turbofan engine中文是什么意思

• 两具战斗机用涡扇引擎
• 涡轮风扇发动机

• turbofan    n. 1.涡轮通风器 (＝ turbofan engin ...
• engine    n. 1.机械，机器。 2.引擎，蒸汽机，发动机。 3. ...
• afterburning turbofan engine    加力式涡轮风扇发动机
• augmented turbofan engine    加力涡轮风扇发动机
• turbofan engine cowling    涡轮风扇发动机整流罩
• high bypass ratio turbofan engine    高函道比涡轮风扇发动机
• three-spool augmented turbofan engine    三转子加力式涡轮风扇发动机
• turbofan    n. 1.涡轮通风器 (＝ turbofan engine)。 2.涡轮风扇。
• afterburning turbofan    加力式涡轮风扇发动机
• dry turbofan    干涡轮风扇发动机
• lift turbofan    升力涡轮风扇发动机
• reheat turbofan    加力式涡轮风扇发动机
• turbofan aircraft    涡轮风扇式飞机
• turbofan freighter    涡轮风扇式货机
• turbofan jet    涡轮风扇飞机; 涡轮风扇喷气发动机
• turbofan mode    涡轮风扇工作状态
• turbofan transport    涡轮风扇式运输机
• turbofan-powered    装涡轮风扇发动机的
• twin-turbofan    双涡轮风扇发动机的
• direct-lift turbofan    升力涡轮风扇发动机
• duct-burning turbofan (dbtf)    导管燃烧式涡轮风扇发动机
• high-by-pass turbofan    高函道比涡轮风扇发动机
• lift-thrust turbofan    升推力涡轮风扇发动机
• mixed-flow turbofan    混流式涡轮风扇发动机
• three-spool turbofan    三转子涡轮风扇发动机

• This experiential formula can be used in simulating steady condition , startup , acceleration work process and integrated design of cruise missile and turbofan engine so as to improve the accuracy of 1d engine performance computation
  该经验公式可用于弹用发动机稳态、起动、加速过程的计算和导弹与发动机一体化设计的数值仿真模型，从而提高发动机性能数值仿真的准确性。
• The relevance functions between total pressure recover coefficient and the parameters ( mach number , angle of attack , flow coefficient , angle of sideslip ) for subsonic submerged inlet in turbojet and turbofan engine were investigated
  摘要根据某埋入式进气道试验数据建立了计算埋入式亚声速进气道总压恢复系数的经验公式，表现为关于马赫数、流量系数、攻角、侧滑角的函数。
• By using the method of aircraft and turbofan engine integrated analysis , a model of maneuverable missile and turbofan engine integrated constrain analysis and mission analysis was developed and the computative examples and the analysis were given
  摘要利用飞机涡扇发动机一体化设计的思路，建立了飞航导弹涡扇发动机一体化设计的约束分析和任务分析模型并给出了算例和分析。
• And those characteristics of compressor and turbine are put into the steady - state design and off - design performance program of augmented turbofan engine , to calculate the influence of the geometry changing of single component on the performance of engine
  计算了单个可变几何部件的调节(包括高压压气机、高压涡轮、低压涡轮、混合器进口面积比和喷管喉道面积)对发动机稳态性能的影响。
• Furthermore , elementary study was applied to this turbofan engine transient state control , especially acceleration control process . so we can draw such a conclusion : the aero - engine control system is robust so as to meet the control specifications well
  因此我们可以得到以下结论，即航空发动机lqg ltr控制系统具有优良的鲁棒性，并且能够较好地满足航空发动机控制的其他基本要求。
• The performance seeking control algorithms are programmed , and the simulations are carried out based on the software , visual c + + 6 . 0 . the results of simulation show that it ' s feasible to apply sqp algorithm to turbofan engine performance seeking control
  并在visualc + + 6 . 0平台上编制了寻优控制算法以及发动机控制仿真程序，对文中给出的涡扇发动机过渡过程寻优控制方法进行了仿真验证。
• Continues to research , develop , and produce a variety of systems - including tactical and special purpose ( e . g . , aerial refueling tankers , airborne early warning and collection , and electronic countermeasure ) aircraft - as well as modern turbofan engine technology
  继续研制、开发和生产各种系统包括战术飞机和特种飞机（用于空中加油、空中预警和资料收集及电子对抗等使命）以及现代涡扇引擎技术。
• Two kinds of aeroengine control systems are established to illustrate the validity of the control system simulation platform . in the last part , an adaptive control algorithm library of the turbofan engine is built . simulation results of the control algorithms show that the controllers have excellent performance in the whole envelope
  此外,本文针对所建立的某大型涡扇发动机数学模型设计了一个自适应控制算法库,将已有的多种控制算法研究成果融入其中,对各种算法进行了仿真测试,取得了良好的控制效果。
• A mathematical model is developed for simulating transient performance of the turbofan engine , in which the transient heat transfer between the components and airflow , tip clearance and components efficiency changes caused by heat transfer are analyzed
  摘要以某涡扇发动机的过渡态性能模拟为研究对象，建立了过渡过程中零部件与气流之间的不稳定热交换、由于热交换引起的间隙变化以及引起的部件效率变化的数学模型，并且将此模型引入面向对象的航空涡扇发动机过渡过程性能模拟程序的框架中。
• To meet the needs for wider surge margin of the turbofan engine , a new model was developed to predict the characteristics of the fan / high pressure compressor and turbine in this thesis . several ways , including , variable inlet guide vanes of the fan , variable guide vanes of the high pressure compressor , the variable inlet area ratio of the mixer and the nozzle areas , were presented to enlarge the surge margin of the turbofan engine . meanwhile , a method of combined variable geometries for optimizing controls of inlet guide vanes of the fan , guide vanes and the first two stators of high pressure compressor , area ratio of mixer and noz zle areas was established
  为了满足下一代作战飞机对推进系统的性能和稳定性要求，本文建立了压缩系统特性和涡轮特性的新模型，并分别采用改变涡扇发动机风扇进口导流叶片、压气机导流叶片和前两级静叶片、混合室进口处内、外涵面积比和尾喷管面积，研究了其对发动机性能和稳定性的影响，进而得出了涡扇发动机变几何扩稳的方法，为发动机变几何扩稳研究打下理论基础。

• turbofan engineとは意味：ターボファン?エンジン