nozzle area 中文意思是什麼

nozzle area 解釋
噴管截面積
  • nozzle : n. 管嘴；噴嘴；〈俚語〉鼻子。 a jet [propelling] nozzle 【火箭】尾噴管。
  • area : n. 1. 面積；平地；地面。2. 空地；〈英國〉地下室前的空地。3. 地區，地方；〈比喻〉區域；范圍。
  1. Method of use : first dissolve the irrigation in solution as per the specified proportion, then push the irrigating nozzle to the focus, and place the absorbing tube into the solution bottle ; hold the air cell and pinch it repeatedly to wash the focus area with the solution passing through the nozzle

    使用方法:先將沖洗劑按規定比例化成溶液，沖洗咀推入患處，吸液管放入存放溶液的容器中，手握氣囊反復捏擠，沖洗液即可通過沖洗咀沖洗患處
  2. The spray area of this series of nozzle is formed by one or several continuous hollow cone - shape rings of concentric circles. the nozzle aperture will not be blocked up. it is mainly used for flue elimination, cooling of steel - making convertor. and redistributing in all kinds of washing towers. it also can be used for jar cleaning. used in cooling tower and fire apparatus

    該系列噴嘴的噴霧區域是由一個或幾個連續的同心圓空心錐環組合而成，不易阻塞，主要用於煉鋼轉爐煙道除塵降溫及各種洗滌塔里的再分佈，也可用於清洗罐、冷卻塔、消防設備中。
  3. The area correction is largest at the nozzle exit, where it may be of the order of 3%.

    面積修正在噴管出口處最大，約為3左右。
  4. Design optimization of chamber pressure and nozzle area expansion ratio of solid rocket motors

    固體火箭發動機燃燒室壓強及噴管擴張比優化設計
  5. Controllable area nozzle

    可調截面噴管
  6. The nozzle diameter and the ejection pressure have a great effect on the flow rate 、 droplet cone shape 、 droplet size and cover area of fluid pesticide

    噴嘴孔徑和噴出壓力在很大程度上影響著藥液的流量特性、霧錐形狀、霧滴大小和覆蓋面積。
  7. According to the experimental data of droplet size 、 particle spectrum range 、 droplet cone shape 、 flow rate 、 cover area and cover area rate which obtained through changing the pressure of power sprayer and the nozzle diameter in greenhouse ， this paper made comparative analysis on atomizing performance in same pressure and different nozzle type between same nozzle type and different pressure. the conclusion is that : the ejection rate and the droplet cone shape change with the variation of pressure and nozzle diameter ， average particle diameter decreases obviously and particle quantity increases obviously with the increase of pressure and decrease of nozzle diameter. these results will lay experimental foundation for precise spraying 、 low pollution and highly effective operation

    本文根據溫室內動力噴霧機壓力與噴嘴孔徑的變化影響霧滴大小、粒譜范圍、霧錐形狀、流量、覆蓋面積及覆蓋面積率的試驗數據，對相同壓力下不同噴嘴型號和相同噴嘴型號時壓力不同時的微粒化性能進行對比分析和研究，得到如下結論噴出量與霧錐形狀隨著壓力和噴嘴孔徑大小變化而變化；平均粒徑隨著壓力的增加和噴嘴孔徑的減小而明顯減小；粒數隨著壓力的增加和噴嘴孔徑的減小而明顯增多，為精噴量、低污染、高防效的防除作業奠定了實驗基礎。
  8. The flow field structure of the power - turbine variable - area nozzle stage of a marine gas turbine

    船用燃氣輪機動力渦輪可調導葉級的流場結構
  9. Static removal lonizing air gun / hs static removal lon - izing air nozzle lonizing air gun / nozzle is a kid of effective static removing instrument, which swiftly blows the great deal of cation and anion occurred in the ion occurring in - strument with high pressure airflow to the area to be re - moved the static, neutralizes the static charge clooecting in the object, at the same time, high speed ion airflow blows off the dust attracted by static, and prevents it to attract dust again

