涡扇发动机的英文

• fanjet
• turbofan

• "涡"英文翻译    eddy; whirlpool; vortex
• "扇"英文翻译    fan
• "发动机"英文翻译    engine; motor
• "齿轮传动涡扇发动机" 英文翻译 :    gtf
• "风扇发动机" 英文翻译 :    fan engine; fan-type engine
• "桨扇发动机" 英文翻译 :    propfan
• "后风扇发动机" 英文翻译 :    aft-fan engine; after fan engine; engine; after fan
• "前风扇发动机" 英文翻译 :    forward fan engine
• "涡轮扇发动机" 英文翻译 :    turbofan
• "变距风扇发动机" 英文翻译 :    variable pitch fan engine
• "导管风扇发动机" 英文翻译 :    ducted fan engine
• "干涡轮风扇发动机" 英文翻译 :    dry turbofan
• "管道式风扇发动机" 英文翻译 :    ducted-fan engine
• "函道风扇发动机" 英文翻译 :    ducted fan engine; ducted-fan engine
• "函道式风扇发动机" 英文翻译 :    ducted-fan engine
• "螺旋桨风扇发动机" 英文翻译 :    propeller fan engine
• "升力风扇发动机" 英文翻译 :    lift fan engine
• "涡轮风扇发动机" 英文翻译 :    ducted fan engine; fanjet engine; turbo fan; turbofanengine
• "升力发动机, 气垫风扇发动机" 英文翻译 :    lift engine
• "低噪音低污航空涡扇（发动机）" 英文翻译 :    quiet clean general-aviation turbofan (qcgat)
• "高函道比涡轮风扇发动机" 英文翻译 :    high bypass ratio turbofan engine; high-by-pass turbofan
• "国际商用风扇发动机公司" 英文翻译 :    commercial fans motor
• "混流式涡轮风扇发动机" 英文翻译 :    mixed-flow turbofan
• "加力式涡轮风扇发动机" 英文翻译 :    afterburning turbofan engine; reheat turbofan
• "加力涡轮风扇发动机" 英文翻译 :    augmented turbofan engine

• Dual - mode optimization asymmetry fuzzy logic controller design for x aeroengine mfp
  某涡扇发动机主燃油通道模糊控制器设计
• Construction of weighting matrixes in mixed sensitivities h controller design for aeroengine
  涡扇发动机转速鲁棒控制器设计及试验
• On a novel multi - objective fsqp algorithm for multi - variable nonlinear control of turbofan engine
  算法实现涡扇发动机多变量非线性控制
• Numerically assessing aerodynamic stability of compression component running in turbofan engine
  涡扇发动机整机环境下压缩部件稳定工作边界计算方法
• But such is the reliability and power of modern high - bypass turbofan engines that it has ceased to be a worry
  但现代涡扇发动机的可靠性和强劲的动力打消了人们的疑虑。
• The simulation accuracy can be improved by above model for the turbofan engine transient performance
  上述模型的建立将有效的提高涡扇发动机过渡过程性能模拟程序的精度。
• The nozzle flow is composed of the main gas stream and the secondary air stream in order to simulate the nozzle of turbofan engine
  喷管中的气流由主流燃气和次流空气组成，用以模拟涡扇发动机的喷管。
• The mathematical model of a twin - spool turbofan engine is set up , and the “ one ? pass through algorithm ” is used to construct the real time dynamic model
  利用部件级建模方法建立了某大型涡扇发动机数学模型,采用一步通过算法使过渡过程计算满足实时性。
• And based on these , the application of sequential quadratic programming ( sqp ) to the turbofan engine performance seeking control is investigated
  并在此基础上，运用序列二次规划法对涡扇发动机的加、减速和加力加速等过渡过程寻优控制问题进行了研究。
• The mission section , the constrain conditions , the weight composition of the maneuverable missile , and the model of used in turbofan engine maneuverable missile were presented
  简述了飞航导弹任务剖面、约束条件的给定、导弹的重量组成以及涡扇发动机模型。