渦扇發動機 的英文怎麼說

中文拼音 [guōshānfādòngjī]
渦扇發動機 英文
fanjet
  • 渦 : 渦名詞1. （漩渦） eddy; whirlpool; vortex 2. （酒窩） dimple
  • 扇 : 扇動詞1 （搖動扇子等使空氣流動） fan 2 （用手掌打） strike with the palm of the hand; slap 3 （鳥...
  • 發 : 名詞（頭發） hair
  • 機 : machineengine
  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 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
  3. 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
  4. But such is the reliability and power of modern high - bypass turbofan engines that it has ceased to be a worry

    但現代渦扇發動機的可靠性和強勁的動力打消了人們的疑慮。
  5. 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。
  6. 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。
  7. 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。
  8. Dual - mode optimization asymmetry fuzzy logic controller design for x aeroengine mfp

    某渦扇發動機主燃油通道模糊控制器設計
  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. A general control system simulation platform of aero engines is constructed on the basis of performance simulation platform. kinds of control laws are discussed

    在控制系統模擬平臺上搭建某大型渦扇發動機和某中小型渦扇發動機的控制系統，通過模擬對控制系統模型類庫進行了驗證。
  14. Construction of weighting matrixes in mixed sensitivities h controller design for aeroengine

    渦扇發動機轉速魯棒控制器設計及試驗
  15. 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。
  16. 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。
  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. The simulation experiment has been done on a turbofan aeroengine. simulation results indicate that the neural network controller has quick response and has good performances in the full envelope

    對某型渦扇發動機飛行包線內不同狀態點進行了模擬試驗，模擬結果表明，控制器響應速度快，魯棒性好，取得了良好的效果。
  19. 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。
  20. 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。
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