scholarly journals Comparison of Performances of Turbines for Wave Power Conversion.

1999 ◽  
Vol 65 (634) ◽  
pp. 2063-2070 ◽  
Author(s):  
Toshiaki SETOGUCHI ◽  
Manabu TAKAO ◽  
Yoichi KINOUE ◽  
Kenji KANEKO ◽  
Tae-Ho KIM ◽  
...  
2000 ◽  
Vol 24 (4−2) ◽  
pp. 815-818 ◽  
Author(s):  
Shinki Kikuchi ◽  
Kiyoshi Ishizawa ◽  
Keiichi Ueki

2000 ◽  
Vol 6 (2) ◽  
pp. 129-134 ◽  
Author(s):  
T. Setoguchi ◽  
M. Takao ◽  
K. Kaneko

A number of self-rectifying air turbines for wave power conversion have been proposed so far. This paper shows the comparison of the performances of all these turbines proposed for use in the near future. As a result, the impulse turbine with self-pitch-controlled guide vanes is found to have the best performance.


2001 ◽  
Vol 40 (7) ◽  
pp. 681-689 ◽  
Author(s):  
Tae-Ho Kim ◽  
Manabu Takao ◽  
Toshiaki Setoguchi ◽  
Kenji Kaneko ◽  
Masahiro Inoue

2003 ◽  
Vol 28 (13) ◽  
pp. 2113-2127 ◽  
Author(s):  
T. Setoguchi ◽  
Y. Kinoue ◽  
T.H. Kim ◽  
K. Kaneko ◽  
M. Inoue

2000 ◽  
Vol 66 (646) ◽  
pp. 1421-1427
Author(s):  
Hideaki MAEDA ◽  
Toshiaki SETOGUCHI ◽  
Manabu TAKAO ◽  
Kenji KANEKO ◽  
Masahiro INOUE

2003 ◽  
Vol 125 (2) ◽  
pp. 302-307 ◽  
Author(s):  
Y. Kinoue ◽  
T. Setoguchi ◽  
T. H. Kim ◽  
K. Kaneko ◽  
M. Inoue

A Wells turbine for wave power conversion has hysteretic characteristics in a reciprocating flow. The counterclockwise hysteretic loop of the Wells turbine is opposite to the clockwise one of the well-known dynamic stall of an airfoil. In this paper, the mechanism of the hysteretic behavior was elucidated by an unsteady three-dimensional Navier-Stokes numerical simulation. It was found that the hysteretic behavior was associated with a streamwise vortical flow appearing near the blade suction surface. In the accelerating process of axial flow velocity, the vortex is intensified to enlarge the flow separation area on the blade suction surface. In the decelerating flow process, the flow separation area is reduced because of the weakened vortex. Therefore, the aerodynamic performance in the accelerating flow process is lower than in the decelerating flow process, unlike the dynamic stall. Based on the vortex theorem, the mechanism to vary the intensity of the vortex can be explained by the trailing vortices associated with the change in the blade circulation.


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