渦輪葉片冷卻 的英文怎麼說

中文拼音 [guōlúnyèpiānlěngquè]
渦輪葉片冷卻 英文
turbine blade cooling
  • 渦 : 渦名詞1. （漩渦） eddy; whirlpool; vortex 2. （酒窩） dimple
  • 輪 : Ⅰ名1 （輪子） wheel 2 （像輪子的東西） wheel like object; ring; disc 3 （輪船） steamer; steamboa...
  • 片 : 片構詞成分。
  • 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...
  • 渦輪 : [機械工程] turbine; worm wheel渦輪泵 [航空] turbopump; roturbo; 渦輪發動機 turbine engine; 渦輪風...
  1. Numerical simulation of leading edge film - cooling of turbine stator blades

    氣膜冷卻渦輪導向葉片流場數值模擬
  2. In this paper. the conclusion of this paper has utility meaning in analysis on turbine blades cooling after some proper correcting of the geometry structure and boundary conditions

    由於所採用的結構及計算域近似渦輪葉片的冷卻形式（主流加熱，內流通道冷卻） ，因此這種方法經過進一步的改進，可用於渦輪葉片冷卻的計算研究。
  3. 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。
  4. A new model for film cooling effectiveness computation on blade surface in a turbine cascade

    渦輪葉片型面氣膜冷卻效率的計算模型
  5. Two good examples about conjugate heat transfer problem, one with cooling method, the other without cooling inside turbine blade were investigated

    最後進一步地討論了渦輪葉片中無冷卻和有簡單冷卻通道情況下的流/熱耦合計算。
  6. Haibo huang ( mechanical engineering ) directed by jianzhong xu cooling techniques in turbine have become more important since the extra high inlet temperature in turbine

    隨著渦輪前溫度的提高，渦輪葉片的冷卻技術變得十分重要。渦輪葉片中流/熱耦合計算成為必不可少的熱環境分析手段。
  7. Touch on developing large - flow and high - pressure ratio impressor and large - enthalpy drop turbine, reducing harmful emission, solving the major problems of high - temperature blade material, cooling, protective coating and single - grain blade casting, and comfirm some important manufacturing techniques

    涉及了開發大流量高壓比壓氣機、大焓降渦輪，降低有害排放量，解決高溫葉片的材料、冷卻、保護塗層及單晶葉片鑄造等主要問題，並確認了一些關鍵的製造技術。
  8. 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。
  9. A parameter has been defined to account for both the heat transfer enhancement and pressure loss caused by different shapes and configuration of pin fin arrays and the optimization analysis shows that cube - shaped pin - fin arrays can be viable alternatives for pedestal cooling in a blade trailing edge

    本文提出了一個強化換熱有效性系數來綜合考慮擾流柱換熱和壓力損失的效果，並用它對各種擾流柱進行了優化分析，優化結果表明方形擾流柱排在渦輪葉片尾緣區冷卻結構設計中是優先考慮的一種結構型式。
  10. Short pin - fin arrays are often used for the cooling of turbine airfoils, particularly in the trailing edge

    短擾流柱排被廣泛應用於渦輪葉片的內部冷卻結構中，尤其是葉片尾緣區域。
  11. The experimental results showed that the film cooling effectiveness were mainly determined by blowing ratios

    該實驗結果對渦輪葉片型面氣膜冷卻的實際工程設計研究有重要意義。
  12. To compare with great deal of experimental data, the results show the improved method could be used as a generalized design methodology of film cooling for turbine blade. predictions of span - wise averaged effectiveness are made with a two - dimensional boundary layer code using the low reynolds number k - two - equation turbulent model

    研究並發展了用低雷諾數k -紊流模型為基礎的氣膜冷卻計算方法，將前人針對平板提出的摻混模型推廣應用於渦輪葉片型面，得到了與實驗數據符合良好的結果。
  13. But the outer wall of the turbine blades was washed by high temperature gas, the internal passage was cooled by cooling gas which was induced from the compressor

    而渦輪葉片的特點是外部受高溫燃氣的沖刷，內部通道通過從壓氣機引來的冷氣進行冷卻。
  14. 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。
  15. 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。
  16. 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。
  17. The surface of a gas turbine blade was cooled by four rows of cylindrical holes in the experiment

    實驗中對渦輪葉片採用四排氣膜孔的冷卻方案，氣膜孔為圓柱形。
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