Читать книгу Wind Energy Handbook - Michael Barton Graham - Страница 108

For many years the wind turbine industry relied on aeronautical experience for the aerodynamic design of turbine blades, but it became clear that aerofoil sections that were optimum for aircraft wings were not necessarily optimum for wind turbine blades.

A major problem for modern wind turbines in the early years of development was sensitivity to insect deposition on the leading edge regions of the blades. There were reports of turbines in the 1970s having to be regularly hosed with water to clear accumulated debris on the blades to restore power levels that had fallen dramatically. An aerofoil that was tolerant to leading edge roughness was required.

Most early turbines of rated power greater than about 50 kW operated at constant rotational speed and relied upon passive stall for power control. With many aircraft aerofoil sections, the stall produced a sudden sharp loss of power output that was not recovered until the wind speed increased. The stalling resulted in significant losses of energy capture. Thus another requirement for a wind turbine aerofoil was a gentle stall.

Aerofoil stall occurs when the boundary layer on the low‐pressure surface starts to separate at some point before the trailing edge is reached, as shown in Figure A3.12. This process, which is due to sufficiently long and strong regions of rising surface pressure following the ‘suction peak’, is discussed in more detail in A3.3. The process is strongly dependent on the state of the boundary layer (whether laminar or turbulent) and hence the location of transition from laminar to turbulent boundary layer flow and what happens immediately after transition. Transition itself is generated by the presence of flow disturbances in the form of small‐scale turbulence in the incident flow, acoustic noise impinging the blade, roughness elements on the surface, the presence of velocity inflexions – see Figures A3.2 and A3.3 – or profiles near to this state in the boundary layer, and by the thickness of the boundary layer. Usually the incident turbulence in the atmosphere is too large scale to affect transition other than by unsteady ‘sloshing’, effects but it is possible that wake turbulence from other turbines could be significant. There are undoubtedly some acoustic disturbances, but the most significant disturbance for a wind turbine blade is the presence of dirt, insects, and other solid particles accreting on blades, particularly near the leading edge. Velocity profiles tending towards inflexion as described above, which result from regions of adverse pressure gradient, are more sensitive to instability. [Classical inviscid hydrodynamic stability theory – see, for example, Lin (1955), shows that an inflected velocity profile is immediately unstable to disturbances unless the Reynolds number is very low.] If the blade is fairly thick and rounded near the leading edge and the Reynolds number is sufficiently high, transition occurs soon after attachment at the leading edge, and the resulting turbulent boundary layer remains attached to fairly high angles of attack because the adverse pressure gradients are only moderately strong, and separation first occurs at the trailing edge where the boundary layer is thickest. As the angle of attack is increased further, the separation point moves steadily forward. The result is a reasonably high C_Lmax with a more gradual rounded maximum of the C_L‐alpha curve, giving a gradual stall known as trailing edge stall. For somewhat thinner aerofoil sections and/or lower Reynolds numbers, the adverse pressure gradient developing with increased angle of attack on the suction surface causes the laminar boundary layer to separate before transition. Once separated, the resulting free shear layer is highly unstable (because of the inflexion in the profile) and immediately transitions to turbulence followed by rapid reattachment, forming a small separation bubble downstream of which the turbulent boundary layer remains attached up to the trailing edge. Two possibilities then can follow as the angle of attack is further increased: (i) the separation bubble grows steadily in length until reattachment just passes the trailing edge, the bubble bursts, and the aerofoil stalls, or (ii) the bubble remains short, reducing further in length, and suddenly bursts. Possibility (i) is known as thin aerofoil stall and occurs for rather thin sections at fairly low Reynolds numbers. The stall is gradual but not usually relevant to wind turbine blades. Possibility (ii) is known as leading edge stall, giving a very abrupt fall in lift at the stall, is usually very disadvantageous, and can occur on smaller size wind turbine blades. Mixed stalls can also occur involving two or three of the above types in a mixed sequence. Gault (1957) has given a very useful correlation to predict stall type by analysing the behaviour of a large number of (clean) NACA sections in low turbulence wind‐tunnel tests. But it is clear from the above that the occurrence of dirt or insects on many of these sections can drastically change the stall type. Hence it has been of considerable importance to develop aerofoil sections that are less sensitive to dirt accretion. A further complication of stalling is that since the presence of a large separation region on the aerofoil section changes its suction surface pressure distribution, when the angle of attack of a stalled aerofoil is reduced systematically, reattachment and unstalling do not usually occur at the same angle of attack as separation and stalling did when the angle of attack was being increased. Thus the stall–unstall cycle results in a hysteresis loop with the early post‐stall region exhibiting two possible levels of lift depending on the direction of change in angle of attack.

Because of data availability, a popular range of aerofoil sections for wind turbine blades was, but less so now, the NACA six‐digit series, an example of which is discussed in Section 3.9. Although more tolerant to leading edge roughness, the NACA six‐digit series is no better overall than the NACA four‐digit series described in Appendix A3. The main reason for the popularity of the NACA aerofoils is because high quality experimental data is available from tests that were carried out in the 1930s in the pressurised wind tunnel built by NACA (superseded by NASA in 1959). The NACA technical reports are available free on the NASA website, and much of the force data is given in Theory of Wing Sections by Abbott and von Doenhoff (1959).