The gas exciting force caused by blade tip clearance may cause rotors unsteady under certain condition.
转子偏心引起的气流激振力在一定条件下可能诱发转子失稳。
This paper also presents the experimental results of effects of the blade tip clearance and the airfoil shape on the stall flutter boundary.
此外还给出了两种叶尖间隙和两种叶型对失速颤振影响的实验结果。
Finally, an important combination parameter was put forward to reflect the overall influence of blade loading and tip clearance distribution on the tip leakage mixing loss.
最后提出一个重要的组合参数，反映了叶片尖部载荷和叶尖间隙的流向分布对叶尖泄漏掺混损失的综合影响。
The paper introduced typical structure of the close clearance seals for blade tip seals in modern aero-turbine and the research progress of gas film seal for gas turbine.
本文介绍航空燃气轮机转子叶尖“紧间隙”密封的典型结构型式现状，转子内流系统应用气膜密封的有关研究进展。
Suppressed by the up passage vortex at upstream side of blade, the intensity and scale of the tip clearance leakage vortex is decreased.
渐缩型间隙在叶片前半轴弦受到上通道涡的抑制，减少了叶顶间隙泄漏涡的强度和范围；
The influence of blade number, blade thickness, location of splitter blades and tip clearance on mass flow, pressure ratio and efficiency is showed.
讨论了改变叶片数目，增加叶片厚度，调整分流叶片周向位置以及增加间隙高度等对离心叶轮流量、压比和效率等总体性能的影响。
The efficiency of pump will be reduce with the increase of tip clearance of blade.
泵的效率随轮缘处间隙变大会有明显减小。
The calculation method for radial clearance of turbine blade tip considering the effect of temperature and rotational speed is developed in this paper.
给出了考虑温度和转速影响的涡轮叶尖径向间隙的分析计算方法。
There are flow separations at the front blade of bulge tip clearance. The high speed area of groove tip clearance increases the secondary flow loss dramatically.
凸型间隙在叶片前缘引起了流动分离，凹型间隙存在一高速区，增加了二次流损失。
Tip clearance flow in a radial inflow turbine rotor blade under stage environment was investigated by 3-dimensional viscous flow simulation.
对微型燃机向心透平叶轮顶部间隙流动在级环境下进行了全三维粘性数值模拟。
Tip clearance flow in a radial inflow turbine rotor blade under stage environment was investigated by 3-dimensional viscous flow simulation.
对微型燃机向心透平叶轮顶部间隙流动在级环境下进行了全三维粘性数值模拟。
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