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Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow

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Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow ( aerodynamic-design-nasa-rotor-67-non-uniform-inflow )

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Master Thesis Report Literature Review 2.3 Blade Parameterization, Construction and Performance Char- acterization After introducing the concept of boundary layer ingestion and analysing the influence of BLI on engine design and cycle performance, this section of the report will present a brief introduction on the parametrisation and construction of axial blades (used in the Blade Modeller) as well as the parameters used to characterise the performance of turbomachinery cascade. 2.3.1 2D and 3D Axial Blade Parameterization and Construction The parameterisation of a complex 3D axial blade such as the NASA Rotor 67 starts from the parametrisation of a 2D Profile. After the construction of 2D profiles at various span positions, the profiles are then stacked together to form a 3D blade shape. Depending on the type of stacking distribution, the blade can be shaped to have lean, sweep or both characteristics. An illustration of the commonly used definition for blade profile geometry is shown in figure 2.12. Figure 2.12: Definitions used in characterising 2D Blade Profile Blade parameterization is an important design tool to be applied in blade optimization. The prudent selection of relevant geometry parameters is one of the most critical aspects of any shape optimization procedures [8]. A good choice of the selected parameters and its range should allow the blade shape to be described accurately. However, the total number of parameters as well as the range of each individual parameter needs to be limited in order to reduce the search space. Simplifications should be applied to the optimization problem by omitting parameters that have little or no impact on 15

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