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   涡喷发动机 在 航空航天科学与工程 分类中 的翻译结果: 查询用时:0.05秒
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涡喷发动机     
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  turbojet engine
    EXPERIMENTAL INVESTIGATION ON FREQUENCY RESPONSE OF A TURBOJET ENGINE TO TURBULENCE-TYPE DYNAMIC DISTORTION
    涡喷发动机对湍流型动态压力畸变频率响应的实验研究
短句来源
    A SCHEME OF CONDITION MONITORING AND MAIN FAULTS DIAGNOSING SYSTEM FOR A TURBOJET ENGINE
    某型涡喷发动机状态监控与主要故障诊断系统方案
短句来源
    AN APPLICATION OF AUTOMATIC IGNITOR DDK-1 TO TURBOJET ENGINE TEST UNDER SIMULATED ALTITUDE CONDITION
    DDK-1自动点火起动装置在涡喷发动机模拟空中点火起动试验中的应用
短句来源
    A REAL-TIME SIMULATION MODEL OF A TWIN-SPOOL TURBOJET ENGINE
    双轴涡喷发动机性能实时模拟简化模型
短句来源
    AN ELEMENTAL CONTROL VOLUME MODEL OF COMPRESSOR IN TURBOJET ENGINE
    涡喷发动机压气机的单元控制体模型
短句来源
更多       
  turbine jet engine
    Top Level Design of Micro Turbine Jet Engine
    微型涡喷发动机顶层设计研究
短句来源
    The overall tests of exit temperature distribution of the combustor used in missile’s turbine jet engine were presented and the statistic analysis results for the tests were given.
    介绍了弹用涡喷发动机燃烧室部件试验 ,对试验结果进行了全面的分析 ,指出燃烧室模拟试验与发动机实际工况之间的差别 ,产生差别的原因以及试验修正的方法。
短句来源
    A digital controller with RTOS for turbine jet engine
    RTOS在涡喷发动机控制系统中的应用
短句来源
    Trouble Analysis and Elimination of Oil Leakage of Turbine Jet Engine Front Casing Vane
    涡喷发动机前机匣叶片漏油故障分析及排除
短句来源
  turbo-jet engine
    Oil system design of a certain turbo-jet engine
    某型号涡喷发动机滑油系统设计
短句来源
    A STUDY OF SURGE CONTROL BY USING PULSE CUT-OFF FOR DUAL SPOOL TURBO-JET ENGINE
    双转子涡喷发动机脉冲切油防喘控制研究
短句来源
    A Study on Sound Intensity Measurement of a Turbo-Jet Engine during Test-bed Testing
    涡喷发动机台架试验声强测量技术研究
短句来源
  turbojet aero engine
    This method was applied to design the steady state controller of a certain double spool turbojet aero engine,and the expected results were obtained
    该方法应用于某型双转子涡喷发动机稳态控制器的设计,取得了预期的效果。
短句来源
    This method is applied to design the steady state two variable regulating controller of a non standard system——a certain double spool turbojet aero engine. And through the simulation results on aero thermodynamic model, it shows that a preferable effect is achieved.
    该方法应用于非“标准”系统——某型双转子涡喷发动机稳态双变量调节控制器的设计 ,通过在气动热力学模型上的仿真结果表明 ,取得了良好的结果
短句来源
    For the requirement of establishing specific system dynamic model in the fields of adaptive control and failure monitor of advance aero engine, the algorithm with given state variable was proposed and derived, which was based on numerical algorithm for subspace state space system identification(N4SID). At last, this method was applied to identify aero thermal model of a certain double spool turbojet aero engine and the result shows that it is feasible.
    针对现代航空发动机的自适应控制和故障监控领域建立物理意义明确的系统动态模型的需要 ,基于数字子空间状态空间系统辨识 (N4SID)方法 ,提出并推导了指定状态变量的子空间辨识方法 ,并在某型双转子涡喷发动机气动热力学模型上进行了仿真实验 ,说明通过指定状态变量的子空间辨识方法可以得到较好的辨识结果
短句来源

 

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  turbojet engine
The structure and the properties of the air flow developing when an intake system (in particular, a turbojet engine) operates near a surface are studied.
      
The acoustic analogy was introduced into acoustics by Lighthill in 1952 to understand and predict the noise generated by the jet of an aircraft turbojet engine.
      
SR-30 turbojet engine real-time sensor health monitoring using neural networks, and Bayesian belief networks
      
This paper describes the use of artificial intelligence-based techniques for detecting and isolating sensor failures in a turbojet engine.
      
This paper tests this model, using the adoption by American "major" airlines of jet aircraft embodying high bypass turbojet engine technology.
      
更多          
  turbo-jet engine
The Navy contract was for development of a Comprex, also known as a wave rotor, to compete with a turbo-jet engine.
      
  其他


A brief view and results of tests for the effects of the inlet total pressure distortion on the performance and the stability of a two-spool turbojet engine are presented. There are a 3-stage H. P. compressor and a 3-stage L. P. compressor in the engine, in which two types of the first stage rotor G02 and 5P are tested separately. The distortion was generated by metallic mesh screens and the compressor surge was induced by a fuel flow step generator.It could be seen from the test results that when the area of...

