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高压涡轮
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  high pressure turbine
     Experimental Study of High Pressure Turbine Cascade Trailing Edge Loss
     高压涡轮叶栅尾缘损失的试验研究
短句来源
     Repairing Technology of High Pressure Turbine Blade Tip Crack for an Aero-Engine
     某型发动机高压涡轮叶片叶尖裂纹修复工艺研究
短句来源
     Film cooling of high pressure turbine blade cascades,which are provided with two rows of cooling orifices at their leading edges,had been numerically calculated,the static pressure distribution over the blades' profiled surfaces,respectively for the blowing rates 0,0.7,1.1,and 1.5 obtained,and calculation results compared with experimental results.
     对前缘带有2排冷却孔的高压涡轮叶栅进行了气膜冷却数值计算,在吹风比分别为0、0.7、1.1、1.5的情况下得到了叶片型面的静压分布,并将计算结果与实验数据进行了对比研究。
短句来源
     This method was used to analyze a high pressure turbine disk with the displacement of stress release as geometrical boundary condition. The residue stress and the maximal stress and strain cycle of the critical points adjacent to central hole and radial pin hole are obtained and the life of low cycle fatigue is predicted.
     应用以应力释放位移为几何边界条件的残余应力确定法对某型发动机高压涡轮盘进行了残余应力分析,得到了涡轮盘中心孔与径向销钉孔交界处的残余应力,并计算了该危险点最大应力应变循环,预测了低循环疲劳寿命。
短句来源
     A Subject "Impact of Suction Surface Shape on High Pressure Turbine Trailing Edge Loss" has been conducted by BRR, GTE and DLR.
     由德国宝马·罗·罗 (BRR)、中国燃气涡轮研究院 (GTE)和德国宇航院 (DLR)联合开展了“叶背表面曲率的变化对高压涡轮尾迹损失的研究”。
短句来源
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  high-pressure turbine
     An Experimental Study on the Stage Performance of a High-pressure Turbine
     某型高压涡轮级性能试验研究
短句来源
     A Method for Eliminating the Trouble of High-Pressure Turbine Flowmeter
     高压涡轮流量计故障排除方法
短句来源
     Researching on mass flow measurement of high-pressure turbine guide vane
     高压涡轮导向器前支撑质量流量测量研究
短句来源
     Against the background of the E3 counter-rotating turbine program, aimed at the problem that the design of the high-pressure turbine stage is difficult to offer sufficient prewhirl for the low-pressure turbine stage, an idea has been presented, that is by the trust of transition duct instead of the first stage vane of the low-pressure turbine to supply the prewhirl.
     本文以E3对转涡轮方案为背景,针对高压涡轮动叶设计难以满足低压涡轮预旋需求的难点,提出了取消低压涡轮导叶,改由过渡段支板弥补高压涡轮所提供预旋不足的过渡段改进设想。
短句来源
     The experimental results show that high-pressure turbine vane has good periodicity of flow field,the performance of turbine vane achieves design target.
     试验结果表明,试验的高压涡轮导向器流场周期性较好,导向器的性能达到了设计指标。
短句来源
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  hp turbine
     Analysis of Coupling Resonance Characteristics of HP Turbine Bladed-Discs for an Aeroengine
     某型发动机高压涡轮盘-叶耦合共振特性分析
短句来源
     FE stress analysis of a turboprop engine HP turbine disk is completed. The results show that the stress level of turbine disk is within the elastic range at various operation conditions and maximum stress location is still at the eccentric orifice.
     对某涡桨发动机高压涡轮盘进行了有限元应力分析,结果表明:在各工作状态,涡轮盘的应力水平在各工作状态都处于弹性范围,最大应力点始终处于轮盘的偏心孔处;
短句来源
     Based on an engineering background, through numerical simulation of the flow field in the HP Turbine of the Energy Efficient Engine(E3), the article research the unsteady flow in a transonic turbine stage, the unsteady phenomena in the stage include the Shockwave, wake, shedding vortex, endwall vortex, passage vortex and leakage vortex, etc.
     本文首先对于研究的意义和国内外研究的现状做了简要的介绍,再从某工程背景出发,通过对E3发动机高压涡轮内流场的数值模拟,研究了干涉的周期性的问题,以及涡轮级内常见的非定常现象:激波、尾迹、脱落涡、根脚涡、通道涡、漏流涡。
短句来源
     Computational Analysis of the HP Turbine Nozzle Guide Vane Internal Flow Characteristics
     高压涡轮导叶内冷通道流动特性计算分析
短句来源
     The flow field of straight HP turbine cascade was investigated experimentally 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。
短句来源
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  “高压涡轮”译为未确定词的双语例句
     Research on Numerical Calculation and Analysis of HPT Tip Clearance
     高压涡轮叶尖间隙数值计算与分析研究
短句来源
     ANALYSIS OF CRACKS ON SERRATION OF TURBINE DISC
     高压涡轮盘榫齿裂纹分析
短句来源
     A STUDY OF THE DESIGN FEATURE OF E~3 COUNTER-ROTATING TURBINE(Ⅰ)——CONSIDERATION ON THE DESIGN OF HIGH-PRESSURE STAGE
     E~3对转涡轮设计特点分析(Ⅰ)——高压涡轮基元级方案分析
短句来源
     A steady of three-dimension numerical simulation was conducted on high pressure (HP) turbine stage by using CFD software CFX-TASCflow with SST turbulen ce.
     本文采用CFD软件CFX-TASCflow对带冷气影响的某高压涡轮级流场进行了数值模拟。
短句来源
     A conjugate numerical methodology of CFX-TASCflow code was employed to predict the radial cooled turbine blade which was based on the experimental study of Ref. [1]. Simulation results agree with the data of experiment.
     借助CFX-TASC flow程序的气热耦合数值模拟技术分析了文献[1]实验研究的径向冷却高压涡轮叶片,计算结果与实验数据比较吻合,与绝热壁面条件的结果比较,叶片外表面的等熵马赫数增加.
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  high pressure turbine
The static pressure distribution along the span in the pressure surface of a high pressure turbine stator is more uniform than that in the suction surface.
      
