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流风扇
相关语句
  flow fan
     Modern Mixed Flow Fan Strength Calculation
     混流风扇的强度计算
短句来源
     A Study on Aerodynamic Characteristics and Velocity Distribution of Flow Field in Cross Flow Fan
     贯流风扇内部流场流动特征及流速分布的研究
短句来源
     Analysis and Test for Noise Radiated from Micro-Axle Flow Fan
     微型轴流风扇噪声特性分析及试验研究
短句来源
     The Study of Three Dimensional Mixed Flow Fan Used in Special Vehicle and Analysis of Effecting Factors
     车用混流风扇三元流设计方法研究及影响因素分析
短句来源
     A Study on Turbulence in Exit of Cross Flow Fan
     空调用贯流风扇出口处紊流的研究
短句来源
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  “流风扇”译为未确定词的双语例句
     So it is important to establish mathematical model of blade for flow field emulating.
     所以建立贯流风扇叶片数学模型对于贯流风扇流场仿真具有重要意义。
短句来源
     EXPERIMENTAL STUDY ON ROTATING STALL IN AN AXIAL-FLOW FAN
     轴流风扇旋转失速的实验研究
短句来源
     QUALITY CONTROL OF PLASTIC AXIA-fLOW FAN PRODUCTION
     塑料轴流风扇的质量控制
短句来源
     A model for computing the loss and deviation angle is developed using stage-stacking method on average streamline. With the method, the calculation of arbitrary stage characteristics is carried out.
     本文研究了计算多级轴流风扇/压气机有水注入工况下的损失模型和落后角模型,使用了在平均流线上级叠加的方法来展开计算,可以计算任意级以及全台风扇/压气机的特性。
短句来源
     Simple Method Using Gurney Flap to Reduce Noise of Axial Fan
     使用Gurney襟翼降低轴流风扇噪声的简便方法
短句来源
更多       
  相似匹配句对
     Modern Mixed Flow Fan Strength Calculation
     混风扇的强度计算
短句来源
     Research on the performance improvement of the low pressure axial flow fan
     低压轴风扇性能的改善
短句来源
     Mechanical Energy Flow
     机械能
短句来源
     WOUNDED PATIENT FLOW
     伤员
短句来源
     Lift fan of air cushion vehicle
     气垫船垫升风扇
短句来源
查询“流风扇”译词为用户自定义的双语例句

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  flow fan
Here the vulnerability is defined as the potential total maximum losses due to a debris flow damaging event for a specific debris flow fan.
      
Investigations on an axial flow fan stage subjected to circumferential inlet flow distortion and swirl
      
The combined effects of swirl and circumferential inlet flow distortion on the flow field of an axial flow fan stage are reported in this paper.
      
This paper studied the velocity field by means of PIV technology for a leading edge swept axial-flow fan without casing, and the tip vortex phenomenon was observed.
      
Natures of rotating stall cell in a diagonal flow fan
      
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The supersonic through flow(STF)fan engine is a new concept with many advantages. To carry out the cycle analysis for STF fan engine, a computer program system for evaluating engines'thermodynamic quality and optimizing its cycle variables has been developed. The program can be used for general turbofan and turbojet engines. Then, a STF fan engine equipped for a transport with cruise Mach number 2.7 was studied,the main results are as follows.At cruise condition,the specific fuel consumption is 2 %(or more)...

The supersonic through flow(STF)fan engine is a new concept with many advantages. To carry out the cycle analysis for STF fan engine, a computer program system for evaluating engines'thermodynamic quality and optimizing its cycle variables has been developed. The program can be used for general turbofan and turbojet engines. Then, a STF fan engine equipped for a transport with cruise Mach number 2.7 was studied,the main results are as follows.At cruise condition,the specific fuel consumption is 2 %(or more) lower for STF fan engine than conventional turbofan engine and 8%(or mo-re)lower for STF fan engine than turbojet engine. At takeoff condition,STF fan engine also has lower specific fuel consumption advantages.Take a one stage 16 degree conical spike inlet as an example,when the entrance area of the STF fan inlet is designed at the takeoff state for a transport mission profile, the mass flow at other mission state can be also obtained fully.The good com- patibility of inlet with STF fan engin'e is the key for a high performance STF fan engine.

超音通流风扇发动机概念新、优点突出.本文发展的计算机程序能对不同类型发动机进行循环分析和某些参数的优化计算,对一架Ma=2.7的超音巡航运输机进行了算例分析.计算结果表明,超音通流风扇发动机耗油率大大低于常规涡扇和涡喷发动机,重量轻,推重比高,亦有明显优势.有效解决飞行剖面上进气道与发动机相容性问题,对提高推进系统性能关系很大.

The numerical simulation of supersonic through-flow fan cascade flow field was conducted by using Flux Vector Splitting in solving N-S equations and Euler equations. The physicalpictures of the compUtational results show that there are neither strong shock nor separationand reversed flow in the cascade passage. The whole cascade flow field is proved to be the supersonic flow. Which is an indication that the calculated two cascade flow fields satisfy thedesign requirement. The performance still needs to be examined...

The numerical simulation of supersonic through-flow fan cascade flow field was conducted by using Flux Vector Splitting in solving N-S equations and Euler equations. The physicalpictures of the compUtational results show that there are neither strong shock nor separationand reversed flow in the cascade passage. The whole cascade flow field is proved to be the supersonic flow. Which is an indication that the calculated two cascade flow fields satisfy thedesign requirement. The performance still needs to be examined in the future experiments.

用矢通量分裂法求解N-S方程和Euler方程,对超音通流风扇叶栅流场进行了数值模拟.由计算结果给出的物理图象表明:叶栅通道内没有强激波,亦未出现分离回流,全叶栅流场均为超音速,说明计算的两种叶型符合设计要求,其性能有待实验检验.

The total characteristics of a Supersonic Through Flow (STF) fan propulsion system of unconventional configuration have been studied.Therefrom some conclusions are obtained as:1.The system's bypass ratio must be actively controlled by adjusting both core and bypass engine's through flow areas.2.A general propulsion system with a bypass ratio variable cycle is able to hold a higher fan compression ratio or a stronger fan power in supersonic flight,when it is coupled with a variable core nozzle critical section...

The total characteristics of a Supersonic Through Flow (STF) fan propulsion system of unconventional configuration have been studied.Therefrom some conclusions are obtained as:1.The system's bypass ratio must be actively controlled by adjusting both core and bypass engine's through flow areas.2.A general propulsion system with a bypass ratio variable cycle is able to hold a higher fan compression ratio or a stronger fan power in supersonic flight,when it is coupled with a variable core nozzle critical section area.3.For this new concept propulsion system,the specific thrust per unit of the total air mass flow does not vary with altitude up to the stratosphere.Some calculational results are presented briefly to support the above mentioned conclusions.

探讨了一种非常规结构的推进系统—超音通流风扇推进系统的总体性能的特征。得到:(1)其必为变涵道比循环系统,由可变几何内、外涵通道提供对涵道比的主动控制;(2)一般的变涵道比循环推进系统超音速飞行时可获较常规系统更高的风扇增压比或风扇功率;(3)该推进系统高空单位流量推力与高度无关。简介了有关算例以说明诸点。

 
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