secondary nozzle 中文意思是什麼
secondary nozzle
解釋
二級噴嘴-
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。 -
The effects of such elements as primary flow total pressure, flow rate, degree of fuel rich, nozzle structure, flying speed and secondary combustion on ejecting mode performance were researched. it was found that thrust augmentation can be achieved on the condition that the flying mach number is above 0. 7. to deeply analyze thrust augmentation mechanism in low speed range, the research was further continued by changing secondary combustion organization and aft - body configuration
研究了一次流總壓、流量、富燃程度、噴管結構、二次流來流速度、二次燃燒組織對引射模態性能的影響，發現實驗樣機構型在0 . 7ma以上的飛行條件下可以獲得推力增強，而在0 . 7ma以下無推力增強。 -
The simulation results show the obvious effect of " stratified and staggered impinging stream type multiple - nozzle secondary air " on eliminating soot
在理論上證明了煤無煙燃燒鍋爐「多孔分層錯列撞擊流」式二次風在消除碳黑方面具有明顯的效果。 -
The conclusion that the optimal secondary nozzle exit area generating the maximum thrust agrees well with the numerical simulation, indicating that the exit area of secondary nozzle should be optimized according to structure and flow parameters during design
表明在引射火箭設計時，應結合引射火箭的結構和流動參數對二次噴管出口面積進行優化設計，以達到最佳推力性能。 -
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。 -
But the real performance can be obtained is mainly determined by the ejected secondary mass flow rate, the mixing degree, the mixing efficiency, and the secondary combustion efficiency can be obtained. 2 ) the ejected secondary mass flow rate, the mixing degree and the mixing efficiency are synthetically affected by the configuration of rbcc engine, especially the mixer and the primary nozzle, in which the primary nozzle, including shape, number and distribution mainly determines the mixing degree ; while the mixer configuration primarily determines the mixing efficiency
而實際能達到的性能則取決于實際的引射比及兩種流體的實際摻混程度、摻混效率和二次燃燒效率； 2 ）引射發動機的構型，包括后體及一次流噴管的形狀、數量、配置等，對引射進來的二次流量、一次流和二次流之間的摻混程度和摻混效率起著主要作用。 -
The effect of secondary fuel nozzle location, the mass flow rate of secondary fuel and outlet area of ejectorjet were studied. the main results are : the geometry structure of ejectorjet can be compatible with other rbcc operation modes by secondary combustion organization ; the distribution of secondary fuel on ejectorjet cross section is significant for secondary combustion stability. spi combustion organization method is promising
實驗研究了二次燃料噴注位置、二次燃料噴注量、后體出口面積對引射火箭性能的影響，得到的結論為：通過燃燒組織，引射火箭模態可以和其他工作模態（亞燃超燃）共用燃燒室而不需做大的幾何變化；二次燃料在引射火箭通道截面上的分佈對于引射火箭的穩定工作有重要意義。 -
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。 -
Characteristic of flow - fields at throat of oxidant nozzle, way to separate the equivalent three - nozzle, ejecting effect of different parameters and engineering situations have been demonstrated. effect of distance between secondary flows, the jet angle and the total pressure on the status of flow - fields, has been studied. reactive flow in a hyten nozzle with dimension that was primarily determined has been simulated
研究了喉部引射主噴管的流場特徵、主噴管等效的三噴管分離方法和不同參數的引射結果以及相關的工程問題；同時還研究了hyten的流場特徵，不同副噴管間距、注入角度和總壓對流場參數的影響。 -
These measures are as follows : shorten the primary wind intervals to improve thermal load of the burner ; reduce the size of hypothetical circle of contact to prevent the flame from splashing ; use nozzles with larger height / width ratio to increase the effusive rigidity, so as to increase the jet flow depth of secondary wind into the main jet flow ; use a higher primary wind velocity to increase its jet flow rigidity ; use a special flame holder structure of the primary nozzle, so as to improve
這些技術措施主要有:縮小一次風間距以提高燃燒器區域熱負荷;縮小假想切圓防止火焰刷墻;採用高寬比較大的二次風噴口以增加射流剛性，提高二次風射流進入主射流的深度;採用較高的一次風速來提高一次風射流剛性;一次風噴口採用特殊穩燃結構;提高下二次風的托粉能力。 -
By orthogonal test, analyze the influence of such factors as nozzle diameter, vacuum degree and sowing speed on the performance specifications of the drill, identify them as primary and secondary, and work out the horizontal combination of the favorable factors
通過正交試驗，分析出吸嘴孔徑、真空度和播種速度等因素對播種機工作性能指標的影響情況，得出因素影響的主次順序，找出較優因素水平組合。 -
The influence of primary flow and secondary nozzle geometry on ejector effect and thrust was investigated, and the approach to increase thrust of rocket ejector was found gradually
研究了一次流參數和二次噴管結構對引射效能和發動機推力的影響，找到了逐步提高推力的措施。
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