Computational study of the effect of sweep on the performance and flow field in an axial flow compressor rotor

• Published in: Proceedings of the Institution of Mechanical Engineers. Part A, Journal of power and energy Journal of power and energy, 2007-05, Vol.221 (3), p.315-329
• Main Authors: Govardhan, M, Kumar, O. G Krishna, Sitaram, N
• Format: Article
• Language: English
• Subjects: Axial flow; Boundary layer; Boundary layer flow; Compressor rotors; Compressors; Deflection; Dimensional analysis; Flow control; Mechanical engineering; Pressure; Stalling; Suction; Three dimensional flow; Turbocompressors; Turbulent flow
• ISSN: 0957-6509; 2041-2967
• DOI: 10.1243/09576509JPE374

Abstract In the recent past, experimental studies have shown some advantages of blade lean and sweep in axial compressors. As most of the experimental results are combined with other features, it is difficult to determine the effect of individual parameters on the performance of the compressor. The present numerical studies are aimed at understanding the performance and three-dimensional flow pattern within and at the exit of swept and unswept rotors. Three rotors, namely, unswept, 20° forward swept, and 20° backward swept rotors, are analysed with a specific intention of understanding the three-dimensional flow pattern within the rotors and also the pattern of the blade boundary layer flow. The analysis was done using a fully three-dimensional viscous CFD code CFX-5. Results indicated a reduction in pressure rise with sweep. Backward sweep adversely affects the stall margin. Forward sweep changes the streamline pattern in such a way that the suction surface streamlines are deflected towards the hub and the pressure surface streamlines are deflected towards the casing. An opposite behaviour is observed in the backward swept rotors. High axial velocities reduce the secondary losses near the hub, resulting in a high pressure rise in forward swept rotor.