Turbine blade cooling techniques have been around for many years, and the addition of coolant into the turbine blade section will remain to be a viable cooling option for many years to come. Film cooling, which will be the main subject of this research, is a form of convection cooling where holes are placed through the surface of the metal components. With the addition of this film coolant into the main flow, an increased amount of total pressure loss will be found downstream. This is caused by the difference of flow momentum of the coolant and main flow when the two fluids are mixed. The test rig used for the upcoming research will be the NASA-designed E3 rig. E3, standing for Energy Efficient Engine, was established to develop technology for improving the energy efficiency of future commercial transport aircraft engines. These engines were designed to provide real-world, actual test configurations in order to produce more efficient turbine engines, mainly to be used for propulsion. Tests were not focused just on heat transfer as its use will be, but with all aspects of the engine's components, especially aero. The annular cascade with 3-dimensional blade profiles as well as high Reynolds numbers make this setup an accurate test bed in which actual turbine conditions can be compared to. The focus of this research is on the increased amount of total pressure loss seen downstream in an annular cascade with 3D blade profiles with the addition of inner endwall film cooling in a high-speed setting. Also, the rig setup of closed vs. open-loop and its effect on the inlet conditions as well as total pressure loss will be investigated.

This master thesis is focused on design and aerodynamic analysis of subsonic turbine engine inlet in NACA duct configuration for unmanned aircraft. The first part of this paper is methodics for design considerations for NACA duct, which is based on theoretical analysis of this type of inlet. The acquired knowledge is used to design an inlet for the specified unmanned aircraft that is subject of CFD analysis. The impact of deflectors is considered in the evaluation and the solution is compared to the S-duct inlet. The proposed inlet with deflectors meets DC60 distortion criterion for all specified cases and the pressure losses requirements are met for lower velocities. Based on the results, the recommended application is for aircraft that flies in optimal design conditions for most of the mission.

This master thesis deals with design of a subsonic intake which is used to supply small jet engine integrate into the fuselage of agile small unmanned aerial vehicle (UAV). Some kinds of these intakes are listed in order to inspire and introduce future designers into this part of jet plane design. This thesis contains a small amount of theory about compressible flow, and necessary knowledge which are important to know before the very first attempt to design an intake. Two models were designed in order to prove that the theory listed in this thesis is useful and can be used as a guide in design process of subsonic intakes. Both designs have the same layout. S-duct design with one intake placed on the belly of fuselage was chosen. After CFD analysis of first model it was found that there are huge area with separated flow and vortex. Separated flow leads to big total pressure loss and pressure distortion. While designing the second model the emphasis was to avoid this vortex and improve flow conditions. This optimization was success and the second design have smaller pressure loss in compare to the first design. The difference is more than 50% at fly speed M=0,8.

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