turbine blade cooling 中文意思是什麼

turbine blade cooling 解釋
渦輪葉片冷卻
  • turbine : n 【機械工程】（渦）輪機，葉輪機，汽輪機，透平機。 a hydraulic [water] turbine 水輪機。 a steam t...
  • blade : n 1 （殼、草等的）葉片，葉身，葉。2 刀片；（安全）剃刀刀片 （＝ razor blade）; 刀口，刃；刀，劍；...
  • cooling : n. ,adj. 冷卻（的）。
  1. The welding technology of francis turbine runners is optimized from the view of subsection welding and local heating by numerical simulation. the result shows that welding residual tensile stress appears in the weld and its area nearby, and peak stress appears in the dangerous area of blades after practising quondam welding technology ; welding residual tensile peak stress in the dangerous area of blades can be decreased by welding both ends earlier and then welding middle section later during subsection welding, and decreasing effect on welding residual stress of the subsection welding is related to the weld length of blade outlets and welding direction of each subsection ; decreasing effect on residual stress of the local heating is direct proportional to heating time, heating temperature, heating area, and inversely proportional to cooling area, and welding residual tensile peak stress in the dangerous area is decreasing trend earlier, and then increasing trend later with heated location increased

    本文利用數值模擬手段對轉輪的焊接工藝從分段焊和局部加熱兩個方面進行了優化，結果表明:採用普通工藝焊接時，葉片焊后殘余拉應力出現在焊縫及其附近區域，並且在葉片出水邊的熔合線附近（危險區域）出現了峰值;在採用優化的分段焊時，先焊兩端后焊中間的方法可以降低葉片危險區域的焊接殘余拉應力峰值，降低效果與葉片出水邊焊段長度、焊縫各段的焊接方向有關;局部加熱法降低轉輪危險區域殘余應力的效果主要與加熱時間、加熱溫度以及加熱面積成正比，與冷卻面積成反比，並且危險區域的殘余應力隨加熱區域的增大呈先降低后升高的趨勢。
  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 very important in the design of turbine blade, with the ever - increasing inlet temperature, the new heat transfer enhancement structures of higher performance are demanded. because of the complexity of the flow and heat transfer of the blade inner channel cooling, the numerical modulation is superior to the experiment. this thesis studied the blade inner channel cooling with the method of numerical modulation

    葉片內部通道冷卻在航空發動機葉片的設計中佔有重要的位置，航空發動機進口溫度的增高對其提出了更高的要求。由於葉片內部通道冷卻的流動與傳熱的復雜性，數值模擬較實驗的研究方法有其優越性，本文利用數值模擬的方法對葉片內部通道冷卻進行了研究。
  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. 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。
  7. Above all, the surface of the gas turbine blade including stator and rotor heat transfer coeficience with no film cooling hole was studied with the main stream reynolds number of 150000, 200000 50000, 300000, 350000, 400000. then, the heat transfer coefficience when all cooling holes opened and only one cooling hole opened was studied partly. and it ' s studied how the mainstream reynolds number, blowing ratio and the position of holes affect the heat transfer coefficience of the surface of blade

    對導葉和動葉，都是先研究了在150000 ， 200000 ， 250000 ， 300000 ， 350000 ， 400000雷諾數下，沒有氣膜冷卻時的表面換熱系數分佈，然後研究了氣膜孔全打開和只打開單排孔時的表面換熱系數分佈曲線，重點研究來流雷諾數，吹風比和不同孔位出流對換熱系數分佈的影響規律。
  8. The method of prediction the discharge coefficients of film cooling holes on the turbine blade suggested by d. a. rowbury et. al has been improved in this paper to fit the computations in the cases of low pressure ratios and the holes in leading edge region especially. the effects of external cross - flow, hole geometry and reynolds number in the hole were taken into account. an additive loss coefficient method is subsequently applied to the test data in order to assess the effect of the external cross - flow

    Rowbury等提出的流量系數工程演算法進行了改進，計算結果和實驗數據的比較表明改進后的新模型使低吹風比和前緣駐點附近流量系數的計算得到了明顯的改進，而在高吹風比下仍能保持與實驗數據相符，這種演算法有可能成為低壓比情況下型面氣膜冷卻的一種通用設計方法。
  9. 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。
  10. 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。
  11. Experimental investigation of discharge coefficients of film cooling hole on turbine blade

    吹風比對渦輪動葉型面氣膜孔流量系數的影響
分享友人
分享到 Line

分享到臉書