combustion nozzle 中文意思是什麼

combustion nozzle 解釋
燃燒噴嘴
  • combustion : n. 1. 燃燒，發火，點火。2. （有機體內營養料的）氧化。3. 騷動。
  • nozzle : n. 管嘴；噴嘴；〈俚語〉鼻子。 a jet [propelling] nozzle 【火箭】尾噴管。
  1. The nozzle mix burners feature short flames, wide turndown ranges and very stable combustion

    燒嘴混合爐頭具有短焰，寬范圍，非常穩定燃燒的特點。
  2. Although a dual - mode scramjet ' s configuration is simple and mainly consists of inlet, combustor and wake nozzle, its working process is complicated, especially in the combustor, involving a lot of subjects, including hypersonic aerodynamics, combustion chemistry, etc. the inner flow of a combustor is three - dimensional and complicated, including the interaction of shock wave, deflagration, vortex and boundary layer, and so on

    它涉及到高超聲速空氣動力學、燃燒化學、擴散傳質等多門學科；其內部的實際流動是復雜的三維流動過程，充滿著激波、膨脹波、燃燒波、各種渦系、附面層及其相互之間的干擾，因此，燃燒室問題是整個發動機研究的關鍵所在。
  3. Based on the analysis of the combustion in cylinder, the thorough research of multiparameters ( engine speed, load, ignition timing, injection timing, injection nozzle type, compression, ignition pattern etc. ) on methanol engine combustion cyclic variations is made on a 1130 single - cylinder diesel engine fueled with methanol

    在燃用甲醇燃料的1130單缸柴油機上，通過缸內燃燒分析，對影響甲醇發動機循環變動的各種因素（轉速、負荷、點火提前角、噴油提前角、噴油嘴類型、壓縮比、點火方式等）進行了詳細的研究。
  4. Fuel injection nozzle used on small bore diesel engine with swirl combustion chamber

    小缸徑渦流室柴油機用噴油嘴的研究
  5. The possible reasons are as follows ; discharge valve damage or over load operation of diesel engine, or leakage of nozzle, or the incomplete combustion in the cylinder because not enough fresh air was pumped

    可能的原因如下；排氣閥損壞或柴油機超負荷運轉，或油嘴漏泄，或由於進氣量不足導致燃燒不完全，等等。
  6. 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。
  7. 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。
  8. The main achievements are as follows : 1 it ' s for the first time to extensively investigate effects of main combustion system parameters such as plunger diameter, plunger stroke, fuel delivery advanced angle, valve opening pressure of nozzle on performance of dme engine. the parameters are optimized

    取得的主要成果有： 1系統地研究了油泵柱塞直徑和行程、供油提前角、噴嘴啟噴壓力等發動機燃燒系統主要參數對二甲醚發動機性能的影響，優化了這些參數。
  9. In this paper, simple reacting flow model in solid - propellant ducted rocket combustor based on eddy break - up model is established. the model is used to simulate the three - dimensional combustion flowfields in an experimental motor. some factors how to affect the combustion efficiency are discussed in the paper, including air intake and gas generator nozzle

    本文基於簡單反應的旋渦分裂模型，建立了固體火箭沖壓發動機補燃室內的湍流燃燒模型，並在該模型下對某實驗發動機進行了三維數值模擬，研究了補燃室設計參數包括進氣道出口設計參數和燃氣發生器噴管設計參數對燃燒效率的影響。
  10. 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
  11. In the analysis i - deas master series 8. 0 program is used. the static strength analysis models of combustion chambers, nozzle, plate closure are established, and the stress and displacement of them are calculated

    文中建立燃燒室、擋藥板、噴管等在不同的受載條件下的有限元模型，求出應力場和變形。
  12. 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。
  13. 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。
  14. The physical and chemical processes of nozzle atomization and the evaporation, mixing and combustion of propellant drop flow are very complex. for the reason, the researches on nozzle are still based on the experimental research now in or abroad

    由於噴嘴霧化及其噴霧流的蒸發、混和和燃燒是一個非常復雜的物理化學過程，目前國內外對噴嘴的研究仍以模型實驗研究為主。
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