film-cooling hole 中文意思是什麼

film-cooling hole 解釋
薄膜冷卻孔
  • film : n 1 薄層，薄膜；薄霧，輕煙；細絲狀的東西。2 【攝影】感光乳劑，照相軟片，電影膠片；影片。3 〈 pl ...
  • cooling : n. ,adj. 冷卻（的）。
  • hole : n 1 洞，穴，孔；（衣服等上的）破洞；傷口；漏洞；窩，坑；水流的深凹處，（河道的）緩流窪。2 （獸的...
  1. The results showed that the discharge coefficient of film cooling hole was greatly increased with the increase of blow ratio when the blow ratio m is lower, buta it had a little increase with the increase of m when m is larger

    實驗結果表明，在吹風比較小時，隨吹風比的增加流量系數大幅度增加，當吹風比較大時，隨吹風比的增加流量系數增幅減小。
  2. In order to study the influence of dimensional configuration of the film cooling hole on the discharge coefficient, some kinds of film cooling holes with different dimensional configuration were designed

    摘要為了研究火焰筒壁面氣膜冷卻孔幾何結構對流量系數的影響規律，設計了幾種具有不同幾何尺寸和排列結構的氣膜冷卻孔實驗件。
  3. 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。
  4. Firstly, for jet array impingement cooling, the effects of the distance of adjacent holes, the impinging distance and jet reynolds number on heat transfer characteristic at the target wall are summarized under staggered holes arrangement and the same hole diameter. and then, the numerical simulation of inclined multi - hole film cooling has been studied. the influence factors examined in this case include blowing ratio and the distance of adjacent holes

    首先通過對射流沖擊冷卻方式的研究，分析了相鄰孔間距、沖擊間距以及射流入口雷諾數對沖擊靶面換熱系數的影響情況，然後對多斜孔冷卻方式進行了數值模擬，重點探討了吹風比和相鄰孔間距對絕熱溫比與壁面換熱系數的影響規律，最後，針對沖擊-發散復合冷卻流場的計算物理模型，研究吹風比、相鄰孔間距的變化對沖擊-發散復合冷卻流動與傳熱特性的影響。
  5. 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。
  6. A numerical study is reported to investigate the flow and temperature fields for jet array impingement cooling, inclined multi - hole film cooling and impingement / effusion film cooling

    運用數值計算的方法分別對陣列射流沖擊冷卻、多斜孔氣膜冷卻以及沖擊-發散復合冷卻方式的流動與傳熱特性進行了三維數值研究。
  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. 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
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