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叶片冷却     
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  blade cooling
     Review of aero-turbine blade cooling technologies
     航空发动机涡轮叶片冷却技术综述
短句来源
     It is concluded that the study of cooling effects in the turbine disks should comprise not only Nusselts number for disk surface convective heat transfer,but also the non dimensional excessive averaged body temperature for total disk temperature level and the non dimensional radial temperature difference for the disk radial thermal stress. With resort to the concept of turbine blade cooling efficiency,an expression is derived for calculating the cooling efficiency of a turbine disk.
     确定了涡轮盘冷却研究的主要研究内容和影响因素 :除盘面对流换热的努赛尔特数外 ,还应包括反映涡轮盘总体温度水平的无量纲过余体平均温度和反映转盘径向热应力大小的无量纲径向温差 ,借助于涡轮叶片冷却效果的概念 ,给出了涡轮盘冷却效果的表达式。
短句来源
     The experimental results are valuable reference for aero-engine turbine blade cooling designers.
     本文的实验结果对于航空发动机涡轮叶片冷却结构设计具有参考价值。
短句来源
     Jointly using the finite element method,the paper studied the improvement of turbulated cooling holes on turbine blade cooling effects and the parameters that affect heat transfer such as heat transfer coefficient,Nusselt Number and so on.
     并结合有限元方法,研究了竹节孔对涡轮叶片冷却效果的改善,对影响传热的参数,如传热系数与努赛尔数Nu进行了分析。
短句来源
     Experimental results show that the heat transfer effect of this new cooling technique is enhanced with increasing in buoyancy,rotational Reynolds number and cooling air Reynolds number,its cooling ability is better than those of the other two kinds of current blade cooling techniques.
     将新型冷却技术与常规两种涡轮叶片冷却方式-肋强化冷却和冲击冷却的平均换热效果进行比较,得出结论:在实验范围内,新型超级冷却技术比另外两种冷却方式具有更优的换热效果。
短句来源
  cooling blades
     Based on the working situation of aero engine blades, two methods toimprove the high temperature properties of the turbine blades are reviewed, i. e. to develope high efficient cooling blades, and optimize the compositions and processings of the blade alloys.
     针对航空发动机涡轮叶片的工作环境和使用要求,介绍了提高涡轮叶片耐温能力的两种途径,即加强叶片冷却和提高叶片材质自身的耐温性能。
短句来源
  “叶片冷却”译为未确定词的双语例句
     Using numerical simulation method to analysis and research the cooling effectiveness on turbine blade surface can improve reliability and reduce the cost.
     应用数值模拟的方法对涡轮的叶片冷却进行分析和研究,有利于提高工作的可靠性和经济性,因此数值模拟的方法是研究燃气轮机叶片冷却技术的一个重要的手段。
短句来源
     A new cooling technique based on thermal driving in high centrifugal field (TDHCF) is developed for gas turbine rotational components, such as turbine blades.
     通过实验研究了一种新型涡轮叶片冷却技术(Ther-mal driving in high centrifugal field,TDHCF)的换热特性。
短句来源
     Experimental Study on The Stability of Cooling Film on a Turbine Blade
     透平叶片冷却膜稳定性的实验研究
短句来源
     Because of extremely high local heat transfer coefficient and simple structure, Jet impingement cooling has been used widely in many fileds especially in aerospace technology.
     射流冲击冷却技术具有结构简单以及局部换热效果显著等特点,在食品业,钢铁退火,玻璃回火特别是航空发动机涡轮叶片冷却领域得到广泛应用。
短句来源
     Experimental Investigation on Thermally Driving Simulated Turbine Blade with Cooling Tunnels
     模拟涡轮叶片冷却通道的热驱动实验研究
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  blade cooling
Influence of turbulators in blade cooling passages on film hole discharge coefficients
      
The objective of the project was the determination of the influence of turbulators in turbine blade cooling passages on film hole discharge coefficients (Cd coefficients).
      
The unsuitability of the convective blade cooling used up to now is noted.
      
The console geometry is designed in order to improve the heat transfer and aerodynamic loss performance of turbine vane and rotor blade cooling systems without loosing the mechanical strength of a row of discrete holes.
      
For a turbine blade cooling film a comparison of this type of differential interferometry with holographic interferometry and a Schlieren visualisation is also given.
      
