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Master Thesis Report Literature Review Other than these major classification of losses in turbomachinery, it is prudent to look into the various mechanisms that initiate these losses. The two main flow phenomenon concerned are separation and flow deviation. • Separation: Separation is characterized by the flow completely detaching from the blade profile. Prior to separation, the boundary layer grows very thick. At the onset of the separation bubble, the fluid particles located at the wall has no velocity relative to the blade. In the bubble itself, the fluid is turned to flow in the opposite direction due to the adverse pressure gradient, leading to an area of recirculation. Separation can occur in various area of the blade, although it most commonly occurs on the aft suction side of the blade. Other than the usual separation at the trailing edge of the airfoil, leading edge separation is another uncommon but localised phenomenon. It can occur after an excessive high suction peak on the suction side of the airfoil or an incorrect blade metal inlet angle onto the pressure side of the airfoil. In the case of the suction side, the flow tends to reattach mainly because of the strong acceleration on the suction side. On the pressure side, such a separation will lead to an extensive re-circulation zone. Separation in transonic fan is promoted by the shock boundary layer interaction due to high pressure gradient across the shockwave. Detailed analysis reveals a significant growth of the boundary layer in the shock region. If the shock is strong enough, separation can occur. • Flow Deviation: Flow deviation represents the discrepancies in angle between the inlet/outlet flow and its respective blade metal angle. However, deviation is not easy to predict by analytical expression. As the incidence angle increases, the flow over the blade deteriorates until the point of stall. It is possible to achieve un-disturbed flow over the blade with zero degree incidences when operating at design rotation speed. An illustration of some of the loss mechanisms described earlier is shown in figure 2.20, 2.21 and 2.22. Figure 2.20: End wall losses [9] Figure 2.21: Secondary flow losses [9] After a discussion on the various loss mechanism, the next part of this subsection will describe the various parameters that characterise the performance of turbomachinery cascade. Other than that, the distortion coefficient parameter that is used to characterised flow distortion will be explained as well. Characterization of Turbomachinery Performance An important performance parameter that is used to characterise the loss in turbomachinery rotor is known as the stagnation pressure loss coefficient. It is defined as shown in equation 2.45. It is 20PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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