IGTC-11 A Measurement of Three-Dimensional Flow at the Exit of an Axial Compressor Rotor Passage(Session A-4 THREE DIMENSIONAL FLOW II)
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概要
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This paper presents an experimental investigation of the three-dimensional flow at the exit of an axial flow compressor rotor passage using a single slant hot-wire. The results indicate, a strong vortex exits at the corner of the hub and the suction surface, which prompts the loss generation nearby. A tip leakage vortex exists at the median part of the blade passage in design condition. In near stall condition, flow mixing among the leakage flow, the thickened casing boundary layer and the developed suction surface boundary layer leads to the large loss and blockage at the tip ; flow separations of the boundary layer on the suction surface occur at 0.2 span and 0.8 span.
- 公益社団法人日本ガスタービン学会の論文
著者
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Jiang H.
Beijing University Of Aeronautics And Astronautics
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Ma H.
404 Group, Beijing University of Aeronautics and Astronautics
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Jiang H.
404 Group, Beijing University of Aeronautics and Astronautics
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Li Y.
404 Group, Beijing University of Aeronautics and Astronautics
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Ma H.
Beijing University of Aeronautics and Astronautics
関連論文
- IGTC-11 A Measurement of Three-Dimensional Flow at the Exit of an Axial Compressor Rotor Passage(Session A-4 THREE DIMENSIONAL FLOW II)
- IGTC-119 A Measurement of Three-Dimensional Flow Field in the Tip Region of a Compressor Rotor Passage in Near Stall Condition(Organized Session III TIP CLEARANCE FLOW)