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Master Thesis Report mance as a whole but very few literatures were found which pry into the detailed fluid mechanism of boundary layer ingestion influencing the rotor performance. Detailed analysis of the blade to blade domain under non uniform inflow condition were not found. Therefore, the main highlight of this thesis will be on the detailed analysis of the blade to blade domain as well as the overall rotor perfor- mance under non uniform inflow condition. The framework of this report is as follows; The first part of the report will focus on blade parametri- sation as well as the process of blade reconstruction. This is followed by the procedures and approach taken to carry out the simulations using the open source Computational Fluid Dynamics (CFD) Tools, SU2. The CFD simulations and analyses conducted in this thesis are divided into two main stages. The first stage will deal with the computational analysis of the 2D fitted profiles in order to validate the profile fitting process. The second stage will deal with the comparison of the 3D simulation results under both uniform and non-uniform inflow. From the 2D results, it was found that the 2D fitted and Actual point coordinate sources of profile 1265 and 1865 have the closest fit in terms of blade loading, Mach/Pressure Contour as well as their stagnation pressure loss results. However, in the case of profile 2265 and 1565, it was found that the 2d fitted and surface fitted profile have the closest fit in terms of their blade loading, Mach/Pressure Contour and stagnation pressure loss results. Therefore, this result suggests that it is difficult to pinpoint a particular source of error for the blade fitting procedures. However, it can be seen that minor deviation in the leading/trailing edge position and curvature of the blade profile can bring about a significant shift in the shockwave position. It can also be concluded that the BSpline surface generation algorithm gives a better fit to the 2d fitted profiles closer to the tip radius than the hub radius. It should be pointed out that the current blade geometry was generated based on a previous version of the Blade Modeller using a different technique for the generation of BSpline surfaces as well as the flaring angle. The conclusion made from this results are based on the older version of the Blade Modeller. The 3D simulation results composed of two parts. The first part of this result will looks into the comparison of results between the case of a uniform and non uniform inflow boundary condition. It was found that the effect of the non uniform inflow is an increase in entropy production and a decrease in isentropic efficiency. The decrease in efficiency is mainly a result of the change in inlet incidence angle as the inlet total pressure varies. Consequently, this has an effect on the blade loading, shock position as well as the trailing edge wake pattern. For the comparison of the results between the case of a rotor with casing and without casing under uniform inflow, it was found that the case of the rotor without casing exhibits a reduction in isentropic efficiency. This is mainly because of the increased tip leakage losses as compared to the case of a rotor with casing. However, it is noted that the pressure ratio over the unducted rotor is slightly higher as compared to the ducted rotor. In this simulation, the total duct length is relatively short and therefore the pressure induced by the shroud does not significantly add to the total pressure ratio. As described above, the variation in the inlet total pressure along the span direction leads to an increase/decrease in the inlet incidence angle. In order to improve the efficiency of the compressor/fan blade, adjustment to the blade profile can be made in term of the inlet blade metal or stagger angle. However, the change in the inlet blade metal angle influences the enthalpy/pressure change across the blade profile and consequently the thermodynamic properties of the engine cycle. Therefore, it is not recommended to change this angle if possible. Implementing changes to the stagger angle is a possibility. Follow up studies on the numerical optimization of the optimal stagger angle at each span position is necessary. IIPDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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