bypass ratio 中文意思是什麼
bypass ratio
解釋
涵道比-
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。 -
These variable geometry components include high pressure - compressor, high - pressure turbine, low - pressure turbine, inlet area ratio of mixer and main nozzle throat area. the results of calculation show that the adjusting of low - pressure turbine and mixer has a remarkable effect on the performance of engine and bypass ratio
計算結果表明，低壓渦輪和混合器的調節對發動機的性能和涵道比的影響尤為顯著；在其它部件幾何結構不同時，單個部件幾何調節后，發動機性能的變化趨勢是不同的。 -
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。 -
The experimental results indicates that the secondary mass flow increases with increasing of primary mass flow rate, but the bypass decrease because the primary mass flow rate increase more rapidly than secondary mass flow. the expansion configuration shows low thrust property due to low pressure in flow path. the secondary nozzle changes the pressure distribution in ejector combustor, and decreases bypass ratio, but obtain more completely mixing
結果表明：二次流流量隨著一次流流量的增加而增加，由於二次流流量的增加速度低於一次流，引射系數減小；在純擴張式結構實驗中，引射燃燒室壓強很低，難以實驗推力增強；二次噴管改變了引射燃燒室的壓強分佈，降低了引射系數，改善了混合狀況能；對于本文的實驗結構，存在一個最優的二次噴管出口面積，使引射火箭推力最大，同數值模擬結果相吻合。 -
The results indicate that with decrease of exit area of secondary nozzle, the bypass ratio is decreasing, and the static pressure in integrated ejector combustor is increasing, and mixing condition becomes better. there exists an optimal exit area of secondary nozzle to get maximum thrust of rocket ejector
結果表明：引射能力隨著二次噴管出口面積的減小而減小；整體式引射燃燒室壓強隨著二次噴管出口面積的減小而上升，混合隨之更為充分；存在一個最優的二次噴管出口面積，使發動機推力最大。 -
It is shown that when the exit area of secondary nozzle and the fuel / oxidizer ratio is fixed, the increase of mass flow rate of secondary flow lead to the decrease of velocity of mixed flow, and increase of total mass flow rate. the synthetical result of these two phenomenon cause the increase of thrust of rocket ejector, but the increasing magnitude is relatively small, indicating that these is no necessary to claim large bypass ratio in rocket ejector design. in the comparison between two configurations, the typical one has better performance, indicating the importance of pressure ratio
結果表明：在固定二次噴管出口面積和氧燃比的條件下，二次流（引射空氣流）流量的增加引起混合氣體出口速度的下降和總流量的增加，二者綜合作用使發動機推力增加，但增幅不大，表明在設計發動機結構和工作參數時，不必過分追求大的引射系數；兩種結構的性能對比分析表明了增壓比對引射火箭性能的提高具有重要意義；對引射火箭的熱力循環分析同樣表明，增壓比對于提高發動機性能非常關鍵。
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