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aircraft engines
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  航空发动机
     PLC Control of Electrical System for Aircraft Engines
     航空发动机电气系统的PLC控制
短句来源
     Application of the Virtual Instrument Technology to the Stability Test System of Aircraft Engines
     虚拟仪器技术在航空发动机稳定性测试中的应用
短句来源
     Applications of New Materials on Aircraft Engines
     新材料在航空发动机上的应用概况
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     The System Design of Aircraft Engines History Recorder
     某型航空发动机历程记录仪的系统设计
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     Dynamic Identification with Neural Networks for Aircraft Engines in the Full Envelope
     适用于全包线的航空发动机BP网络模型的动态辨识
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  飞机发动机
     The purpose cf measurement of drone exhaust is to improve structure of aircraft engines.
     测量靶机尾气的目的在于:模似真实的飞机,通过对发动机燃烧产物(尾气)的测定,为发动机燃烧效率提供实测数据,以便改进飞机发动机的结构。
短句来源
     New Technologies Used for Commercial Aircraft Engines
     商用飞机发动机几项关键新技术
短句来源
     In order to put to practical use the study of artificial intelligence, this paper presents an artificial intelligence system for trouble diagnosis of aircraft engines by incorporating some experts' experience in AN-24 engine trouble diagnosis and some typical examples.
     作为人工智能研究中面向实际应用的课题,本系统综合安24飞机发动机故障诊断的专家经验和各种典型实例,用基于规则的演绎推理系统,实现了对飞机发动机故障的经验性诊断。
短句来源
     Detection of the near surface cracks in small parts of aircraft engines with miniature TR probe is described including the design, manufacture and application of the TR probe.
     介绍利用双晶片 (TR)微型探头检测飞机发动机小部件近表面缺陷的方法 ,包括探头的设计、制作与应用
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  “aircraft engines”译为未确定词的双语例句
     The Applications of DD402 Single Crystal Alloy on Turbine Blades of Small Aircraft Engines
     DD402单晶合金在小发涡轮工作叶片上的应用
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     Nb/Nb 5Si 3 in\|situ composites have potential to replace nickel\|based superalloys in the hottest sections of future aircraft engines.
     Nb/Nb5Si3原位复合材料极具替代现有镍基超合金作为未来飞行器发动机超高温部件材料的潜力。
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     Recent Status of Commercial Aircraft Engines Competition
     商用飞机的动力竞争此起彼伏
短句来源
     A Quantitative Prediction Method for Controlling the Maintenance Cost of Civil Aviation Aircraft Engines
     民航发动机维修成本定量评估方法研究
短句来源
     Thermoelasticity Creep Analysis of Aircraft Engines Single-Crystal Air-Cooled Turbine Blade
     单晶叶片的热弹性蠕变分析
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  aircraft engines
This standard specified the testing method for heat resistance under temperature gradient of materials and coated members of equipment exposed to high temperature, such as aircraft engines, gas turbines, and so on.
      
The effective use of TBC in hot-section components of aircraft engines requires nondestructive testing (NDT) methods to detect porosity variations and measure thickness changes to reduce the risk of damage to the coating due to such variations.
      
Process development of PVD TBCs has been carried out at several different sites, including GE Aircraft Engines (GEAE).
      
PVD thermal barrier coating applications and process development for aircraft engines
      
TBC life requirements for aircraft engines are typically less than those required for industrial gas turbines.
      
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In this paper stastistical methods (frequency histogram, probability paper, linear regression, chi-square X2 tests) are applied to analyzing TBO of aircraft engine. The calculated results of three types of aeroengines have shown that the normal distribution is an appropriate model for TBO of aircraft engine. Therefore, along with the given value of TBO, it is reasonable to indicate the probability of the actual operating time of aircraft engines exceeding the given TBO. It is suggested to express the TBO...

In this paper stastistical methods (frequency histogram, probability paper, linear regression, chi-square X2 tests) are applied to analyzing TBO of aircraft engine. The calculated results of three types of aeroengines have shown that the normal distribution is an appropriate model for TBO of aircraft engine. Therefore, along with the given value of TBO, it is reasonable to indicate the probability of the actual operating time of aircraft engines exceeding the given TBO. It is suggested to express the TBO by H(Rk%).Thus many unnecessary overhauls can be evaded, this is of significant economical importance. The mean TBO for normal distribution H = H(50%) is recommended as the parameter of aircraft engine for overhaul. While accepting the mean TBO concept, on-condi-tion maintenance and condition monitoring technology must be adopted in engine operation in order to obtain sufficient flight safety. If the 50% actual operating time of aircraft engine is greater than the mean TBO in airline operation, the TBO can be prolonged. The method for estimating the prolonged life is also given.

