| Summary: | 碩士 === 國立成功大學 === 航空太空工程學系碩博士班 === 90 === The main purpose of the present study is to investigate in depth, using computational fluid dynamics (CFD) method, the complex three-dimensional flow field associate with the tip clearance of an axial compressor. The influence of tip clearance on compressor performance is discussed. The CFD method employed is based on CFX-TASCflow, which is a finite volume based method solving Reynolds averaged Navier-Stokes equations. The Compressor model under study is based on the same configuration and operating condition used in the experimental work done by Inoue and Kuroumaru. The comparison with experimental data indicates that the present calculation predicts tip clearance flow with good accuracy. It further provides good simulations of three-dimensional leakage jet flow, leakage vortex, and passage secondary vortex flow. With large tip clearance, the leakage vortex is stronger and with greater energy loss. This is consistent with the theory developed by other researchers earlier. The understanding of tip clearance loss mechanism is useful to the compressor design improvement.
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