A brief view and results of tests for the effects of the inlet total pressure distortion on the performance and the stability of a two-spool turbojet engine are presented. There are a 3-stage H. P. compressor and a 3-stage L. P. compressor in the engine, in which two types of the first stage rotor G02 and 5P are tested separately. The distortion was generated by metallic mesh screens and the compressor surge was induced by a fuel flow step generator.It could be seen from the test results that when the area of the jet nozzle increases from 100% to 142%, the operating line of L. P. compressor falls significantly, no matter whether the inlet airflow is distorted or not.The engine with G02 or 5P first stage rotors has surged 42 times. The surge line and operating line were determined with and without distortion. Test results are given in relationship of the pressure ratio to corrected mass flow and corrected speed.The inlet distortion caused the surge line and operating line of the H. P. and L. P. compressors to be moved downward, and the surge margin decreased. The greater the distortion index, the steeper the surge line falls. When the distortion index increases, the operating line falls slightly, the loss in surge margin increases. The quantitative relationship of the above-mentioned trend is shown with curves of test data in the paper.Comparing the engine test results with the rig test results, the surge line of the L. P. compressor obtained from engine test is higher than that from rig test, no matter whether the inlet airflow is distorted or not. This confirms that the surge margin and the compressor characteristic lines are effected not only by the inlet conditions, but also by outlet conditions, the interaction between compressor and other components, the initial process of surging and the difference between quasi-steady flow and dynamic flow. The characteristic lines of an independent component could not be simply used as a substitute for that of the compressor coupled with other components in a engine. That is, the test results of certain component obtained on test rig under specified conditions could not be considered as a reasonable base for evaluation of its performance and stability in an engine system.

介绍进气总压畸变对双轴涡喷发动机性能和稳定性影响的试验及其结果。试验在地面台架进行。发动机为低压和高压各三级、中等增压比加力式双轴涡喷发动机。 稳态周向压力畸变由90°扇形纱网造成。测定了不同堵塞比的纱网或叠合纱网产生的畸变幅度随发动机空气流量的关系曲线。 在有畸变和无畸变条件下,对装有两种不同展弦比的第一级超音级压气机叶片的发动机,分别测定喘振边界线和工作线,给出低压和高压压气机喘振裕度变化规律,对比试验结果进行了初步分析。 改变发动机喷口面积比由100~142%,在三种畸变和无畸变条件下进行了充分的稳、动态试验,发动机未出现不稳定工作情况。给出无畸变时工作线随喷口面积比变化曲线。 试验采用公司自行设计调试成功的燃油阶跃装置,逼喘双轴涡喷发动机42次。分别获得高压和低压压气机喘点84个以及进喘过程的示波曲线,简要分析了喘振过程参数变化特征。

Instrumentation technique for determining the surge point of a twin-shaft turbojet engine on ground test bed is presented in this paper. The effectiveness of two surge-inducing methods used in the test is also described in the paper. A practical fuel flow step unit is introduced and the surge point measurement and the trace analysis of engine operating point are discussed.Typical oscillograms are given which were taken when the engine was surging or not surging during the fuel flow stepping. When the engine...

Instrumentation technique for determining the surge point of a twin-shaft turbojet engine on ground test bed is presented in this paper. The effectiveness of two surge-inducing methods used in the test is also described in the paper. A practical fuel flow step unit is introduced and the surge point measurement and the trace analysis of engine operating point are discussed.Typical oscillograms are given which were taken when the engine was surging or not surging during the fuel flow stepping. When the engine was brought into Surging, the engine operating point trace diagram is determined by a calculation method based on the flow continuity through nozzle guide vanes of the turbine. This diagram is the final result of the surge point determination technique.

本文介绍双转子涡喷发动机台架喘振点测定技术,阐述了两种逼喘手段在本试验的作用效果,提供一种实用的燃油阶跃装置,喘振测量以及工作点轨迹分析方法,示出典型的喘振和未喘振示波曲线,用涡轮导向器流量连续法计算的进喘过程工作点轨迹图作为喘点测定技术的综合结果。

In this paper, experimental results and analysis about the effect of the inlet pressure distortion, decrease in the first stage turbine nozzle area and engine test run program on the characteristic and instability behavior of an axial compressor in a turbojet engine are presented. The experiments have been conducted on the test bed on a turbojet engine with a 9-stage compressor, whose first stage is transonic.The results show that: (1) inlet distortion and decrease in turbine nozzle area may shift considerably...

In this paper, experimental results and analysis about the effect of the inlet pressure distortion, decrease in the first stage turbine nozzle area and engine test run program on the characteristic and instability behavior of an axial compressor in a turbojet engine are presented. The experiments have been conducted on the test bed on a turbojet engine with a 9-stage compressor, whose first stage is transonic.The results show that: (1) inlet distortion and decrease in turbine nozzle area may shift considerably the speed lines of compressor leftward and cause it to become more flat in shape; (2) the different run program for engine test may produce different speed line of compressor both in position and shape; (3) at low and medium speed, the instability of compressor exhibits itself as a rotating stall, and at high speed, a surge, whose mode depends on the degree of inlet distortion and decrease in turbine nozzle area.

本文介绍进气畸变、第一级涡轮导向器面积及开车程序对涡喷发动机压气机特性及不稳定性态影响的试验结果及分析.试验在一台涡喷发动机上进行,发动机的轴流压气机共九级,第一级为跨音级.

 
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