Effect of corner modifications on aeroelastic instabilities of tall buildings
Effect of corner modifications on aeroelastic instabilities of tall buildings
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DOI：
10.1016/s0167-6105(98)00065-8
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发表时间：
1998-04-01
影响因子：
4.8
通讯作者：
Kawai, H
中科院分区：
文献类型：
--
作者：
Kawai, H
通过方柱和直角方柱的风洞试验，研究了切角、后角和圆度对涡激和驰振等气动弹性不稳定性的影响。根据试验，获得了以下结果。小的切角和后移可以有效地增加气动力阻尼，防止方柱体的气动弹性失稳，但当阻尼足够小时，大的切角和后移会促进低速时的失稳，从而降低失稳的起始速度。角部圆化也能有效地增加气动阻尼以抑制不稳定性。浅埋矩形棱柱体发生低速驰振失稳。在低速时，角部的修正阻止了涡的脱落，从而增加了不稳定性。深埋矩形棱柱体存在运动诱导振动，且角部变形对运动诱导振动影响不大。(C)1998由Elsevier Science Ltd.出版。保留所有权利。
Effects of corner cut, recession and roundness on aeroelastic instabilities such as vortex induced excitation and galloping oscillation were investigated by wind tunnel tests for square and rectangular prisms. According to the tests, the following results were obtained. Small corner cut and recession are very effective to prevent aeroelastic instability for a square prism by increasing the aerodynamic damping, but large corner cut and recession promote the instability at low velocity to reduce the onset velocity of the instability when the damping is small enough. Corner roundness is also effective to increase the aerodynamic damping to suppress the instability. Low-speed galloping type instability occurs for a shallow depth rectangular prism. The corner modifications promote the instability at low speed, because the vortex shedding is prevented by the modifications. The motion induced vibration occurs for a deep depth rectangular prism, and it is little affected by the corner modifications. (C) 1998 Published by Elsevier Science Ltd. All rights reserved.