et al. 2022

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Hypersonic boundary layer transition is a hot yet challenging problem restricting the development and breakthrough of hypersonic aerodynamics. In recent years, despite great progress made by wind tunnel experiment, transition mechanism and transition prediction, only partial knowledge has been gained so far. In this paper, firstly, the specific scenarios of hypersonic boundary layer transition control are clarified. Secondly, the experimental research progress and mechanism of passive control and active control methods under different hypersonic transition control demands are summarized, with their advantages and disadvantages being analyzed separately. Plasma actuation is easy to produce controllable broadband aerodynamic actuation, which has potential in the field of boundary layer transition control. Hence, the following part of the paper focuses on plasma flow control. The feasibility of plasma actuation to control the hypersonic boundary layer transition is demonstrated and the research ideas are presented. Finally, hypersonic boundary layer transition control methods are summarized and the direction of future research is prospected.

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Blade Design with Passive Flow Control Technologies

Cited by 5 publications

References 72 publications

Experimental investigation of Mini Gurney Flaps in combination with vortex generators for improved wind turbine blade performance

Experimental investigation of Mini Gurney Flaps in combination with vortex generators for improved wind turbine blade performance

Rotating Microtab Implementation on a DU91W250 Airfoil Based on the Cell-Set Model

Research Progress of hypersonic boundary layer transition control experiments

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