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3.3 Aerodynamic design The aerodynamic design can commence when the flow properties are defined from the thermodynamic analysis. In this process, the dimensions, pressure losses, efficiencies, and other aerodynamic parameters for the different components can be determined and evaluated. 3.3.1 Software description MATLAB is a widely used numerical computing environment and programming language suitable for a range of applications. Its ability to read data from external sources, built in functions, advanced plotting functions and extensive documentation made it an appropriate choice for this project [17]. 3.3.2 Turbomachinery The initial turbomachinery sizing requires a few assumptions from the designer in order to proceed with further analysis of the component. Based on these assumptions together with the fluid properties from the thermodynamic analysis the areas, rotational speeds, blade speeds, number of stages, stage loading etc. can be determined. The initial sizing procedure can be found in [18], where guidelines for initial assumptions of the necessary parameters are also given. With the initial sizing procedure done, the parameters described in the following sections can be evaluated, and the turbomachinery properties can be modified to assure adequate performance. 3.3.2.1 Velocity triangles In order to design the blades, the power input per stage needs to be related to velocity triangles. These give an indication of how the blades change from the hub to the tip by showing the variations in velocity. The velocity triangles for a typical stage at the mean radius can be seen in figure 4. The fluid approaches the rotor with an absolute velocity of πΆ1 at an angle πΌ1 relative to the axial direction. By combining πΆ1 vectorially with the blade speed U, the velocity relative to the blade π1 at an angle π½1 relative to the axial direction can be found. As the flow passes through the rotor, the absolute velocity of the fluid increases leaving the rotor with a velocity π2 at an angle π½2. With the axial velocity πΆπ1 constant over the stage, π2 can be found and the outlet velocity triangle constructed by combining π2 and U vectorially to give πΆ2 at the angle πΌ2. The fluid then passes to the stator where itβs diffused to a velocity πΆ3 at an angle πΌ3. Generally πΌ3 approximately equals πΌ1 and πΆ3 approximately equals πΆ1 so that the fluid is prepared for entry into another similar stage [19]. 21PDF Image | Conceptual Design of a Supersonic Jet Engine
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