Abstract
Abstract. Responses of an axial compressor isolated rotor blade row to various inlet distortions have been investigated utilizing computational fluid dynamic technique. Distortions have been imposed by five screens of different geometries, but with the same blockage ratio. These screens were embedded upstream of the rotor blade row. Flow fields are simulated in detail for compressor design point and near stall conditions. Performance curves for distorted cases are extracted and compared to the undisturbed case. Flow simulations and consequent performance characteristics show that the worst cases belong to non-symmetric blockages, i.e., those of partial circumferential configurations. These cases produce the largest wakes which can disturb the flow, considerably. Superior performances correspond to the inner and outer continuous circumferential distortion screens. Since, they produce no significant disturbances to the main flow in comparison to the non-symmetric screens.
Highlights
Demands on designing gas turbines with high efficiency and stable operation range under various conditions are extensively increasing
Aerodynamic and thermodynamic performances of gas turbines of power stations, aircraft and road vehicles are highly dependent on entrance air flow conditions
Aircraft may be encountered to non-uniformity of the entrance air flow during their manoeuvres
Summary
Demands on designing gas turbines with high efficiency and stable operation range under various conditions are extensively increasing. Static inflow distortion effects on an axial flow fan performance has been numerically studied by Raj and Pandian (2014) They had focused on development of stall cells and consequent losses within the blades passages. Inlet distortion effects on performance of an axial compressor rotor blade row in the presence of casing treatment of circumferential groove type are investigated by Jian and Hu (2008) They concluded that this kind of treatment can expand the compressor rotor operating range either with or without inlet circumferential pressure distortion at the expense of a slight drop in the isentropic efficiency. In the present research work, three dimensional numerical simulation of flow field in an axial compressor rotor blade row is executed for different distorted inlet flows from far to near stall conditions. Performance map and contours of flow properties are extracted from excessive CFD analyses for each inlet distortion case and for the non-distorted case for comparison
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