Appropriate tip clearance flow can improve the flow in the tip region.
适量的间隙流动有利于改善通道顶部区域流动。
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。
Finally a scheme of engine's tip clearance measurement by capacitance method is given.
提出了电容法测量发动机叶尖间隙的方案。
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。
The effects of tip clearance on duct propeller's performance were investigated in six different tip clearances.
选择六种不同的叶梢间隙研究叶梢间隙对导管桨性能的影响。
The result indicates that with the increase of tip clearance size, the performance of fan stage changes obviously.
计算结果表明，随着动叶叶顶间隙的增加，风扇性能变化显著。
The numerical result shows increasing the tip clearance will reduce hydrostatic head, especially at small flow rate.
数值结果表明，间隙增加，扬程下降，特别是越在小流量工况下越明显。
The results showed that the main flow rolled up the leakage flow of the tip clearance and generated the tip leakage vortex.
结果表明：叶顶间隙气流与主流发生卷吸而生成泄漏涡。
Tip clearance numerical analysis is an important content of studying tip clearance control and improving engine performance.
叶尖间隙分析是研究叶尖间隙控制方法，改善发动机性能的重要内容。
The computed conclusion show that the magnitude of tip clearance has close relationship with the intension of tip leakage flow.
根据所测量得到的三维速度，清楚地展现了转子顶部流动的特性，特别是泄漏流对顶部流动的影响。
The influence of tip clearance on the performance of fan rotor has been investigated by numerical method at different clearances.
在不同叶尖间隙下，对高负荷风扇转子的特性进行了研究；通过数值方法分析了叶尖间隙对转子特性的影响。
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；
Downstream rotor-stator interaction increases the unsteady fluctuating intensities of the rotor tip clearance flow and the tip leakage loss.
下游静叶干涉增加了动叶顶部间隙流的非定常波动强度和泄漏损失。
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。
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。
The influence of tip clearance on overall performance and detailed flow structure in tip region of an axial compressor rotor was investigated.
研究了顶部间隙对压气机转子总性能及内部流场的影响。
The high pressure turbine tip clearance variation versus time under different operating conditions were analyzed by the finite element method.
利用有限元分析软件分析了某型高压涡轮叶顶间隙在不同工况下随时间的变化。
This article investigates the nonlinear dynamic characteristics and stability of an axial flow compressor with tip clearance and ball bearings.
研究叶尖气隙和滚动轴承共同作用下轴流压缩机的非线性动力特性及稳定性。
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。
Research finding about the tip clearance of engine in the paper is basal; they can be used as reference of aero-engine design and the tip clearance control.
这些工作对于发动机初步设计设计和叶尖间隙控制理论研究有一定的参考价值。
The new parameter representing the nonuniformity of tip clearance is recommended, and the modeling approach for the nonaxisymmetry compressor is introduced.
首先介绍了表征机匣变形程度的新参数，进而引进了非轴对称压气机模型的建模方法。
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。
The 3d viscous code had been developed to calculate flow field in rotor with tip clearance by solving three-dimensional Navier-Stokes equation with time-marching method.
采用时间推进法求解三维n - S方程，开发了一种用于计算考虑顶部间隙的压气机转子内部流场的三维粘性程序。
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。
However, the detailed transient flow field, the originating mechanism and the potential application of unsteady tip clearance flow are unclear or not enough understood to date.
然而到目前为止，这种非定常波动的基本流动特征，形成机理及其潜在的应用前景都不够清楚。
Recently, the unsteady characteristics of tip clearance flow, which appears in some flow conditions, was discovered and its influence to the compressor performance was recognized.
近年来，人们发现压气机叶顶间隙流并非始终处于定常状态，在某些流动条件下，它会产生明显的非定常波动，并影响压气机的总性能。
Numerical methods were utilized to investigate the time-dependent flow patterns and the frequency characteristics of unsteady tip clearance flow in an axial-flow low-speed isolated compressor rotor.
利用数值方法研究了某低速轴流孤立压气机转子中非定常叶顶间隙流的流动特征和频率特性。
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。
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。
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。
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