膜冷卻葉片 的英文怎麼說
中文拼音 [mólěngquèyèpiān]
膜冷卻葉片
英文
film cooled blade-
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。( 2 ) on the leading edge, the film cooling effectiveness at the zone immediately downstream of the cooling holes is affected by blowing ratio and mainstream reynolds number, while the effects are not important in the downstream zone far from the cooling holes. ( 3 ) on the front half of pressure surface, the effectiveness increases with decreasing blowing ratio at the downstream near the cooling row and it is contrary at the downstream far from the cooling row. ( 4 ) on the rear pare of the pressure surface, the effectiveness decreases with increasing blowing ratio and does not vary so much downstream in the cases of higher blowing ratio
研究結果表明葉片吸力面端壁附近區域壓力系數分佈呈現出較強的三維特性，動葉吸力面尤其明顯；氣膜孔流量系數隨吹風比的增加而增大，在高吹風比情況下，流量系數逐漸趨于常數；在不同型面區域，冷卻效率分佈有較大的差異，而且吹風比與主流雷諾數的影響程度也不盡相同；低吹風比下，孔出口下游附近可以得到較好的冷卻，中、高吹風比下，冷氣射流在加速流動主流的作用下返回壁面進行二次冷卻，孔下游較遠區域可以得到較好的冷氣覆蓋。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Measured hole mass flows and a constant static pressure mixing analysis, together with the measured losses, allowed the decomposition of the losses into three distinct entropy generation mechanisms : loss generation within the hole, loss generation due to the mixing of the coolant with the mainstream, and change in secondary loss generation in the " blade passage
論文還進行了葉片冷卻孔質量流的測量與常靜壓氣流混合分析，結合前述氣動力損失和冷卻空氣損耗的測量結果表明，端壁氣膜冷卻的綜合損失明顯地由三個部分組成：葉片冷卻孔內產生的損失；由於冷卻空氣與主流熱空氣的混合產生的損失；二次流的變化產生的損失。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。Main working principal is that the bottom scraper with low rotate speed impels materials to form circumfluence in the basin of machine, the impeller of rotor rotating with medium speed can not only add wallop to sand, but also can add shear force to the sand with scraper so that the sand can touch and scrub each other fast ; wind blasting is set to cool the hot sand, remove dust and strip the membrane so that fast speed of regeneration and top - grade used sand can be gained
主要工作原理是低速轉動的底刮板推動物料在機盆內形成環流，中速轉動的轉子葉片既對砂子施以沖擊力，又與刮板配合對砂子施以剪切力，使砂粒間快速接觸和強烈摩擦，圍圈設風帶鼓風使熱砂沸騰冷卻除塵脫膜，從而達到再生速度快，回用砂質量好的目的。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。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。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。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。分享友人