can combustor 中文意思是什麼

can combustor 解釋
筒形燃燒室
  • can : n 1 〈美國〉罐頭，聽頭（＝〈英國〉tin）；（裝液體的）鐵罐，玻璃罐（等）；一罐（之量）；茶杯。2 〈...
  • combustor : n. 【機械工程】燃燒室。
  1. This article aims at the boiler ' s problems in operation : 1 ) under nominal load, the smoke temperature at the outlet of hearth reaches 1200, far more exceeds 1050 the original designed temperature. this will always result in slag inside boiler and the temperature of overheater ' s pipe superheat, so that boiler cannot take nominal load and all these influence boiler ' s nomal operation heavily, 2 ) this article also studied the reason why the assistant oil becoming necessary when coal changes. during the nomal operation, many factors ( makeup of combustor and its disposal, smirch and encrust of water wall, excessive air coefficient, temperature of primary air, coal type and density of coal dust ) can deviate the designed working conditions, then affect the boiler ' s nomal operation

    本文針對該鍋爐在實際運行中存在的問題：在額定負荷下，爐膛出口超溫、低溫段過熱器前煙溫高達936 ，遠遠超過815的設計值；噴燃器四周水冷壁結焦嚴重，過熱器管壁溫度超標，無法帶上額定負荷；甚至有時因燃煤質量的變化，必須投油助燃的嚴重情況進行了分析研究。在實際生產過程中，燃燒器的結構、布置，水冷壁的粘污、結垢，過剩空氣系數、一次風溫、煤種及其濃度變化等許多因素都會偏離鍋爐的設計工況，從而影響爐內的傳熱和燃燒，造成爐膛出口超溫、水冷壁結渣等問題。
  2. Results from this thesis concluded that numerical simulation can be applied to study " effect of varying the incident angle of dilution air on the performance of the gas turbine combustor "

    本文針對某種航空發動機火焰管模型結構，採用數值模擬方法對「摻混空氣噴射角度對燃燒室性能的影響」這一問題進行了探討。
  3. The combustor do n ' t fail if transient rise of temperature field is neglected, the stress field of combustor can n ' t cause gas film wall rupture. 2. combustor ' s creep and relaxation is calculated in steady temperature field, the results show that creep and relaxation is not main reason destroying combustor chamber

    對穩態溫度場下的蠕變鬆弛計算表明，高溫下的蠕變鬆弛促使火焰筒的熱應力下降，在所考慮的條件下穩態溫度場導致火焰筒的蠕變變形不是火焰筒破壞的主要原因。
  4. While the speed is very large, the fuel - air mixing behind the airstream is decreased and the span that the fuel flow in the second combustor is reduced, so the combustion efficiency is decreased, h ) if the fuel streams impinge with the airstreams directly at the air - inlet exit, it make against increasing the combustion efficiency, i ) increasing air - to - fuel ratio within proper range can increase the combustion efficiency

    增加燃氣噴射速度有利於增強迴流區強度，頭部燃燒溫度上升，但速度太大則會減弱燃氣同空氣在進氣道下游的摻混燃燒，減少燃氣在室內停留時間，燃燒效率降低； 8燃氣射流與空氣流在進氣道出口直接撞擊不利於燃燒效率的提高； 9在適當范圍內增大空燃比能顯著提高燃燒效率。
  5. On the contrary, if temperature gradient is relatively low, combustor only undergo low compressive stress at high temperature. the combustor of engine has a longer life length. these results can provide some reference for maintain and design for gas turbine combustor

    分析也表明，若在起動過程中筒壁的溫度梯度較為平緩，火焰筒的氣膜唇邊在起動完成後始終受微小的壓應力作用，火焰筒的壽命可以大大延長。
  6. The mixing of air and fuel can be improved, d ) adding air distributary valve at exit of air - intake can increase the amount of air bifurcated into the dome region, so the value of combustion efficiency is increased, e ) increasing gas generator nozzle number can improve combustion characteristics in the dome region and produce good condition for combustion progress, f ) when the fuel streams are ejected into the second combustor with a angle, the combustion efficiency is increased, g ) when the speed of fuel streams increased, the intension and temperature of recirculation region is improved

    兩個進氣道在補燃室周向成180度布置，有利於增強燃氣同空氣的摻混； 4在進氣道出口增加空氣分流擋板，有利於增加進入頭部的空氣流量，提高燃燒效率； 5增加燃氣噴管數量能增強燃氣同空氣在頭部的燃燒效果，為燃燒的進行創造良好的條件； 6
  7. Scramjet combustor may realize the subsonic - combustion mode and supersonic - combustion mode respectively based on the control of fuel in variable flight conditions. isolator has great effect on mode transition and preventing unstart of inlet. inlet can be unstarted by raising the back pressure result from chemical energy release in the combustor

    計算研究表明，在相同的來流條件下，供油規律對燃燒室的工作模態有著重大的影響；在不同的來流條件下，可以通過調節供油規律使燃燒室分別實現亞燃模態和超燃模態；隔離段對防止燃燒引起的壓力升高對進氣道的干擾和燃燒室的模態轉換具有重要的作用。
  8. With computations and analysis, the comprehension on the mixing and combustion process is increased, and some significative results are listed below : a ) there are three recirculation regions and one vortex region in the combustor, and these recirculation regions affect the combustion process deeply, b ) increasing side - arm angle and moving side - air inlet position toward the fuel inlet can improve mixing and combustion characteristics, and increase the combustion efficiency, c ) when the angle between two air - inlets equals to 180

    通過計算與分析，增進了對補燃室內摻混燃燒過程的理解，為固體火箭沖壓發動機補燃室設計提供了一些有意義的結果： 1補燃室內的流動十分復雜，存在三個迴流區和一個旋渦區，迴流區對摻混燃燒過程有重要影響； 2增大空氣入射角度、向前移動進氣道出口位置有利於增強頭部迴流區強度，增強摻混效果，燃燒效率上升； 3
  9. In addition, in the experiments i simulated the affection of cws jet flow to the combustor ' s aerodynamic field. from the results, we can get the affection of the location of air gun to the aerodynamic field

    本文首先對3 . 5t h時的水煤漿旋流燃燒器進行了實驗研究，並採用了k -雙方程模型計算了該燃燒器的出口流場分佈。
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