    離子風槍/風嘴是一種高效的靜電消除裝置，通過高壓氣流將離子發生裝置所產生的大量正負離子迅速吹向所要除靜電的區域，中和物體上所積累的靜電電荷，同時，高速離子氣流將靜電吸引的塵粒吹除，並阻止其再次吸收塵埃粒子。
  10. The ratio of the diameter of nozzle to the diameter of vessel has greater effect on the distribution area of high stress in plastic deformation stage

    對于均處于塑性階段的結構而言，開孔率的大小對高應力區的分佈范圍影響較大。
  11. 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。
  12. The conveying parameters were relatively optimized by adjusting the throat area of adjustable laval nozzle and pressure parameters, so that the foodstuff particle breaking rate during pneumatic conveying was decreased at certain extent

    通過調節可調式拉法管的喉徑以及各壓力參數實現了輸送參數的相對最優，在一定程度上減輕了糧食顆粒在輸送過程中的破碎率。
  13. Cfd is also used to get the data of performance parameters of the nozzle at different nozzle pressure ratio, different nozzle area ratio and different geometric defected angle. the theory of function approximation is used to establish the transient model of thrust vectoring with the data calculated

    本文通過cfd計算獲得矢量噴管的性能參數，如流量系數、推力系數以及有效推力矢量角等與矢量噴管壓比、面積比以及幾何偏轉角之間的關系數據，並利用函數逼近理論建立了矢量噴管的動態數學模型。
  14. 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。
  15. To meet the needs for wider surge margin of the turbofan engine, a new model was developed to predict the characteristics of the fan / high pressure compressor and turbine in this thesis. several ways, including, variable inlet guide vanes of the fan, variable guide vanes of the high pressure compressor, the variable inlet area ratio of the mixer and the nozzle areas, were presented to enlarge the surge margin of the turbofan engine. meanwhile, a method of combined variable geometries for optimizing controls of inlet guide vanes of the fan, guide vanes and the first two stators of high pressure compressor, area ratio of mixer and noz zle areas was established

    為了滿足下一代作戰飛機對推進系統的性能和穩定性要求，本文建立了壓縮系統特性和渦輪特性的新模型，並分別採用改變渦扇發動機風扇進口導流葉片、壓氣機導流葉片和前兩級靜葉片、混合室進口處內、外涵面積比和尾噴管面積，研究了其對發動機性能和穩定性的影響，進而得出了渦扇發動機變幾何擴穩的方法，為發動機變幾何擴穩研究打下理論基礎。
  16. More than 200 different condition 3d viscosity steady flow fields in the thrust vectoring nozzle at different nozzle pressure ratio and different nozzle area ratio and different geometric defected angle is calculated by the program developed. and the related performance parameters are acquired by numerical simulation

    利用該程序計算了某矢量噴管在不同的壓比、面積比和幾何偏轉角下的200多種三維有粘流場，獲得了矢量噴管的性能數據。
  17. 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。
  18. And the affect of nozzle pressure ratio, nozzle area ratio and geometric defected angle on the performance parameters is also investigated. 4

    研究了影響矢量噴管性能的因素，研究了壓比、面積比以及幾何偏角對矢量噴管性能的影響。
  19. ( 3 ) on the background of the development of an ignition rocket, some application investigations have been carried out. some parameters related to water - resistant ignition mixture, the charge of ignition rocket, such as heat - flow, density of charges, structure of charges, coating and its process, area ratio of nozzle and high temperature corrosion of the nozzle, were calculated and studied, respectively. on the basis of the above studies, an ignition rocket was successfully developed

    （ 3 ）進行了應用研究，以某系列點火發動機的研製為背景，分別對耐水點火藥用作點火發動機裝藥所涉及的能量衡算、裝藥密度、裝藥結構、包覆及其工藝、喉面比及噴口燒蝕等問題進行了分析和實驗研究，在這些研究的基礎上成功地製作了一種點火發動機。
  20. 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。
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