Wind Energy Handbook. Michael Barton Graham

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Figure 3.26 The variation of maximum C_P with design λ for various lift/drag ratios.

A similar result is apparent for the inflow angle distribution (Figure 3.25), in which drag is also seen to have little influence.

      As far as blade design for optimal operation is concerned, drag can be ignored, greatly simplifying the process.

The results of Eq. (3.57) show that the maximum power coefficients for a range of design tip speed ratios and several lift/drag ratios are as shown in Figure 3.26. The flow induction factors have been determined without drag using Eqs. (3.54a) and (3.55), but the torque has been calculated using Eq. (3.57), which includes drag. The losses caused by drag are significant and increase with increasing design tip speed ratio. As will be shown later, when tip‐losses are also taken into account, the losses at low tip speed ratios are even greater.

      3.8.5 Optimal blade design for constant‐speed operation

      If the rotational speed of a turbine is maintained at a constant level, then the tip speed ratio is continuously changing, and a blade optimised for a fixed tip speed ratio would not be appropriate. Closed‐form solutions have been derived for optimum wind turbines; see Peters and Modarres (2013) and Jamieson (2018).

      No simple technique is available for the optimal design of a blade operating at constant rotational speed. Non‐linear (numerical) optimisation techniques may be used to solve the problem of maximising energy capture at a given site incorporating the data on its specific wind speed distribution. Alternatively, a design tip speed ratio can be chosen corresponding to the wind speed at the specified site that contains the most energy, or, more practically, the pitch angle for the whole blade can be adjusted to maximise energy capture.

3.9 The effects of a discrete number of blades

      3.9.1 Introduction

      The analysis described in all prior sections assumes that the rotor has an infinite number of blades of infinitesimal chord so that every fluid particle passing through the rotor disc passes close to a blade through a region of strong interaction, i.e. that the loss of momentum in any annulus is uniform with respect to azimuth angle θ. With a finite (usually small, two or three) number of blades, some fluid particles will interact more strongly with the blades and some less strongly. The immediate loss of (kinetic) momentum by a particle will depend on the distance between its streamline and the blade as the particle passes through the rotor disc. These differences are subsequently reduced but not eliminated by the action of pressure forces between the adjacent curved streamlines and eventually by mixing. The axial induced velocity will therefore vary around the disc, the average value determining the overall axial momentum of the flow. What is also relevant is the incident velocity (relative angle and speed) that each blade section senses, i.e. to which it responds, as it rotates. When as here the incident flow is not uniform, a blade section senses a weighted average of the flow induced in the region occupied by the section in the absence of its own self‐generated flow field. This is usually evaluated as the velocity at the quarter chord of the section (cf. lifting line theory). For a rotor for which the product σλ of solidity and tip speed ratio is not too small, as is usual, it is found that the combination of incident wind, average axial induced velocity, and blade rotation speed gives a very good approximation to this incident velocity except close to the tip and root ends of the blade, where the sectional approximation breaks down.

3.9.2 Tip‐losses

Where the axial flow induction factor a becomes large at the blade position, then, by Eqs. (3.44), the inflow angle ϕ will reduce, and for a given pitch angle the angle of attack α and hence the lift force will become small. At the tip the lift force must decrease to zero because the blade surface pressures must be continuous around the tip. The component of the lift force in the tangential direction in the tip region will therefore be small and so will be its contribution to the torque. A reduced torque means reduced power, and this reduction is known as tip‐loss because the effect occurs at the outermost parts of the blades. A similar effect occurs for the same reason at the blade root but being at small radius has much less effect on torque and power.