本文利用数理统计方法(频数直方图、概率坐标纸、线性回归、X~2检验)分析航空发动机的翻修寿命。对三种航空发动机计算结果表明翻修寿命基本上符合正态分布,因此在给出翻修寿命的同时应给出实际使用寿命可达到所给出翻修寿命的概率,用H(R_k%)表示。建议采用平均翻修寿命[对于正态分布(?)=H(50%)]来作为发动机翻修寿命指标,这样可减少大量不必要的翻修,具有很大的经济意义。采用平均翻修寿命概念后必须采用视情维护和状态监控技术,以保证飞行的安全性。航线使用中如有50%以上发动机实际使用寿命超过平均翻修寿命,发动机就可以延寿,给出了延寿估算方法。

In order to select the optimal cycle parameters in the preliminary design, in this paper we try to apply the "Cycle Analysis" to the estemation of the specific fuel consumption and specific thrust for turbofan engine with separate exhaust streams and augmerted turbofan engine with mixed exhaust streams. Here we introduce a numerical iteration method which may be used to optimize one parameter or simultaneously two parameters without changing other parameters. The calculating program of the optimization at TI--59...

In order to select the optimal cycle parameters in the preliminary design, in this paper we try to apply the "Cycle Analysis" to the estemation of the specific fuel consumption and specific thrust for turbofan engine with separate exhaust streams and augmerted turbofan engine with mixed exhaust streams. Here we introduce a numerical iteration method which may be used to optimize one parameter or simultaneously two parameters without changing other parameters. The calculating program of the optimization at TI--59 programmable calculator is given in the appendix.As an example, we estimate JT9D and F100 turbofan engine and discuss the various factors which influence the selection of optimal cycle parameters. We also use this method to predict the cycle parameters for turbofan engine of the next generation which will power subsonic passenger airliners, supersonic transports and supersonic air superiority fightcrs. For subsonic commercial aircraft engines, the main goal is to reduce specific fuel consumption at subsonic cruise, so the high bypass ratio non-after burning turbofan with mixed exhaust streams may be applicable for this purpose, and during the selecting of optimal cycle parameters, the increase. in bypass ratio, single-stage fan pressure ratio and the overall compressor pressure ratio must be Properly taken into acoount in comparison with the up-to-date level. For-supersonic air superiority fighter engines, the successor of F100 turbofan, the main goal is to satisfy air combat requirements, so the variable bypass-ratio, duct burning, seperate flow turbofan may be utilized for this aim, and during the optimization of cycle parameters, the increase in turbine inlet temperature and fan pressure ratio must be properly taken into account in comparison with the up-to-date level. It is evident that the method given in this paper is applicable in the preliminary design, the whole calculation is comparatively easy and quick, and the result is quite satisfactory.

为了在初步设计阶段选定涡扇发动机最佳循环参数,本文利用气动热力循环分析得出了计算分开排气与混合排气加力涡扇发动机耗油率和单位流量推力的解析表达式。介绍了存其他循环参数固定条件下求某一参数最佳值或两个参数同时为最佳值的数值算计方法,给出了在程序式袖珍计算器TI—59上进行计算的程序。以JT9D、F100两种发动机作为实例进行了计算。讨论了影响参数选择的各种因素。并对下一代亚音速民航机、超音速运输机及超音速战斗机所可能采用涡扇发动机的循环参数进行了予测。以降低巡航耗油率为主的亚音速民航用发动机可采用高函道比混合排气不加力涡扇发动机。循环参数选择应进一步提高函道比、单级风扇增压比以及内函增压比。以满足战斗性能要求为主的F100后继机可采用分开排气、外函加力,变函道比加力涡扇发动机,进一步提高涡轮前总温及外函道增压比。表明本文提出方法是可用的。计算工作量小,可得到满意的初步结果。

This paper deals with the features of AC-AC VSCF power system operating at low speed motor state.There are two operating modes: current continuous and current discontinuous.At low speed,the machine commutation is brought about by A.C voltage of the source,and the allowable maximum current of the machine is greater as compared with that at high speed,hence the maximum torque of the machine is also larger.The low.speed range comes to 30 percent of synchronous speed of the machine.In order to make the most of the...

This paper deals with the features of AC-AC VSCF power system operating at low speed motor state.There are two operating modes: current continuous and current discontinuous.At low speed,the machine commutation is brought about by A.C voltage of the source,and the allowable maximum current of the machine is greater as compared with that at high speed,hence the maximum torque of the machine is also larger.The low.speed range comes to 30 percent of synchronous speed of the machine.In order to make the most of the ability of machine,we should take different current limits for different operating speeds,so that the starting time of aircraft engine may be shortened.

本文讨论变速恒频电源系统交-交方案低速电动机运行时的工作特点。它有两种工作状态:电流连续和电流断续。低速电动工作藉交流电源电压实现电机换相,和高速反电势换相相比,低速允许最大电流较大。故电磁转矩也较大。低速工作转速范围达同步转速的30%。为了充分发挥电机的能力,应根据电机转速取不同的调节器电流限制值,以缩短起动航空发动机的时间。

 
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