| Summary: | 碩士 === 中華工學院 === 航空太空工程研究所 === 85 === With the tip gap vortex, the tip leakage flow which
pass through the clearance between the compressor rotor blade
tip and casing shroud is important to influence the
rotor efficiency, pressure rise and rotorary map. This paper,
using Jameson cell-centered scheme, based on 3-D Euler and
Navier-Stokes equations and constructed turbulence model, is to
solve the rotor tip clearance flow field of 3-D axial air
compressor. The Euler analysis is shown that the pressure ratio
of the tip gap 0% blade chord (=1.402 ) is higher than the tip
gap 3% and 19% blade chord (= 1.34~1.39 ), while the efficinecy
of the tip gap 0% blade chord(η= 0.908% ) is smaller than the
tip gap 3% and 19% blade chord(η= 0.91~0.92% ). The Navier-
Stokes analysis is shown that the pressure ratio of the tip gap
0% blade chord (=1.312 ) is smaller than the tip gap 19% blade
chord (=1.352 ), while the efficiency of the tip gap 0% and 19%
blade chord almost equal each other(η= 0.9~0.903% ).
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