英语释义

• the long airfoil that rotates to provide the lift that supports a helicopter in the air

片语

effect of rotor-blade modulation旋叶调制效应

rotor-blade angle旋翼桨叶角

rotor-blade disk system转子轮盘系统

rotor r blade转子叶片

compressor rotor-blade压气机转子叶片

effects of rotor-blade modulation旋叶调制效应

rotor fan blade转子扇翼

rotor-blade airfoil旋翼翼型

rotor-blade modulation旋翼调制效应

英汉例句

• according to the specialized demands of the rotor blade design, the paper studies emphatically how to creat the feature library which is used to design the root and the platform of blade.

  根据转子叶片设计的特殊要求，本文着重研究了转子叶片榫头、安装板的特征库。

• 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 cause of water erosion in the end rotor blade of 100 mw steam turbine is analyzed with solution proposal.

  对神木发电有限公司100mw汽轮机末级动叶片水蚀原因进行了分析，并提出了解决方案。

• 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。

• fw61 rotor hub device is equipped with a periodic pitch, rotating in the rotor blade can be changed during the pitch.

  fw61旋翼毂上装有周期变距装置，在旋翼旋转过程中可改变桨叶桨距。

• 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。

• a new way to solve dynamical response of rotor blade in helicopter.

  提出了一种全新的计算旋翼桨叶动力响应的方法。

• a support beam for connecting a lift generating wing section of a helicopter rotor blade with a rotor hub, said support beam comprising.

  支持梁连接电梯发电翼的第一个直升机旋翼叶片与转子枢纽的地位，表示支持梁，包括。

• investigation and application of non-contact rotor blade vibration measurement technique;

  介绍一种非接触式、静电感应型测量静电的应用。

• this model accounts for the uncertainty about the loads acting on the wind-turbine rotor blade by the unstable wind distribution. a 20-year design lifetime is considered.

  该种模型考虑了由于风速的不稳定所带来的作用在风力机叶片上分布载荷的不确定因素，并假定风力机的设计寿命为20年。

• the results are believed to be useful for the experimental research on the rotor blade system as numeric references.

  所得结果可以为实验研究转子叶片系统提供数值参考。

• it provides a basis for rotor blade crack diagno.

  这就为转子叶片裂纹故障的监测与诊断提供了依据。

• 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。

• 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。

• a new method is presented for calculating the quasi steady transonic flow over a lifting rotor blade in hover by using euler equations.

  描述了数值计算有升力旋翼的跨声速流场过程。

• this paper presents the optimal design method of the last stage rotor blade root cascade for large-output steam turbines with actual design examples being given.

  本文提出了大功率汽轮机末级动叶根部叶栅的最优化设计的方法，并给出设计实例。

• 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。

• the derived nonlinear ordinary differential equations with time-dependent coefficients of the rotor blade are given in the sense of the generalized forces.

  导出的旋翼桨叶非线性时变常微分方程以广义力的形式给出。

• the wing withstands vertical bending, chordwise bending and torsional deformations, and the rotor blade is considered to be capable of rigidly withstanding one order flap and lag motions.

  机翼承受垂向弯曲、弦向弯曲和扭转变形，螺旋桨旋翼的桨叶认为是刚性的并承受一阶挥舞和摆振。

• 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。

• the design of structure and dynamics of a rotor blade is based on its section characteristic of composite blade.

  复合材料桨叶剖面特性是旋翼桨叶设计的最基本原始参数，也是桨叶结构设计、动力学设计和结构分析的基础。

• the coupled flap-lag flutter stability of a helicopter rotor blade in hover is investigated by using a finite element formulation based on the principle of minimum potential energy.

  本文用基于最小位能原理的有限元方法研究了直升机悬停时旋翼浆叶挥舞—摆振耦合颤振。

• response calculation method for the rotor blade with arbitrary rigid motions;

  提出了一种全新的计算旋翼桨叶动力响应的方法。