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Master Thesis Report Literature Review After the blade profiles are stacked accordingly, the next step is to generate B-Spline surfaces for the pressure/suction side as well as the LE/TE edges. The generation of the B-Spline surfaces de- pends on a number of parameters. They are the degree, multiplicities as well as the knots. They control the continuity of the span-wise surface as well as the accuracy with which the surface approxi- mates the individual control profile. A selection of higher degree leads to a higher continuity but lower accuracy. Intermediate profiles are constructed based on interpolation using the generated span-wise distribution of the various design parameters (blade inlet/outlet metal angles, stagger angle, leading edge position, axial chord, thickness distribution, etc). For any typical turbomachinery blade, the hub and tip control profiles may be flared. Flaring is defined as the inclination of the blade profile with respect to a certain reference axis. In the case of the NASA Rotor 67, the control profiles at the hub and tip location are flared with respect to the axial direction (x-axis). Flaring is controlled in the Blade Modeller using a 2D meridional channel. 2.3.2 Performance characterisation of Turbomachinery Cascade Firstly, a short description of the various loss mechanisms and flow phenomenon that initiate these losses in turbomachinery cascade will be explained. Then, the parameters used to characterize the performance of turbomachinery cascade will be described in detail. Loss Mechanism A review of the most common type of losses are presented below: • Profile Losses: The profile loss consists of a combination of the wall shear stress losses and the trailing edge mixing losses. Since both losses can hardly be separated in experimental results, they are often combined under the term known as the profile losses. Wall shear stress losses originate in the boundary layer. Trailing edge mixing losses occur when the boundary layer mixes with the free stream. These losses can be minimised by increasing the surface quality and decreasing the trailing edge radius. However, there are manufacturing limitations to both solutions. • Shock Losses: Shock losses can occur especially in fans that operate in transonic flow field. It contributes greatly to the overall entropy rise and has the same order of magnitude of losses as that of the profile loss. • EndWall/Secondary Losses Secondary losses are generated by the build up of the endwall boundary layer, secondary flow as well as the tip clearance. Secondary flow can be described as flow that flows at right angle to the intended primary flow. They are mostly caused by a pressure gradient that is generated between the pressure and suction side of two adjacent blades within a flow channel. This pressure gradient is a function of the blade loading present on each blade. A positive pressure gradient gives rise to an increase in the boundary layer thickness. Secondary flow generates vibration, noise and flutter because of the unsteady pressure field between the blades and the rotor-stator interaction. • Tip Leakage Flow Losses: Tip leakage losses are generated as result of fluid flowing from the pressure side to the suction side of the blade. This occurs because of the gap that is present between the annulus wall and the blade. This leakage flow induces three dimensionality effects such as the formation of vortices. 19PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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