As to the selection of rotor blade number for light and medium helicopter, 4 blade and 5 blade rotor are typical.
而旋翼桨叶片数的选择，对轻型和中型直升机来讲，4片桨叶旋翼和5片桨叶旋翼具有典型意义。
The comparative tests of the pinrotor with conventional two blade rotor in a domestic internal mixer were reported.
本文介绍了在国产密炼机上采用销钉转子和普通二棱转子进行对比试验的情况。
Then there's increasing the number of rotor blades. This helps because each additional blade carries less of the weight of the helicopter, and thus produces less noise.
增加旋翼桨叶数量也是一种方法，这使得每片桨叶负载的直升机重量降低了，因此产生的噪音更小。
Rotor blade connection according to claim 1 wherein each intermediate layer of the individual dampers is fixed to the support beam structure by a single fastening point.
转子叶片方面，根据权利要求1，其中每一个中间层的个别阻尼器是固定的支持梁结构，由一个单一的紧固点。
Rotor blade connection according to claim 1 wherein individual elastomer dampers are arranged to provide a damping effect in a lead-lag bending direction of the support beam.
转子叶片方面，根据权利要求1，其中个别弹性阻尼器的安排，以提供一个阻尼效应在带头滞后弯曲方向的支持束。
Rotor blade connection according to claim 1 wherein the support beam and the intermediate layers comprise a fiber reinforced material.
转子叶片方面，根据权利要求1其中，支撑梁和中间层组成，纤维增强材料。
Connection apparatus for a helicopter rotor blade, comprising.
连接装置的直升机转子叶片，其中包括。
Rotor blade connection according to claim 4 wherein the intermediate layers are covered with electrically controlled piezo elements.
转子叶片连接据索赔4其中，中间层是涵盖与电控压电元素。
The airfoil member according to claim 1, configured as a rotor blade for a helicopter.
翼型会员根据权利要求1 ，配置为转子叶片为直升机。
Adding a rotor blade (it had five on the main rotor and four on the tail) and using a modified exhaust system were among them.
增加一个桨叶(主桨有5个叶片，尾桨有4个)，并使用了改进的排气系统。
This text made FEM calculation and analysis for rotor disk of heavy blower in a plant, and found that the disk can be reused safely again after the arc grooves along outside of blade being repaired.
对某发电厂大型鼓风机转子轮盘强度进行了有限元计算与分析，确认了转子轮盘在出现沿叶片外弧的弧形沟槽后，略加修复仍可安全使用。
Rotor design is comprised of some factors such as hub configuration, blade number, rotor diameter, rotor solidity and airfoil which have effects on helicopter performances.
旋翼设计包括桨毂构型、旋翼桨叶片数、旋翼直径、旋翼实度、翼型剖面等一系列影响直升机性能的因素。
Thermal analysis on the first stage turbine rotor blade has been completed based on the CFD results under calculated conditions.
根据某型涡喷发动机计算状态叶片流场计算结果，对该发动机高压涡轮转子叶片进行了热分析；
The second part presents the application of skewed blade in the design of diagonal rotor.
第二部分是将叶片的弯曲设计应用于本文所用的斜流叶轮中。
This paper gives the design method and key point during machining of pin holes on rotor for the fork-type blade root.
论述了转子叉形齿叶根销孔加工用钻模的设计方法及制造时关键要点。
The helicopter rotor blade deicing technique is greatly important to ensure the flight safe - ty.
直升机旋翼桨叶除冰技术对保证直升机飞行安全是十分重要的。
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.
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。
The engines main body structure is an internal-combustion rotor, which has no blade and no piston but has an internal revolved stream combustor.
该发动机主体结构为一内置有旋流燃烧室的高速旋转无叶无塞内燃转子，能融压气、燃烧和排气做功于一体。
A blade, essentially made of composite material, for a rotorcraft rotor, comprising.
刀片，基本上制成的复合材料，为旋翼机转子，其中包括。
Experimental results show that under the effect of the rotor wake, the dominant frequencies of pressure fluctuations on stator blades are the rotor blade passing frequency (BPF) and its harmonics.
实验结果表明：在转子尾迹的影响下，静子叶片表面的波动频率是转子的尾迹频率及其倍频。
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.
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。
The seals on different blades have different influence on the vibration of the rotor, and the seal on the middle blade has the most obvious influence on the rotor.
转子各级叶轮处的密封对转子振动的影响程度不同，以中间一级叶轮的影响最为显著。
Gravity center modification method can be used in high-load rotor blade design in engineering.
重心线调节法可应用于高负荷叶片设计。
The numerical method of determining the water droplet impingement property of rotor blade in hover was studied.
介绍了直升机在悬停状态下，求解旋翼水滴撞击特性的数值方法。
Main rotor is the key part of helicopter modeling, the associated modeling methods of aerofoil aerodynamic loads, rotor inflow dynamics and blade flap motion are discussed in detail.
主旋翼是直升机建模的关键，详细讨论了与其相关的翼型气动力模型、 诱导速度模型和挥舞运动模型的建模方法。
The top blade clearance flow image of rotor was taken by intuitionistic smoke display technology successfully.
采用直观的烟雾显示技术成功地捕捉转子叶顶间隙泄漏流动图像。
Because of the symmetry of the flow field of hovering rotor, one blade is needed to be calculated.
悬停旋翼的流场由于具有对称性，只需要对一片桨叶进行计算。
As a critical part of helicopter, rotor blade anti-fatigue design technique is one of the key to improving safety life and decreasing cost.
作为直升机的关键动部件，桨叶的抗疲劳设计技术是提高桨叶安全寿命，降低桨叶使用成本的关键。
As a critical part of helicopter, rotor blade anti-fatigue design technique is one of the key to improving safety life and decreasing cost.
作为直升机的关键动部件，桨叶的抗疲劳设计技术是提高桨叶安全寿命，降低桨叶使用成本的关键。
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