turbofan engine 中文意思是什麼

turbofan engine 解釋
兩具戰斗機用渦扇引擎
  • turbofan : n. 1. 渦輪通風器 （＝ turbofan engine）。2. 渦輪風扇。
  • engine : n. 1. 機械，機器。2. 引擎，蒸汽機，發動機。3. 機車，車頭。4. 工具；〈古語〉方法，手段。vt. 給…安裝發動機。
  1. The nozzle flow is composed of the main gas stream and the secondary air stream in order to simulate the nozzle of turbofan engine

    噴管中的氣流由主流燃氣和次流空氣組成，用以模擬渦扇發動機的噴管。
  2. On designing fixed - order mixed robust controller for turbofan engine

    控制器設計方法的研究
  3. Study of maps methods for turbofan engine performance seeking control

    方法在航空發動機性能尋優控制中的應用
  4. On a novel multi - objective fsqp algorithm for multi - variable nonlinear control of turbofan engine

    演算法實現渦扇發動機多變量非線性控制
  5. Numerically assessing aerodynamic stability of compression component running in turbofan engine

    渦扇發動機整機環境下壓縮部件穩定工作邊界計算方法
  6. The simulation accuracy can be improved by above model for the turbofan engine transient performance

    上述模型的建立將有效的提高渦扇發動機過渡過程性能模擬程序的精度。
  7. 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

    摘要利用飛機渦扇發動機一體化設計的思路，建立了飛航導彈渦扇發動機一體化設計的約束分析和任務分析模型並給出了算例和分析。
  8. By adjusting many variable geometry components of the engine, bypass ratio can be changed during large range ( the most 0. 25 of military fighter ). the high specific thrust characteristic of turbojet engine and the low specific fuel consumption characteristic of the turbofan engine can be realized during different flight phase by the usage of vce technology

    變幾何變循環發動機是應用於第四代多用途戰斗機的理想動力裝置，通過多個部件幾何的調節在較大范圍內改變涵道比，能夠使發動機在不同航段分別實現渦噴發動機的高單位推力性能和渦扇發動機的低油耗性能。
  9. In arbitrary curvilinear coordinate systems, three dimensional turbulent combustion flow fields of the three kinds of turbofan engine afterburner with the longitudinal heat shield 、 outer cold flow and the jet nozzle are simulated. the three - dimensional body - fitted grids are generated by an elliptical grid generation procedure and zone method

    本文在任意曲線坐標系統下對三種帶有縱向隔熱屏、外冷卻通道和尾噴管的渦扇發動機加力燃燒室的三維紊流燃燒流場進行數值模擬。
  10. 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

    簡述了飛航導彈任務剖面、約束條件的給定、導彈的重量組成以及渦扇發動機模型。
  11. The cycle parameters of missile for turbofan engine were optimized for meeting the demand of maneuverable missile, and the developing trend of missile for turbofan engine was predicted

    根據飛航導彈的要求對渦扇發動機進行了循環參數優化選擇並預測了未來渦扇發動機的發展趨勢。
  12. By using the method of aircraft and turbofan engine integrated analysis, a model of maneuverable missile and turbofan engine integrated optimum design was developed and the computational examples and the analysis were presented

    摘要利用飛機渦扇發動機一體化設計的思路，建立了飛航導彈渦扇發動機一體化設計的優化設計模型並給出了算例和分析。
  13. 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

    計算了單個可變幾何部件的調節（包括高壓壓氣機、高壓渦輪、低壓渦輪、混合器進口面積比和噴管喉道面積）對發動機穩態性能的影響。
  14. 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

    利用部件級建模方法建立了某大型渦扇發動機數學模型，採用一步通過演算法使過渡過程計算滿足實時性。
  15. And based on these, the application of sequential quadratic programming ( sqp ) to the turbofan engine performance seeking control is investigated

    並在此基礎上，運用序列二次規劃法對渦扇發動機的加、減速和加力加速等過渡過程尋優控制問題進行了研究。
  16. 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

    繼續研製、開發和生產各種系統包括戰術飛機和特種飛機（用於空中加油、空中預警和資料收集及電子對抗等使命）以及現代渦扇引擎技術。
  17. In this paper, the nonlinear real - time model of x turbofan engine is analyzed. some improvement is adopted to reduce the calculating time cost by engine model

    本文分析研究了某型渦扇發動機的非線性實時模型，對模型的迭代運算部分進行了改進，以提高模型的運算速度。
  18. Modern low bypass ratio turbofan engine is the heart of the new fighter, whose performance and aerodynamic stability greatly affect the characteristics of the new fighter

    渦扇發動機作為現代戰斗機的心臟，其性能和穩定性對戰斗機的性能和穩定性能有很大的影響。
  19. 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

    為了滿足下一代作戰飛機對推進系統的性能和穩定性要求，本文建立了壓縮系統特性和渦輪特性的新模型，並分別採用改變渦扇發動機風扇進口導流葉片、壓氣機導流葉片和前兩級靜葉片、混合室進口處內、外涵面積比和尾噴管面積，研究了其對發動機性能和穩定性的影響，進而得出了渦扇發動機變幾何擴穩的方法，為發動機變幾何擴穩研究打下理論基礎。
  20. 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

    摘要根據某埋入式進氣道試驗數據建立了計算埋入式亞聲速進氣道總壓恢復系數的經驗公式，表現為關于馬赫數、流量系數、攻角、側滑角的函數。
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