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turbofan

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turbofan n.1.渦輪通風器 (＝ turbofan engine...

n. 1.渦輪通風器 (＝ turbofan engine)。 2.渦輪風扇。 “afterburning turbofan“ 中文翻譯：   加力式渦輪風扇發動機“dry turbofan“ 中文翻譯：   干渦輪風扇發動機“lift turbofan“ 中文翻譯：   升力渦輪風扇發動機“reheat turbofan“ 中文翻譯：   加力式渦輪風扇發動機“turbofan aircraft“ 中文翻譯：   渦輪風扇式飛機“turbofan engine“ 中文翻譯：   兩具戰斗機用渦扇引擎; 渦輪風扇發動機“turbofan freighter“ 中文翻譯：   渦輪風扇式貨機“turbofan jet“ 中文翻譯：   渦輪風扇飛機; 渦輪風扇噴氣發動機“turbofan mode“ 中文翻譯：   渦輪風扇工作狀態“turbofan transport“ 中文翻譯：   渦輪風扇式運輸機“turbofan-powered“ 中文翻譯：   裝渦輪風扇發動機的“twin-turbofan“ 中文翻譯：   雙渦輪風扇發動機的“afterburning turbofan engine“ 中文翻譯：   加力式渦輪風扇發動機“augmented turbofan engine“ 中文翻譯：   加力渦輪風扇發動機“direct-lift turbofan“ 中文翻譯：   升力渦輪風扇發動機“duct-burning turbofan (dbtf)“ 中文翻譯：   導管燃燒式渦輪風扇發動機“high-by-pass turbofan“ 中文翻譯：   高函道比渦輪風扇發動機“lift-thrust turbofan“ 中文翻譯：   升推力渦輪風扇發動機“mixed-flow turbofan“ 中文翻譯：   混流式渦輪風扇發動機“three-spool turbofan“ 中文翻譯：   三轉子渦輪風扇發動機“triple-turbofan transport“ 中文翻譯：   三臺渦輪風扇式運輸機“turbofan engine cowling“ 中文翻譯：   渦輪風扇發動機整流罩“turbofan power plant“ 中文翻譯：   渦輪風扇動力裝置“twin-shaft turbofan“ 中文翻譯：   雙轉子渦輪風扇發動機“turboexpander“ 中文翻譯：   膨脹渦輪; 渦輪膨脹機“turboexiter“ 中文翻譯：   渦輪勵磁機

turbogenerator

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。

This paper studies the helicopter , the propeller - driven aircraft and the turbofan jet airplane echo modulating feature parameter model and analyses the echo signal feature . it gains the target echo ’ s the cyclical modulation feature by using the complex ar frequency range bispectrum slice . because traditional method in extraction airborne radar ’ s radiant signal feature time has certain insufficiency , this paper proposes the approximate entropy and the norm entropy as the passive feature parameter in the airplane 由于傳統方法等在提取機載雷達輻射源信號特征的時候存在著一定的不足,本文提出把近似熵和范數熵作為飛機目標識別的無源特征參數,給出了提取相應特征熵的算法,實現對機載雷達輻射源信號的識別,通過和機載雷達類型的匹配,實現對目標的識別。

In the paper , useful attempts and research on adaptive control are developed for a turbofan engine . a model reference adaptive control ( mrac ) using input and output measurements and pi adaptive law are applied to aeroengine multi - variable control system . simulation results show that controller avoids the measurement of full states variables and has good control performance 將利用輸入輸出測量值的模型參考自適應控制方法和比例?積分型自適應律應用于航空發動機多變量控制中，并進行了數字仿真研究，結果表明控制器有效地避免了全狀態量的測量，并獲得好的動、靜態性能。

Regarding the development of control system , we studied a non - linear control method , variable structure control method , elaborating the basic concepts , methods of design and the solution of buffeting problem , modelling the linearization variable of a certain turbofan engine , for which the variable structure control system was designed and verified by a great many simulations 就控制系統設計問題,本文主要研究了一種非線性的控制方法? ?變結構控制方法。闡述了變結構控制基本概念、設計方法和抖振問題的解決,建立了某渦扇發動機線性化狀態變量模型,并為其設計了變結構控制系統。最后進行大量的仿真,以驗證其有效性。

A new modeling method is applied to build the real - time mathematical model of the turbofan engine . in this model , the relations of the engine components “ parameters can be expressed by analytical formula , which avoid the complex and time - consuming iterations in the components computing process 本文應用的發動機實時數學模型，提出了一種新的實時模型建模方法，該方法通過將發動機部件參數間的關系通過解析式表示，從而避免了部件計算過程中復雜而又耗時的迭代過程。

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于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。

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，并分別采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。

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 摘要以某渦扇發動機的過渡態性能模擬為研究對象，建立了過渡過程中零部件與氣流之間的不穩定熱交換、由于熱交換引起的間隙變化以及引起的部件效率變化的數學模型，并且將此模型引入面向對象的航空渦扇發動機過渡過程性能模擬程序的框架中。

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,本文針對所建立的某大型渦扇發動機數學模型設計了一個自適應控制算法庫,將已有的多種控制算法研究成果融入其中,對各種算法進行了仿真測試,取得了良好的控制效果。

Along with the advent of the highly efficient turbofan jet engine , used today on the majority of commercial aircraft , came a new and challenging problem for maintenance personnel . the repair and replacement of the abradable liner seal , sometimes also known as the fan track . . 在大多數商用飛機使用高效率的渦輪風扇噴氣發動機時代到來的同時，飛機維修人員也面臨著新的挑戰，即如何修理和替換發動機上的耐磨損內襯密封條，有時候也被稱為風扇軌道

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 繼續研制、開發和生產各種系統包括戰術飛機和特種飛機（用于空中加油、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。

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平臺上編制了尋優控制算法以及發動機控制仿真程序，對文中給出的渦扇發動機過渡過程尋優控制方法進行了仿真驗證。

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 因此我們可以得到以下結論，即航空發動機lqg ltr控制系統具有優良的魯棒性，并且能夠較好地滿足航空發動機控制的其他基本要求。

In the start stage , working points linear state space models for this turbofan aero - engine have been derived using the stone method . and the importance of proper scaling the plant to achieve the desired target - feedback - loop ( tfl ) is emphasized 首先，利用斯通法計算得到發動機的若干狀態空間模型即系統矩陣，并且強調了合理地對參數進行歸一化對于尋找期望的目標反饋回路的重要性。

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。

The constrain - analyzed results and the mission - analyzed results of some maneuverable missiles indicate that the model of maneuverable missile and turbofan integrated constrain analysis and mission analysis is feasible and available 對飛航導彈的約束分析計算結果和任務分析計算結果表明，建立的飛航導彈渦扇發動機一體化約束分析與任務分析模型是合理可行的，具有很好的工程實用價值。

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并給出了算例和分析。

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。

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 該經驗公式可用于彈用發動機穩態、起動、加速過程的計算和導彈與發動機一體化設計的數值仿真模型，從而提高發動機性能數值仿真的準確性。