0
Research Papers

Simulating Pitching Blade With Free Vortex Model Coupled With Dynamic Stall Model for Conditions of Straight Bladed Vertical Axis Turbines

[+] Author and Article Information
Eduard Dyachuk

Department of Engineering Sciences,
Division of Electricity,
Uppsala University,
Uppsala 751 21, Sweden
e-mail: eduard.dyachuk@angstrom.uu.se

Anders Goude

Department of Engineering Sciences,
Division of Electricity,
Uppsala University,
Uppsala 751 21, Sweden
e-mail: anders.goude@angstrom.uu.se

Hans Berhnoff

Department of Engineering Sciences,
Division of Electricity,
Uppsala University,
Uppsala 751 21, Sweden
e-mail: hans.bernhoff@angstrom.uu.se

1Corresponding author.

Contributed by the Solar Energy Division of ASME for publication in the JOURNAL OF SOLAR ENERGY ENGINEERING: INCLUDING WIND ENERGY AND BUILDING ENERGY CONSERVATION. Manuscript received September 18, 2014; final manuscript received May 13, 2015; published online June 1, 2015. Assoc. Editor: Yves Gagnon.

J. Sol. Energy Eng 137(4), 041008 (Aug 01, 2015) (7 pages) Paper No: SOL-14-1271; doi: 10.1115/1.4030674 History: Received September 18, 2014; Revised May 13, 2015; Online June 01, 2015

This study is on the straight bladed vertical axis turbines (VATs), which can be utilized for both wind and marine current energy. VATs have the potential of lower installation and maintenance cost. However, complex unsteady fluid mechanics of these turbines imposes significant challenges to the simulation tools. Dynamic stall is one of the phenomena associated with the unsteady conditions, and it is in the focus of the study. The dynamic stall effects are very important for VATs, since they are usually passively controlled through the dynamic stall. A free vortex model is used to calculated unsteady attached flow, while the separated flow is handled by the dynamic stall model. This is compared to the model based solely on the Leishman–Beddoes algorithm. The results are assessed against the measured data on pitching airfoils. A comparison of force coefficients between the simulations and experiments is done at the conditions similar to the conditions of H-rotor type VATs.

FIGURES IN THIS ARTICLE
<>
Copyright © 2015 by ASME
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Fig. 1

Dynamic stall illustration, NACA0018, α = 10+12 sin(ωt),k = 0.15,M = 0.1,c = 0.4 m

Grahic Jump Location
Fig. 2

Force response during the pitching motions of NACA0015 airfoil with an amplitude of 22.60 deg at the Reynolds number of 1,000,000. Comparison between the explicit and implicit methods: (a) normal force coefficient and (b) tangential force coefficient.

Grahic Jump Location
Fig. 3

Normal force coefficient during the pitching motions of NACA0015 airfoil with an amplitude of 22.60 deg at the Reynolds number of 1,000,000. Comparison of the results for different blade models during vortex propagation. Note: all simulated results are plotted and almost coincide.

Grahic Jump Location
Fig. 4

Force response during the pitching motions of NACA0015 airfoil with an amplitude of 22.60 deg at the Reynolds number of 1,000,000. Comparison of the results for different numbers of released vortices: (a) normal force coefficient and (b) tangential force coefficient.

Grahic Jump Location
Fig. 5

Force response during the pitching motions of NACA0015 airfoil with an amplitude of 12.20 deg (corresponding to λ = 4.73): (a) normal force coefficient and (b) tangential force coefficient

Grahic Jump Location
Fig. 6

Force response during the pitching motions of NACA0015 airfoil with an amplitude of 17.40 deg (corresponding to λ = 3.34): (a) normal force coefficient and (b) tangential force coefficient

Grahic Jump Location
Fig. 7

Force response during the pitching motions of NACA0015 airfoil with an amplitude of 22.60 deg (corresponding to λ = 2.60): (a) normal force coefficient and (b) tangential force coefficient

Grahic Jump Location
Fig. 8

Force response during the pitching motions of NACA0021 airfoil with an amplitude of 22.60 deg (corresponding to λ = 2.60): (a) normal force coefficient and (b) tangential force coefficient

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In