The behaviour of a premixed propane flame in three dimensions was studied numerically and experimentally in a jet flow combustor at different equivalence ratio, Reynolds numbers and turbulent intensity. The detailed attract here has come up with data of propane -air mixtures flame propagation over a range of equivalence ratios (e) between 0.6 lean flame to 1.3 rich flame on environmental conditions of temperature and atmospheric pressure. The instantaneous flame was visualized using a high-speed camera on the domain of the burner of 100 mm diameter. From 174 to 472 images were recorded for each experimental test. Flame surface density was obtained from the instantaneous image of the flame. The influence of the flame area density in the evaluation of the flame propagation will be discussed. The study shows that the increase in turbulent intensity leads to increase the turbulent flame propagation speed subsequently increase in flame area density at a constant an equivalence ratio value. Also, it was shown that the wrinkling flame shape is the dominant characteristic leading to the increased turbulence intensity. The research results are expected to be used for developing jet flow combustor burners.
In this study, a numerical and experimental investigation for the flow separation over 170 mm chord, the NREL S822 aerofoil low Reynolds number wind turbine blade aerofoil section has been investigated at 15.8 m/s wind speed using suction and blowing techniques for the locations between 0.15 and 0.41 of the chord to improve aerodynamic characteristics of a wind turbine rotor blade. In a numerical study, two-dimensional aerofoil (i.e. NREL S822), using Shear Stress Transport (SST (γ − Reθ)) turbulence model, is presented. Careful selection for the number of mesh was considered through an iterative process to achieve the optimum mesh number resulted in optimum values for the ratio of lift to drag coefficients (CL/CD). Values of the lift coefficient, drag coefficient, and separation location were investigated at an angle of attack 18°. Flow separation is monitored and predicted within the numerical results at the tested angles, which has been compared with the experimental results and should a fair agreement. The results revealed that the aerodynamic characteristics of NERL S822 aerofoil would be improved using the suction technique more than the suction and blowing techniques and there is a delay of flow separation with the increase of blowing or suction volumetric flow rate. Using these two techniques and careful selection of the mesh numbers with the right angle of attack can improve the aerofoil characteristics and therefore lead to improve the turbine performance characteristics.
The majority of wind turbine models are built to work in areas with high wind speeds. Such turbines would waste a lot of the energy available in low-speed zones. The performance of these turbines should be improved using sophisticated techniques in order to match the locations' available wind energy. Therefore, in the current study, active flow control (AFC) was applied over the NREL S822 profile (small horizontal wind turbine) using blowing/suction techniques to determine where these methods will be most effective. At a constant speed of 15.8 m/s and an angle of attack of 18 deg, blowing and suction techniques have been used either together or individually. The results showed that the use of the NREL S822 aerofoil with AFC enhances the wind turbine performance by an average of 15% compared to using no AFC. It was discovered that the technique at the B3 (x/c = 0.54) slot was the best blowing technique, and the technique at the S1 (x/c = 0.18) slot was the best suction case and the maximum lift-to-drag ratio (C<sub>L</sub>/C<sub>D</sub>) when S1B3 was activated, indicating that S1B3 is the best technique with an 87% improvement rate.
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