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  cooling blades
Experimental and theoretical analytical studies are reviewed which are devoted to the problems of cooling blades of high-temperature gas turbines and were reported at the Third Russian National Conference on Heat Transfer.
      
Changes in the influx into the plasma of iron ions from "cooling" blades significantly affected the location of the gain region and can be used as a mechanism to control the gain region in two-target experiments.
      
Modeling the nonsteady thermally stressed states of the cooling blades of gas turbines
      


Although ceramic coatings are remarkably heat-resisting, internal cooling for high temperature turbine must still be enhanced in virtue of the limiting temperature of the alloy bond coat. Analysis carrying out in this paper shows, that the ceramic coating effectiveness is lower for leading edge than for flat section of the turbine vane and reduces with a increase in ceramic coating thickness. It strongly depends upon cooling intensity of the turbine vane, and for this reason several ways of heat transfer augmentation...

Although ceramic coatings are remarkably heat-resisting, internal cooling for high temperature turbine must still be enhanced in virtue of the limiting temperature of the alloy bond coat. Analysis carrying out in this paper shows, that the ceramic coating effectiveness is lower for leading edge than for flat section of the turbine vane and reduces with a increase in ceramic coating thickness. It strongly depends upon cooling intensity of the turbine vane, and for this reason several ways of heat transfer augmentation in the turbine cooling passage are suggested. Calculations show, that the thermal performance of turbine vane is satisfactory and encouraging.

虽然陶瓷本身具有良好的耐热性能,但粘结剂的温度限制要求加强叶片的内部冷却。本文分析了内冷强化对陶瓷涂层效能的重大影响,提出了加强叶片冷却的几个措施,并通过计算作出了不同冷却条件下叶片前驻点温度与陶瓷涂层厚度的关系曲线。最后利用斯贝MK202发动机一级导向叶片的有关参数对陶瓷涂层叶片进行冷却计算,计算结果表明了采取强化冷却措施后的陶瓷涂层叶片的优良性能。

The functions of available equipment for cooling effectiveness of turbine blade are surveyed, and the corresponding experimental methodology is considered, which is divided into two classes, by comparison and by simulation. Stress is put on the simulating experimentation.

本文对我国现有的涡轮叶片冷却效果实验器的实验功能及相应的实验方法和数据处理方法等进行了探讨。对冷却结构优劣比较性实验只略加评述,重点讨论发动机工况模拟性实验。文章指出,现有冷效实验器有可能对现有水平的发动机进行模拟实验,但对未来更高增压比的发动机工况模拟实验则存在限制。

The stability of the cooling film to attach to a blade surface is investigated by flow visualization technique in a water lunnel under hydrodynamicaly analogous conditions. Cylinder and enlarged blades are used as test models for simulating the leading edge and concave surface of the blade. The flow patterns of cooling film on the cylinder and blade are observed, using colour liquid and air bubbles generated by emulsification. The critical velocity ratio mcr of cooling film at injecting angle θ of 10°,20°, 26°,...

The stability of the cooling film to attach to a blade surface is investigated by flow visualization technique in a water lunnel under hydrodynamicaly analogous conditions. Cylinder and enlarged blades are used as test models for simulating the leading edge and concave surface of the blade. The flow patterns of cooling film on the cylinder and blade are observed, using colour liquid and air bubbles generated by emulsification. The critical velocity ratio mcr of cooling film at injecting angle θ of 10°,20°, 26°, and 40° are measured and related to the acceleration parameter K and spanwise angle β: mcr=f(K,β). The experimental results reveal the factors which affect the effectiveness of discrete holes cooling film and its regularity.

在水洞中,对透平叶片冷却膜附壁的稳定性进行了显示观察和测量的实验研究。用圆柱和放大的叶片做模型,模拟叶片前缘和叶盆凹面的流动。在流体动力学相似条件下,用色液显示的方法,观察了圆柱上展向喷射角β为30°的冷漠的流动图案;测量了从圆周角θ为10°、20°、25°和40°处喷射的冷膜的临界速比m_(cr)与主流加速度参数K的关系,并得出经验公式;m_(cr)=f(K、β)。测量的叶片凹面上冷膜的m_(cr)与K的关系,有与圆柱凸面上的相近趋势,可作为工程设计的参考依据。

 
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