尾渦片 的英文怎麼說

中文拼音 [wěiguōpiān]
尾渦片 英文
trailing vortex sheet
  • 渦 : 渦名詞1. （漩渦） eddy; whirlpool; vortex 2. （酒窩） dimple
  • 片 : 片構詞成分。
  1. The vortex simulated in this article include the shedding vortex induced by the vane trailing edge boundary layer, the endwall vortex generated by the endwall boundary layer interaction, the passage vortex generated by the rotor rotation, and the leakage vortex generated by the tip clearance flow

    渦輪級內的渦運動包括：導向器葉片尾緣附而層引起的脫落渦；轉子通道內轉子的旋轉運動產生的通道渦；根腳區兩個端壁附面層干涉，形成的根腳渦；存在葉尖漏流時，出現的漏流渦。
  2. The complex vortex system structure and shock wave system structure inside this rotor is obtained. wall flow patterns on the blade surface and hub surface are found out. the complex vortex system structure, such as horseshoe vortex, passage vortex, corner vortex and trailing vortex, and the interaction with shock wave system are researched. especially, the character of the tip clearance flow inside the rotor passage is revealed, and the interaction between shock wave and tip clearance flow near blade tip and the evolution of tip clearance flow are considered

    給出了葉片表面及輪轂面上的壁面流型，分析並揭示了轉子葉道內的馬蹄渦、通道渦、角渦、尾渦等復雜渦系及其與激波的相互干涉；特別是，分析並揭示了轉子葉道內頂隙射流的特點，得到了頂隙附近激波與泄漏流動的干涉形態及泄漏流動的發展，並著重給出了其與激波的干涉形態。
  3. 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。
  4. 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。
  5. 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。
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