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中文摘要：
有三种不同尖端清理尺寸的尖端清理流动的摇摆数字地在这篇论文被调查。NASA 转子 67 被选择为计算模型。尖端清理的尺寸什么时候等于，被发现在所有模仿的案例之中，摇摆存在或比设计尖端清理尺寸大。相对全部的压力系数轮廓显示由尖端漏流动的影响的那个区域以固定集体流动率随尖端清理尺寸的增加扩充。在转子尖端区域的静态的压力分发的根吝啬的方形的轮廓被提供为设计尖端清理(1.1%尖端弦)说明那最强壮的波动 区域在前缘附近位于片的压力方面，当时为更大的尖端清理(2.2%尖端弦)，它在在冲击波和尖端漏流动之间的相互作用的区域。
英文摘要：
Unsteadiness of tip clearance flow with three different tip clearance sizes is numerically investigated in this paper. NASA Rotor 67 is chosen as the computational model. It is found that among all the simulated cases, the un- steadiness exists when the size of the tip clearance is equal to or larger than design tip clearance size. The relative total pressure coefficient contours indicate that region of influence by tip leakage flow augments with the increase of tip clearance size at a fixed mass flow rate. Root Mean Square contours of static pressure distribution in the rotor tip region are provided to illustrate that for design tip clearance （1.1% tip chord） the strongest fluctuating region is located on pressure side of blade near leading edge, while for the larger tip clearance （2.2% tip chord）, it is in the region of the interaction between the shock wave and the tip leakage flow.
同期刊论文项目
同项目期刊论文
Numerical Investigation on the Self-Induced Unsteadiness in Tip Leakage Flow for a Transonic Fan Rot
The Role of Tip Leakage Flow in Triggering Rotating Stall of a Low Speed Compressor under Inlet Dist
A new model for the prediction of turbofan noise with the effect of locally and non-locally reacting
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