turbofan 中文意思是什麼
turbofan
解釋
n. 名詞 1. 渦輪通風器 （＝ turbofan engine）。2. 渦輪風扇。
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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。 -
Robust controller design and experiment of turbofan
航空發動機多變量魯棒數字控制器的設計 -
On designing fixed - order mixed robust controller for turbofan engine
控制器設計方法的研究 -
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 -
General specification of turbojet engines and turbofan engines for aircraft
飛行器用渦輪噴氣及渦輪風扇發動機通用規范 -
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 -
Analysis of some typical faults of hydraulic system of turbofan jet fuel - supplying governing system
發動機供油調節器液壓系統典型故障分析 -
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 -
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。 -
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。 -
A component level aerothermodymamic model of a turbofan aeroengine is created in this thesis using oo technology
本文基於面向對象技術建立了某型雙軸渦扇航空發動機的部件級氣動熱力模型。 -
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。 -
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。 -
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。 -
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。 -
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。 -
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。 -
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 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。 -
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。
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