空氣冷卻片 的英文怎麼說

中文拼音 [kōngqìlěngquèpiān]
空氣冷卻片 英文
air cooling fin
  • 空 : 空Ⅰ形容詞（不包含什麼; 裏面沒有東西或沒有內容; 不切實際的） empty; hollow; void Ⅱ名詞1 （天空） s...
  • 氣 : Ⅰ名詞1 （氣體） gas 2 （空氣） air 3 （氣息） breath 4 （自然界冷熱陰晴等現象） weather 5 （氣味...
  • 冷 : Ⅰ形容詞1 （溫度低; 感覺溫度低） cold:冷水 coldwater; 你冷不冷? do you feel cold?; are you feeling...
  • 卻 : Ⅰ動詞1 （後退） step back 2 （使退卻） drive back; repulse 3 （推辭; 拒絕） decline; refuse; reje...
  • 片 : 片構詞成分。
  • 空氣 : 1 （大氣） air; atmosphere 2 （氣氛） atmosphere 3 （氣閘） air brake4 pneum ; pneumo ; pneumat ;...
  1. 4 heating zones on barrel, all with air - cooling. each zone with multiple rows of copper fins for high cooling efficiency, coupled with oversized cooling fans mounted at the rear of the extruder barrel. large wattage on heaters coupled with the efficient cooling system ensures very fast heating and cooling of each zone

    機筒上有4個加熱區域，都帶有空氣冷卻裝置；每個區域含附帶大冷卻風扇的多排銅葉片可獲得高冷卻效果，高功率的加熱模塊同有效的冷卻系統相結合可以確保每個區域的快速加熱和冷卻。
  2. One cooling method that has gained increasing importance is endwall film - cooling, where coolant air is discharged though discrete holes in the inner and outer endwalls of a turbine blade passage. after leaving the holes, the coolant forms a protective layer between the hot mainstream gas and the surface that is to be protected

    目前廣泛採用的一種重要冷卻方法是渦輪葉柵端壁氣膜冷卻，該方法中冷空氣穿過渦輪葉片上內外端壁離散冷卻孔進行交換，且冷空氣流經冷卻孔后在主流熱空氣與被保護表面之間形成保護層。
  3. The blade inner channel cooling is a complex convection - conduction coupling problem. this thesis build a three - dimension. compressible turbulence model, and give a general solve method. with the geometrical model of the glossily rectangle straight channel, the rectangle straight channel with in - line arrays disturb plates, the rectangle straight channel with staggered arrays disturb plates, the rectangle straight channel with slant disturb plates, this thesis compute the flow and heat transfer condition when the cold air path though these channels, and gain the temperature field, pressure field, velocity filed, in addition. this thesis also analyze the influence of the different channel height, the different channel materials, the different channels, and gain the function relation between he nusselt number, friction factor and reynolds number. this thesis is emphasis on the new heat transfer enhancement structure, that is, disturb plates, with the comparison with the glossily channel and channel with pin fins, the heat transfer enhancement effect of the former is better, and the conclusion can be used in the design of aircraft blade

    葉片內部通道冷卻是一個復雜的對流?導熱耦合傳熱問題，本文在分析葉片內部通道冷卻的流動與傳熱情況的基礎上，建立了三維、可壓縮紊流的物理模型，得到了通用的求解辦法；利用不帶擾流片的矩形直通道、帶順排擾流片矩形直通道、帶叉排擾流片、帶傾斜擾流片的矩形直通道的幾何模型，計算了冷卻空氣通過這幾種通道時的流動與換熱情況，得到了各種不同情況下計算區域的溫度場、壓力場、速度場；在此基礎上分析了不同的通道高度、不同的葉片通道材質對葉片內部通道冷卻的影響，並整理得到了各種通道形式下，努謝爾數和阻力因子與雷諾數的函數關系；本文重點研究了新型的葉片內部通道冷卻強化傳熱措施?帶擾流片的內部冷卻通道的強化傳熱效果，通過與光滑矩形直通道、帶針肋通道的冷卻效果的比較，表明了這種新型鮚構的優勢，對于葉片內部通道冷卻結構的設計可以起到指導的作用。
  4. Clogging up of the cooling air slits in the turbine blades is primarily caused by ultrafine particles with a high specific surface area

    渦輪葉片之間冷卻空氣縫隙的堵塞主要是因為存在高比表面積的超細粒子。
  5. Measured hole mass flows and a constant static pressure mixing analysis, together with the measured losses, allowed the decomposition of the losses into three distinct entropy generation mechanisms : loss generation within the hole, loss generation due to the mixing of the coolant with the mainstream, and change in secondary loss generation in the " blade passage

    論文還進行了葉片冷卻孔質量流的測量與常靜壓氣流混合分析，結合前述氣動力損失和冷卻空氣損耗的測量結果表明，端壁氣膜冷卻的綜合損失明顯地由三個部分組成：葉片冷卻孔內產生的損失；由於冷卻空氣與主流熱空氣的混合產生的損失；二次流的變化產生的損失。
  6. Some of the air is used for cooling the turbine blades and nozzle guide vanes, and part of it is employed to cool and seal the turbine discs

    在現代航空發動機中，從壓氣機引出的壓縮空氣一部分用來冷卻渦輪葉片和渦輪導向葉片，另外一部分用來冷卻和密封渦輪盤。
  7. Film cooling of the surface of a gas turbine blade was studied in a large - scale low - speed opening wind tunnel according to actual requirement of the design of aero - engine. the surface of a gas turbine blade was cooled by cylindrical holes in the experiment, with the hole number of fifteen in stator and eight in rotor

    應航空發動機設計的要求，在大尺寸低速葉柵傳熱風洞中分別對發動機渦輪導向葉片和動葉表面的氣膜冷卻特性進行了研究，具體研究在不同氣膜孔出流時，在不同主流雷諾數和吹風比情況下葉片表面局部換熱系數的分佈規律。
  8. To satisfy the practical need of film cooling in turbine blades of aeroengine, some detailed experimental measurements on the flow field in the channel with the holes on the wall and in the holes had been completed within a wide range of aerodynamic parameters. and the interrelated numerical simulated compute had also been implemented

    本文根據航空發動機中渦輪導向葉片氣膜冷卻的實際需要，在寬廣的氣流流動參數范圍內，對葉片內冷通道的流場進行了詳細的實驗測試，同時還進行了相應的數值模擬計算。
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