给出了一个计算亚、跨音涡轮叶栅叶型损失的数值计算方法。
A new numerical method for predicting the profile loss of turbine blades in subsonic and supersonic flows is presented.
为论证方法的有效性，给出了几个跨音速涡轮叶栅的计算结果。
Several computed results of transonic turbine cascades are presented to illustrate the method's capabilities.
详细测量了平行进口端壁附面层与设前导叶两种进口条件下某涡轮叶栅的出口流场。
The exit flow fields of a turbine cascade with or without the front guide vanes were investigated.
使用FLUENT软件对某型跨音速涡轮叶栅的导叶进行了S_1流面的粘性流动计算。
The present paper computed the viscous flow of S_1 flow surfaces in some transonic turbine vane cascade by using the computational software FLUENT.
应用一维源项喷气模型，结合涡轮叶栅流场数值模拟，得到了不同喷气形式下涡轮叶栅流场细节。
The detailed flow field of ejection cascade was obtained by using a compact ejection model coupled with the calculation of main flow field.
为了详细研究涡轮叶栅的气动特性，深入了解涡轮叶栅流道内的气体流动，对某型涡轮导向叶栅内的流场结构进行了数值模拟。
For investigating the aerodynamic character of the turbine cascades, understanding the detail flow in turbine cascades, the computational investigation was applied on some type turbine guide vane.
本文提出轴流涡轮不等栅距板式喷嘴直叶片的造型计算方法。首先确定切向平面上的叶型中弧线、叶厚和不等栅距。
This article is intended to provide a method for the profile-calculating of unequally pitched nozzle plate straight blades in the axial-flow turbine.
研究表明，可调导叶对涡轮性能的影响是叶栅收敛度、气流冲角与出气角的综合影响。
The results showed the influence of pivoting-stator on the turbine's aerodynamic performance was combined effect of cascade convergence, attack Angle and out-flow Angle.
根据航空发动机设计的实际需要，在大尺寸低速叶栅传热风洞中对涡轮叶片表面的气膜冷却进行了综合性实验研究。
Film cooling of the surface of a gas turbine blade was studied in a large-scale low-speed opening wind tunnel according to actual requirement of the design of aero-engine.
为了考查低压涡轮导向器的气动性能，在低速环形叶栅风洞上对导向器的实验叶栅进行了吹风实验。
For validating the aerodynamic characteristics of LP turbine guide vane, the wind blow was carried out for test cascade of the guide vane on the low speed annular wind tunnel.
结果表明，对此涡轮导向叶栅的改型设计比较成功。
The results showed that it is successful of the redesign to the guide vane.
在大尺寸低速开式叶栅传热风洞中对一种高压涡轮导向叶栅中的流场进行了流动显示实验研究。
The flow field visualization of a straight HP turbine cascade is conducted in a large-scale low-speed open -loop cascade heat transfer wind tunnel.
本文在大尺寸低速开式叶栅传热风洞中对一种高压涡轮导向叶栅中的流场进行了实验研究。
The flow field of straight HP turbine cascade was investigated experimentally in a large-scale low-speed open-loop cascade heat transfer wind tunnel.
针对涡轮叶片的热冲击疲劳寿命实验，提出了一种新的对比实验方案和措施：将实验叶片和参照叶片组合在同一组试验叶栅上，并且在试验过程中定期对调两种叶片的安装位置。
A new comparative test approach is provided for the thermal fatigue life experiments of turbine blade under thermal shock. The tested blades and reference blades were mounted in a common vane cascade.
对某型涡轮正弯及直叶栅流场进行了三维粘性求解。
Flow fields in a bowed and a straight turbine blade channels were simulated with 3d N-S solver.
本文对一种高压涡轮导向叶栅中的紊流特性进行了实验研究。
The characteristics of turbulent flow in a high pressure turbine cascade were investigated experimentally.
通过计算表明，海豚形叶栅在改进传统的涡轮机短叶栅的气动性能方面是明显有效的。
The dolphin -cascade is adopted to replace the traditional TC-1A cascade for reducing high secondary loss in the short cascade.
通过计算表明，海豚形叶栅在改进传统的涡轮机短叶栅的气动性能方面是明显有效的。
The dolphin -cascade is adopted to replace the traditional TC-1A cascade for reducing high secondary loss in the short cascade.
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