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温度畸变
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  temperature distortion
     Design and Experimental Study of the Inlet Temperature Distortion Generator
     温度畸变发生器的设计与实验
短句来源
     A Study on High Response Instrumentation Technology Used in Aero-engine Inlet Temperature Distortion Measurement
     发动机进气温度畸变高响应温度测试技术研究
短句来源
     Study on Some Measuring Technologies of Temperature Distortion on Inlet Flow of Engine
     发动机进口流场温度畸变测试技术研究
短句来源
     Study on Intake Temperature Distortion
     进气道温度畸变问题的研究
短句来源
     Study on the Effects of Inlet Temperature Distortion on Stability of an Engine
     进气温度畸变对某发动机稳定性影响的研究
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  temperature distortions
     THE MODEL FOR PREDICTING AERODYNAMIC STABILITY IN THE AXIAL COMPRESSION SYSTEMS WITH INLET DYNAMIC TEMPERATURE DISTORTIONS
     动态温度畸变下压缩系统稳定性模型研究
短句来源
     By using this model, the predictions for a three-stage experimental axial compressor are given based on a set of stage-by-stage characteristics. The quantitive relationships between the inlet total temperature distortions and the surge margin losses or the time to surge are obtained.
     基于级特性,模型对一三级实验压气机进行了数值分析,给出了进口动态温度畸变与稳定裕度损失及与不稳定发生时间之间的定量关联关系。
短句来源
     WT5BZ] The unsteady numerical simulation is completed by means of two dimensional,Navier Stokes analysis to predict unsteady flow and temperature fields with inlet temperature distortions in a turbine stage.
     通过求解二维 N-S方程对涡轮级进口有温度畸变时的流场和温度场进行了非定常数值模拟。
短句来源
     Combined effective coefficient shows engine's capability to resist the combined distortion and the interaction between pressure and temperature distortions.
     组合影响系数表示发动机抗组合畸变的能力以及压力畸变和温度畸变之间的相互影响。
短句来源
  “温度畸变”译为未确定词的双语例句
     Research on the heat distortion parameters and the design for engine surge control systems
     航空发动机进口温度畸变参数和防喘控制系统设计
短句来源
     This paper is to emphatically study the influence of steady - state tem-perature distortion on the engine stable operation.
     重点研究稳态温度畸变对发动机稳定工作的影响。
短句来源
     A two dimensional Navier Stokes equation was solved to predict the unsteady,multipassage flow and temperature fields with hot streak in turbine inlet.
     通过求解二维 N-S方程对多通道涡轮级进口有温度畸变时的流场和温度场进行了非定常数值模拟。
短句来源
     The design and development of engine surge control system,especially the parameters of heat disturbance when the fighter launches a missile,were discussed in this paper.
     主要研究了航空发动机防喘控制系统的设计和研制,特别是研究了当战斗机发射导弹时温度畸变对发动机的影响。
短句来源
     A flight test with this engine surge control system has completed and it is shown that the method of design and development for engine surge control system introduced is successful.
     连续温度畸变时间tB。 通过试验和数据分析的方法得出发动机防喘控制系统的设计准则,发动机防喘控制系统的研制和飞行试验证明了该设计准则的正确性。
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  temperature distortion
This study describes the observed effects of rapid cooling from the liquid phase, room temperature distortion (cold working) and heat-treatment on the measurement of ferrite in types 308L, 309L, 316L and 347 stainless steel weld metal.
      
All of these sources can produce a pressure or temperature distortion that will create problems when the air is ingested into the engine.
      


In the investigation of inlet/engine compatibility, the effects of the distorted pressure distortion on engine stability are considered not only by distortion indices but also by distortion contour maps. So distortion maps of given pressure data must be afforded.In this paper, the technique of drawing distortion contour maps with a plotter are described. The effects of the digital approaching and its boundary conditions on the drawing of the map are discussed. It is suggested that a two dimensional third order...

In the investigation of inlet/engine compatibility, the effects of the distorted pressure distortion on engine stability are considered not only by distortion indices but also by distortion contour maps. So distortion maps of given pressure data must be afforded.In this paper, the technique of drawing distortion contour maps with a plotter are described. The effects of the digital approaching and its boundary conditions on the drawing of the map are discussed. It is suggested that a two dimensional third order spline approach can be used to obtain the values of pressure at the node points of the fine mesh. The drawing technique described can be used as well to draw temperature or other contour maps.

本文介绍了一种用绘图仪绘制畸变图谱的技术,並讨论了数值逼近方法及边界条件对图谱的影响。文中建议用二元三次样条逼近压力分布来求得密网格节点上的压力值。文中的绘图技术也可用来绘制温度畸变图谱和其他类型的等值图。

theoretical model is established for predicting the aerodynamic stabilities in muilti-stage axial compressor systems, with inlet dynamic temperature distortion. The numerical method is given based on a method of characteristics and MacCormack's finite difference scheme. By using this model, the predictions for a three-stage experimental axial compressor are given based on a set of stage-by-stage characteristics. The quantitive relationships between the inlet total temperature distortions and the surge margin...

theoretical model is established for predicting the aerodynamic stabilities in muilti-stage axial compressor systems, with inlet dynamic temperature distortion. The numerical method is given based on a method of characteristics and MacCormack's finite difference scheme. By using this model, the predictions for a three-stage experimental axial compressor are given based on a set of stage-by-stage characteristics. The quantitive relationships between the inlet total temperature distortions and the surge margin losses or the time to surge are obtained. The first stage in which the flow instabilities occur is found using this method.

推导并建立了动态温度畸变下多级轴流压缩系统稳定性分析的理论模型,并给出了基于特征线和MacCormack二步差分法的数值分析方法。基于级特性,模型对一三级实验压气机进行了数值分析,给出了进口动态温度畸变与稳定裕度损失及与不稳定发生时间之间的定量关联关系。本模型还确定了压气机失稳的首发级。

A general numerical method is developed for predicting aerodynamic stability inmultistage axial compression systems with inlet combined pressure and temperature distortion basedon stage-by-stage parallel compression system model. The predictions for two multistage axial flowcompressors are given by using this method. The quantitative relationships between the inlet totalpressure distortion, or total temperature distortion, or combined pressure and temperature distortionand the surge margin losses are obtained....

A general numerical method is developed for predicting aerodynamic stability inmultistage axial compression systems with inlet combined pressure and temperature distortion basedon stage-by-stage parallel compression system model. The predictions for two multistage axial flowcompressors are given by using this method. The quantitative relationships between the inlet totalpressure distortion, or total temperature distortion, or combined pressure and temperature distortionand the surge margin losses are obtained. It is found that the effects of aligned pressure andtemperature distortion on aerodynamic stability of axial compressors are the most strong.

基于逐级平行压缩系统模型,发展了一种分析周向组合畸变对多级轴流压缩系统稳定性影响的通用分析方法。应用此方法对两个多级轴流压气机进行了详细的数值分析,给出了纯压力畸变、纯温度畸变及压力-温度不同位置的组合畸变与轴流压气机喘振裕度损失之间的定量关系。

 
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