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   涡轮盘-叶片 的翻译结果: 查询用时:0.21秒
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航空航天科学与工程
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涡轮盘-叶片
相关语句
  turbine disk-blade
     Finite element analysis on inherent mode of turbine disk-blade
     涡轮盘-叶片整体振动固有模态有限元分析
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  “涡轮盘-叶片”译为未确定词的双语例句
     A kind of aero-engine high pressure turbine blade is simplified and the inherent mode with the turbine join hole fully constrained and in free state is calculated respectively using UG 3-D modeling and Finite element analysis,and the first 10 inherent frequencies and modal figures is given in this paper.
     为了分析方便,对某发动机高压涡轮盘-叶片进行了合理的简化,利用UG三维建模和有限元计算,分别进行了涡轮盘联接孔全约束和完全自由状态下固有模态计算,给出了两种约束前十阶的固有频率和振型图。
短句来源
     The basic reason for different modes and the bad effects on the turbine blades and other structure system are also discussed.
     说明了各阶固有频率振型的运动特点,以及不同形式的振型振动对涡轮盘-叶片和其它结构系统的不利影响。
短句来源
  相似匹配句对
     Blade Machining for Turbine Disk of Aeronautical Cooler
     航空冷却器涡轮叶片的加工成形
短句来源
     Thermal Viscoplastic Analysis of Turbine Blade
     涡轮叶片的粘塑性分析
短句来源
     FRACTURE ANALYSIS FOR TURBINE DISC
     涡轮的破裂分析
短句来源
     Lasers Repair Turbine Blades
     涡轮叶片的激光修理技术
短句来源
     Turbine disk is the heart of aero engine.
     涡轮是航空发动机的心脏。
短句来源
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A reliable method of contact analysis is presented for turbine disk with blades. As the temperatures of the turbine disk and the blade vary greatly,Oak Ridge Nat ional Laboratory′s creep law,in which th e effect of temperature on creep strain is considered,is applied and integrated into the general purpose structure analy sis program APOLANS.Then the thermal ela sto plastic creep contact analysis of a given turbine disk with blades has been...

A reliable method of contact analysis is presented for turbine disk with blades. As the temperatures of the turbine disk and the blade vary greatly,Oak Ridge Nat ional Laboratory′s creep law,in which th e effect of temperature on creep strain is considered,is applied and integrated into the general purpose structure analy sis program APOLANS.Then the thermal ela sto plastic creep contact analysis of a given turbine disk with blades has been carried out.The results show that the ef fective streeses and creep strains are s mall in most of zones,but a high stress zone appears in No.5 throat of disk.The peaks of the effective plastic and creep strain are 0.0164% and 0.01147% respect ively.The results of contact analysis we re compared with the ones of the thermal elasto plastic creep analysis of the di sk without contact.The comparision shows that there are different stress distrib utions near the contact zones.In the No. 5 throat of disk,where stress concentrat ion is most serious,the effective stress ,plastic strain,creep strain obtained by noncontact analysis are smaller than th ose obtained by the contact analysis.The refore it is unsafe to use the results o f noncontact analysis for strength check and life prediction.

利用大型通用结构分析程序APOLANS对某型航空发动机高压涡轮盘叶片进行了热弹塑性蠕变接触分析,并与轮盘热弹塑性蠕变分析结果进行了比较,得出了一些有益的结论,为涡轮盘叶片的应力应变分析提供了一种较为准确的方法。

More and more twist blade is adopted in Aero - engine turbines for improvement of operating efficiency.Geometric molding of twist blade is the premise for turbine blade machining. Blades are fitted by using dual - cubic B-spline surface, from the date of wrap blade surface is given. Some specific problems in cormection with blade modelin, such as choosing coordinate, spanning rectangular gridded area and searching for intersection of surfaces are discussed.

由于可以大大提高发动机的工作效率,所以航空发动机上的涡轮越来越多地开始采用弯扭叶片,弯扭叶片几何造型是当代飞行器发动机涡轮盘叶片加工的前提条件。主要研究了在给定扭曲叶片型值数据的前提下,如何使用双三次B样条曲面来拟合叶片,同时还较深入地探讨并解决了叶片造型过程中遇到的坐标系选取、剖分网格确定以及曲面交线的求解等具体问题。提出的造型方法得到的造型结果可以很好的满足工程需要。

Gas turbine rotor disk-blade system has rather complicated geometric shape and structural form and works under abominable conditions of high temperature and high rotary speed. Accurate stress analysis is the important prerequisite for carrying out strength calculation and prediction of fatigue life. In this paper, ANSYS software of finite element structure analysis was employed to construct a three-dimensional cycle-symmetric finite element model. Circumstances of the anisotropy of blade material, the contact...

Gas turbine rotor disk-blade system has rather complicated geometric shape and structural form and works under abominable conditions of high temperature and high rotary speed. Accurate stress analysis is the important prerequisite for carrying out strength calculation and prediction of fatigue life. In this paper, ANSYS software of finite element structure analysis was employed to construct a three-dimensional cycle-symmetric finite element model. Circumstances of the anisotropy of blade material, the contact nonlinear between turbine disk and blade tenon, the elastic-plasticity deformation of material and the thermal stress caused by non-uniform temperature were considered in this model. Force bearing status and boundary conditions were numerically simulated in the model, and a three dimensional nonlinear cyclic stress-strain analysis was conducted.

燃气涡轮转子盘 -片系统的几何形状和结构形式比较复杂 ,在高温、高转速的恶劣条件下工作 ,准确的应力分析是进行强度计算和疲劳寿命预测的重要前提。使用ANSYS有限元结构分析软件 ,建立了燃气涡轮盘 -片接触系统三维循环对称有限元模型 ,考虑了叶片材料的各向异性、涡轮盘叶片榫头之间的接触非线性、材料的弹塑性变形和温度不均匀引起的热应力等情况 ,数值模拟涡轮盘 -叶片组件的受力状态及边界条件 ,进行三维非线性循环应力 -应变分析。

 
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