The static pressure distributions along the span in the pressure surfaces and the suction surfaces of a high pressure turbine rotor and a low pressure turbine rotor are all uneven.
      
The numerical results also indicate that the load of a high pressure turbine rotor will increase with the increase of the span.
      
The deviation is very big between the direction of air flow at the outlet of a high pressure turbine rotor and the axial direction.
      
This means that the specific work of a high pressure turbine rotor and a low pressure turbine rotor is big enough to reach the design objectives.
      
更多          
  high-pressure turbine
Calculation of the Flow around a High-Pressure Turbine Blade with Cooling-Jet Injection from Slots at the Leading Edge
      
High-pressure turbine-driven gas-expansion machine RT-5/200
      
Peculiarities of operation of guide vanes of the first stage of high-pressure turbine of the gas-pumping unit GTN-6
      
The environmental protection of aircraft engine high-pressure turbine blades is dependent upon the formation of a thin, slow-growing, external alumina scale.
      
A high-pressure turbine bypass is used to regulate control system pressures on the exhaust side.
      
更多          
  hp turbine
No information below the Combustor or HP Turbine is visible.
      
This lets us achieve greater accuracy in performing HP turbine tip clearance, resulting in better performance.
      
The first two stages use the proven design of the previous PGT10 HP turbine model with cooling provided by air bled from the axial compressor.
      
The high-pressure, high-temp steam is carried from the superheater outlet of the boiler to the HP turbine of the main engine.
      


Based on the analysis of physical and geometric features of turbine characteristics, a flow and efficiency-characteristics fitting model for variable-nozzle turbines is provided. A new "two step" method for determining the unknown parameters of the mathematical fitting model is suggested. With this model, the characteristics of a variable-nozzle power turbine have been fitted. As compared with the original data, the average relative errors of the corrected flow and efficiency obtained from the model are 0.675%...

Based on the analysis of physical and geometric features of turbine characteristics, a flow and efficiency-characteristics fitting model for variable-nozzle turbines is provided. A new "two step" method for determining the unknown parameters of the mathematical fitting model is suggested. With this model, the characteristics of a variable-nozzle power turbine have been fitted. As compared with the original data, the average relative errors of the corrected flow and efficiency obtained from the model are 0.675% and 0.534% respectively. In addition, the flow characteristics of a high-pressupe turbine with 2 independent variables have also been fitted, the avenge relative error being 0.638%. Thus, the results obtained from the present model may be considered satisfactory.

本文通过对涡轮特性曲线的物理意义和几何特征的分析,提出了适用于喷嘴安装角可调的涡轮流量特性和效率特性的拟合模型,并提出了一种新的计算方法来确定拟合数学模型中的待定参数。用该模型拟合了某发动机变几何动力涡轮的特性。与原节点数据相比,流量和效率特性拟合回代值的平均相对误差分别为0.675%和0.534%。另外,又拟合了某定几何高压涡轮的流量特性,平均相对误差值为0.638%,其结果令人满意。

Based on analysis of physical and geometric features of turbine performance, a fitting model of flow and efficiency characteristics for variable-nozzle turbine is prcsented. A New method for determining the unknown parameters of the mathematical fitting equation is suggested. As compared with the original data of a variable-nozzle power turbine, the average relative errors of the flow and efficiency obtained from this model are 0.675% and 0.534% respectively.

作者通过对涡轮特性曲线的物理意义和几何特征的分析,提出了适用于喷嘴安装角可调的涡轮流量特性和效率特性的拟合模型,并提出了一种新的计算方法来确定拟合数学模型中的待定参数。用该模型拟合了某发动机变几何动力涡轮的特性。与原节点数据相比,流量和效率特性拟合回代值的平均相对误差分别为0.6%和0.5%。另外又拟合了某定几何高压涡轮的流量特性,平均相对误差值为0.6%,其结果令人满意。

According to strict theory of similarity,the modelling conditions for model experiments on cooling blades or vanes of a gas turbine are obtained from a necessary set of differential equations and single valued conditions.It is shown that when the pressure in modelling is lower than that in the actual turbine,the temperature in modelling must be lowered simultaneously in order to maintain the criterion on pl/μc PT for cooling air and for...

According to strict theory of similarity,the modelling conditions for model experiments on cooling blades or vanes of a gas turbine are obtained from a necessary set of differential equations and single valued conditions.It is shown that when the pressure in modelling is lower than that in the actual turbine,the temperature in modelling must be lowered simultaneously in order to maintain the criterion on pl/μc PT for cooling air and for gas invariant.Therefore,it is necesary to increase the pressure and to decrease appropriately the temparature in modelling tests for the blades and vanes of high pressure turbines with high pressure ratio.

从所需微分方程组及单值性条件出发 ,以严格的相似理论得出涡轮叶片冷效模拟实验所应遵循的模化条件。指出 ,当实验所用压力比原型低的条件下 ,为满足表征密流水平的准则 p L/ μcp T相等的条件 ,则实验所用温度水平也应下降。为能模拟高增压比发动机高压涡轮叶片的冷效 ,应尽可能提高实验器的压力水平并适当地降低实验中的温度水平 ,不应采取与此相反措施

 
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