首页|Investigation of non-uniform leading-edge tubercles in compressor cascade:Based on multi-objective optimization and data mining
Investigation of non-uniform leading-edge tubercles in compressor cascade:Based on multi-objective optimization and data mining
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Corner stall receives noticeable attention in the aeroengine field as an important phenomenon in highly-load compressors.Non-uniform leading-edge tubercles,as an effective method to delay stall,are introduced into the compressor.In this paper,the shape of leading-edge tubercles was controlled by a third-order Fourier function.To judge corner stall,a more precise stall indicator for compressor cascade with flow control methods was defined.Besides,the total kinetic energy of the secondary flow at large inci-dence was adopted as a parameter for stall evaluation to save computing resources.The results of multi-objective optimization reveal that the loss coefficient exhibited negligible variation at design incidence,while the total kinetic energy of secondary flow showed a significant reduction at large incidence,resulting in a substantial increase in stall incidence.In the optimal profiling cases,the stall incidence was delayed from 7.9° to 11.6°.The major purpose of the research is to provide proper design guidelines for non-uniform leading-edge tubercles and uncover the flow control mechanisms of leading-edge profiling.Hence,the geometric features that meet different optimization objectives were extracted through geometric anal-ysis near the Pareto Front and through Self-Organizing Map(SOM)data mining methods in the optimiza-tion database.Besides,flow field analysis reveals the flow control mechanism of leading-edge tubercles.The convex-concave-convex structure at the 0％-70％blade height region can form two branches of leading-edge vortex pairs that are opposite in the rotation direction to the passage vortex.The two branches of leading-edge vortex pairs mixed with the leading-edge separation vortex to form two stronger mixed vortices,which can effectively suppress the development of passage vortex and delay stall incidence.
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