secondary fuel 中文意思是什麼
secondary fuel
解釋
二次燃料-
Effects of different fuel - air ratios and different geometric parameters of dual - stage swirler ( such as inner diameters of the primary swirl and secondary swirl passages, outer diameters of the secondary swirl passages, vane angle of the primary and secondary swirler, the distance of the flare exit from throat etc ) on combustion performances are studied experimentally. the experimental results show that radial profiles of the outlet gas temperature 、 combustion efficiency 、 emissions of co2 、 co and nox and lean blowout are affected with different degrees by the different geometric parameters of dual - stage swirler and the arrangement of primary holes
在不同油氣比下，不同的雙級旋流器幾何參數（例如:一級與二級旋流器出口內徑d 、葉片安裝角、二級旋流器出口外徑d 、二級旋流器的喉道到出口截面的距離l和喉道前後的圓弧半徑r以及主燃孔孔布局等）對單頭部環形燃燒室的出口溫度分佈、燃燒效率、貧油熄火油氣比以及污染物（ co _ 2 、 co和nox ）排放等燃燒性能的影響規律進行了研究。 -
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 bump height and secondary wall - impingement distance were discovered to play an important role in producing a secondary space jet, reducing the quantity of fuel stuck on the wall and forming lean mixture, and their suitable values being 1. 0 - 1. 5mm and 0 - 2. 0mm respectively
發現bump高度及二次撞壁距離對撞壁油束形成二次空間射流、減少壁面燃油堆積以及形成稀混合氣有重要作用，且發現bump的高度和二次撞壁距離分別為1 . 0 1 . 5mm和0 2 . 0mm比較合適。 -
The secondary combustion, which has better controllability, and plays the most pivotal role on the overall performance of a strutjet, so the paper detailedly studied and analyzed the mechanism of fuel ' s atomization, the mechanism of fuel ' s spray burning, vital spray burning models and the combustion ' s controllability, combined with the author ' s practical investigation in the rbcc lab, finally, the author got a most simple and feasible method to control the spraying burning of liquid kerosene - - to set up an adjusting valve in the fuel pipeline
文中重點對燃油的霧化機理、燃油的噴霧燃燒機理、主要的燃燒模型和燃燒過程的可控性，展開了詳細地分析研究，並結合在rbcc實驗室的實際研究，獲得了對燃油噴霧燃燒進行調節的最簡單、可行的方法，即在燃油管路上設置流量調節閥。於是燃燒組織問題轉化為對該調節閥的開度如何施加適當控制的問題。 -
The research indicated that, if the secondary combustion chamber was looked on as a controlled object, with the adjusting valve as a input, the pressure and the temperature of a selected point on the inside wall of the combustion chamber as outputs, then such controlled system would be a strongly non - linear, time varying system with number of random disturbances, which resulted in huge difficulty to build an analyzed mathematics model for the spray burning of the liquid fuel, so that classic control methods were all invalid
研究表明，若將rbcc發動機的二次燃燒室視為一個控制對象，同時以燃燒室內壁面取定點處的壓強、溫度和調節閥的開度為輸入輸出變量，則該系統將是輸入?輸出特性非線性很強、隨機干擾嚴重的復雜時變系統。這導致建立燃油噴霧燃燒具體模型的很大困難，從而宣告了經典控制方案的失效。 -
Four conclusions were obtained : 1 ) the ideal maximum performance of rbcc engine is basically determined by the match of rbcc " s basic operating parameters such as the ratios of primary / secondary mass flow rate, total pressure, total temperature and the ratio of overall oxidant / fuel mass flow rate, etc
主要獲得如下結論： 1 ）基本工作參數的匹配，如引射比、總壓比、總溫比，決定了引射發動機最大可能獲得的性能。 -
The discussing emphases are structural and stagnation parameters of ejecting nozzles and secondary fuel nozzles
重點對喉部引射主噴管和燃料副噴管的不同結構、滯止參數進行探討。 -
Planar laser induced fluorescence ( plif ) was used to study the spray / wall impinging in constant volume vessel. the experimental result show that when fuel spray impinging on the plane wall, wall jet was formed while fuel impinging on a plane wall with a bump, when the wall jet meet the bump, a secondary jet can be formed. some parameters affecting the secondary spray were studied, including bump height, the secondary impinging distance, impinging distance and injector parameters
對傳統燃燒室和bump燃燒室內燃油空氣混合過程進行了對比研究，發現燃油撞壁以後在傳統燃燒室壁面形成壁面射流，這一層燃油濃度很高，很難與空氣混合，而在bump燃燒室內，壁面射流遇到bump后，會在空間形成二次射流，二次射流進一步能快速與空氣充分混合。 -
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 last or main injection pulse is set around tdc. when the diesel spray impinging on the combustion wall, the bump around the combustion chamber wall can strip off the wall jet and form a secondary spray in combustion chamber, so the fuel and air can mix well and homogenous
在主噴射時刻，利用燃燒室壁面的bump迅速剝離壁面射流，在空間形成二次射流，二次射流進入燃燒室空間后，再一次與空氣混合，形成相對均勻的稀混合氣。 -
The main results are : supersonic region and subsonic region can co - exist in flow path simultaneously, subsonic flow is insignificance for engine performance ; total pressure of primary rocket should be decreased when mach number is increased. in the experimental aspect, some components of ejectorjet experimental system were improved, ejectorjet experiments using alcohol as secondary fuel were conducted
由數值計算獲得的結論為：引射火箭內的一般流態為超音速區與亞音速區共存，亞音速區不具備做功能力；飛行馬赫數增大，引射火箭內更易於產生壅塞；為了獲得最佳的性能，隨著飛行馬赫數的提高，應當降低一次火箭的工作壓強。 -
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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