渦輪風扇 的英文怎麼說

中文拼音 [guōlúnfēngshān]
渦輪風扇 英文
turbo fan
  • 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...
  • 風 : Ⅰ名詞1 （空氣流動） wind 2 （風氣; 風俗） practice; atmosphere; custom 3 （景象） scene; view 4 ...
  • 扇 : 扇動詞1 （搖動扇子等使空氣流動） fan 2 （用手掌打） strike with the palm of the hand; slap 3 （鳥...
  • 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...
  • 風扇 : 1. （電扇） electric fan;2. [機械工程] fan; blower; ventilator
  1. Cutaway of the pw 4000112 - in ( 284. 48cm ) gas turbine engine, showing fan bypass section

    渦輪發動機剖面圖，展示風扇旁路部分。
  2. General specification of turbojet engines and turbofan engines for aircraft

    飛行器用渦輪噴氣及渦輪風扇發動機通用規范
  3. Check no damage for fan blades and turbine blades

    檢查風扇葉片和渦輪葉片無損壞跡象。
  4. 1 testing methods for turbo - fans erratum 1

    渦輪風扇的試驗方法
  5. High - thrust turbine fan engine

    大推動渦輪風扇引擎
  6. Testing methods for turbo - fans

    渦輪風扇試驗方法
  7. Along with the advent of the highly efficient turbofan jet engine, used today on the majority of commercial aircraft, came a new and challenging problem for maintenance personnel. the repair and replacement of the abradable liner seal, sometimes also known as the fan track.

    在大多數商用飛機使用高效率的渦輪風扇噴氣發動機時代到來的同時，飛機維修人員也面臨著新的挑戰，即如何修理和替換發動機上的耐磨損內襯密封條，有時候也被稱為風扇軌道
  8. Port engines ingested some foreign matter during take - off roll, fan blades severely damaged, we abandoned taxing back to terminal

    飛機起飛滑跑中左發進氣口吸入異物， （渦輪）風扇葉片損壞，中斷起飛，滑到候機室。
  9. 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。
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