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Master Thesis Report Executive Summary As the demand to improve the fuel efficiency of current commercial aircraft increases, new commer- cial airliner concepts such as the Blended Wing Body has been researched on and studied in various aspects over the years as an efficient alternative to the conventional transport configuration. One particular aspect of the Blended Wing Body is the use of the propulsive fuselage concept. In this concept, the fuselage boundary layer is ingested by the engine and this is aimed at producing benefits such as improved fuel efficiency, reduced ram drag as well as lower structural weight of the engine. During the ingestion process, the low momentum boundary layer is re-energized by the propulsion system before exiting into the atmosphere. In this way, the ingested flow does not contribute to the wake deficit and hence, the overall drag of the aircraft is reduced. Since thrust equal drag in steady and level flight, and power is equal to thrust multiplied by velocity, the reduction in drag implies a reduction in the power required to drive the vehicle. In essence, the ingestion of the boundary layer which leads to a lower inlet stagnation pressure rep- resents a direct thermodynamic penalty. However, the momentum deficit captured by the engine represents a drag reduction to the aircraft. In this way, the propulsion system performance suffers a decrease in engine efficiency while the aircraft drag is reduced in proportion to the amount of boundary layer flow that is ingested. Therefore, a trade-off exists between the increase in aircraft drag reduction and the decrease in engine performance as more boundary layer is consumed. Another important concern is the significant flow distortion which can lead to increased vibration and fatigue of the fan and compressor blades in particular. This flow distortion is characterised by the distortion coefficient, a standard widely used in the aircraft engine industry. While it was found that the ingestion of the boundary layer can provide a decrease in fuel burn of several percentages, the benefits of boundary layer ingestion have shown to be very sensitive to the magnitude of the fan and duct losses. Hence, it is crucial that fan designers are able to design new rotor blades that are able to withstand theses flow distortion while ensuring that engine performance degradation is kept to a minimum in order to maximise the overall gain in fuel efficiency. The main aim of this research is therefore to understand and analyse the rotor performances un- der both uniform and non uniform inflow condition. This will then provide insights into the main fluid mechanism affecting rotor performances under such conditions. As such, the early phase of this research was focused on the development of an in-house blade modeller which was then later used in the parametrisation and reconstruction of the NASA Rotor 67. Other than the development of the Blade Modeller, this research was also focused on the coupling of an open-source meshing software, SALOME to the Blade modeller which will then allow the user to achieve automated meshing needed for the design optimization process. A literature study was carried out in order to understand the effect of boundary layer ingestion on inlet performance and subsequently its influences on rotor performance. Extensive literature was found which characterized and analyse the influence of boundary layer ingestion on the engine perfor- IPDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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