指出了目前离心泵叶片出口角研究存在的不足。
The present deficiency about numerical simulation research on impeller outlet Angle of centrifugal pumps is pointed out.
本文研究了离心叶轮内的流动及不同叶片出口角对离心泵性能的影响。
This paper studies the influence of flow in centrifugal impeller and outlet blade angle on the performance of centrifugal pumps.
模拟结果表明，叶片出口端部前缘，温度达到最大，颗粒的运动速度也达到最大值。
The results of this simulation showed that the maximum temperature appears at the tip of the blade. And the particle velocity will reach the maximum value at the end of the blade finally.
这种方法有效地解决了调节转轮叶片出口角度的困难，能较快的设计出性能良好的转轮。
This approach effectively solved the problem of runner blade Angle adjustment and is able to rapidly design runner blades with good performance.
借助于分离参考点的位置坐标，通过改变叶片形状系数，能有效地使分离参考点移向叶片出口端。
Having the aid of position coordinate of reference separation point, the point can be moved to outlet of vane by changing coefficient of vane shape.
因此在高压导叶设计中 ，当采用低展弦比叶片时 ，应注意削弱叶片出口附近流场的严重径向窜流。
Therefore when using low aspect ratio blade during the design of high pressure guide vane, attention should be made in order to obstruct the …
本文作者定量分析计算由转轮有限叶片数引起的叶片出口相对速度分布状态，并以所获结果提出了改善叶片设计的措施。
The author of this paper analyzes and calculates the relative velocity distribution at the blade exit of runner caused by limited blades and offers the way to improve blade design.
若分离参考点接近于出口端，则可获得满意的测试结果，这说明边界层实际分离点的位置已经很接近于叶片的出口端。
If the reference separation point approaches the outlet, the test results are satisfactory, which state that the practical position of boundary layer separation point will be close to the outlet.
通过改变叶片数和出口安装角构造扩压器，进行CFD分析，建立样本数据。
Through changing vane number and exit installation Angle to construct candidate diffusers which are analyzed by CFD, sample data is then setup.
此外上游静子尾迹以及动叶尾缘出口膨胀波等也是产生转子叶片表面非定常力的因素。
In addition, the wake interaction of upstream blade row and the expansion wave at rotor exit also cause an unsteady force acting on the downstream rotor blade surface.
结果表明，从叶道的进口到出口，轴流通风机叶片对气流的作用是一个渐变的能量传递过程。
The result is that from inlet to outlet of the blade channel, Axial fan blade effected on air flow is a gradually changed process of energy transmitting.
利用电阻应变片、动态压力传感器、滑环式引电器和磁带记录仪等，录取叶片振动应变和动叶出口压力信号，然后回放磁带，做信号处理。
Using resistance strain gage, dynamic pressure sensor, slip ring and tape recorder, the blade vibration strain and exit pressure signals of rotor blades are recorded and then processed.
讨论了冲角、叶片弯曲角和出口条件对叶片正弯曲作用的影响。
The influence of incidence Angle, blade's flexure Angle and exit conditions on the effect of positive blade flexure is discussed.
实验并且采用考虑粘性的涡传输方程计算端弯压气机叶片通道出口二次流。
The outlet secondary flows in compressor cascades with end-bend blades have been studied experimentally and numerically. The viscous secondary vorticity equations are applied to prediction.
实验结果表明：采用最佳倾斜角叶片能降低叶栅能量损失和改善叶栅出口流场的气动性能。
Experimental results show that by using an optimal Angle of inclination energy losses can be reduced and outlet flow fields improved.
在相同叶轮出口速度下，叶片扩压器比无叶扩压器中气流速度下降迅速，叶轮出口处平均流场趋于均匀。
Under the same impeller outlet speed, the flow speed of blade diffuser is faster than the vaneless one. The average flow field at impeller outlet trends to uniform.
实验结果表明，采用非光滑叶片改变了叶栅出口旋涡结构及流动分布，使叶栅出口的流场趋于均匀，叶片可以随更大的负荷。
The experiment results show that using non-smooth blades can change the exit streamwise vortex structures. The exit flow fields tend to well-distributed. The overall blade losses are reduced.
分析在不同叶片安装角下，叶片表面静压系数、出口总压损失系数和出口气流角的变化规律。
The static pressure loss coefficients, total pressure loss coefficients and flow outlet Angle distribution are simulated in conditions of different setting angles.
由测量结果可知：在双叶片叶轮内，流体基本沿叶片吸力面流动，叶片压力面上的相对速度较低，在压力面出口出现了速度很低的回流区，有明显“射流-尾迹”特征。
The results indicated that in the two-blade impeller, the fluid mainly flowed along the suction side, the velocity is very small on the pressure side, and a typical jet-wake flow has been observed.
由测量结果可知：在双叶片叶轮内，流体基本沿叶片吸力面流动，叶片压力面上的相对速度较低，在压力面出口出现了速度很低的回流区，有明显“射流-尾迹”特征。
The results indicated that in the two-blade impeller, the fluid mainly flowed along the suction side, the velocity is very small on the pressure side, and a typical jet-wake flow has been observed.
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