Nonlinear Analysis of Rotating Stall
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概要
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A new stall model to describe rotating stall in axial flow compressors is established, where blade rows are replaced by semi-actuator discs (finite chord and infinitesimal pitch), flow fluctuations are permitted to be finite and nonsteady, and cascade characteristics are taken into consideration in both nonlinear and nonsteady forms. Through numerical analysis adopting finite difference method, it is tried to make clear the aspects of rotating stall-such as the number of stall cells, the amplitude and the wave shape of disturbance, the stall propagation velocity, and their variations with flow rate through the compressor-and the mechanisms for establishing them, which are not yet known by the usual linear theories. The numerical analysis is applied to both isolated (two dimensional or three dimensional) blade row and multi-blade rows (with infinitesimal or finite axial distance). It is shown that the effects of the dynamic response of the blade row (the effects of the time delays due to both the behavior of the blade boundary layer and the inertia of the fiuid in the blade passage) and the three dimensionality of the blade row have little connection with the determining mechanism of the number of stall cells. And the interference between adjacent blade rows is proved to have the effect to determine the number of stall cells. The stall patterns generated in a compressor and their change with the throttling of the compressor are also shown to be controlled by the interference effects between blade rows. And finally all the aspects of rotating stall observed in common compressors are exemplified numerically using a model of the present analysis.
- 宇宙航空研究開発機構の論文
著者
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Takata Hiroyuki
Department Of Aeronautics University Of Tokyo:institute Of Space And Aeronautical Science University
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Takata Hiroyuki
Deparoment Of Production Engineering School Of Engineering
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NAGANO Saburo
Department of Aeronautics, University of Tokyo
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Nagano Saburo
Department Of Aeronautics University Of Tokyo
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