本文選題：渦輪葉片　切入點：前緣氣膜冷卻　出處：《南京航空航天大學(xué)》2016年碩士論文　論文類型：學(xué)位論文

【摘要】：提高渦輪前燃氣溫度可有效提高航空發(fā)動機推力和熱效率。自20世紀60年代以來渦輪前燃氣溫度逐年增長,目前已遠高于葉片材料耐熱極限。葉片前緣區(qū)域直接承受高溫燃氣沖擊,在整個渦輪中溫度最高,常采用氣膜冷卻對此區(qū)域加以保護。本文通過實驗和數(shù)值計算相結(jié)合的方法對葉片前緣氣膜冷卻特性開展研究,分析了氣膜孔的孔型與孔位置對葉片表面換熱特性的影響,為優(yōu)化渦輪葉片冷卻特性提供數(shù)據(jù)支撐。具體研究內(nèi)容如下:(1)對葉片表面冷卻效率和對流換熱系數(shù)進行實驗研究,分析了不同孔型和孔位置葉片的全表面冷卻效率和對流換熱系數(shù)規(guī)律。研究得出:在實驗工況下,葉片的冷卻效率和對流換熱系數(shù)均隨吹風(fēng)比的增大而升高;冷卻效率和對流換熱系數(shù)在氣膜孔出口區(qū)域最大,沿流向因氣膜冷卻效果減弱而降低,降至葉片尾緣區(qū)域達到最小值;若葉片前緣吸力面和壓力面同時開有氣膜孔,相同吹風(fēng)比條件下,吸力面的冷卻效率和對流換熱系數(shù)皆比壓力面的大;在氣膜出流區(qū)域中,交叉孔葉片的冷卻效率和對流換熱系數(shù)均高于圓孔葉片。(2)運用Fluent軟件對渦輪葉片的真實工況進行數(shù)值模擬來分析其氣膜冷卻特性,研究葉片前緣氣膜孔對葉片冷卻效率和對流換熱系數(shù)的影響,并進行孔型與孔位置的對比。同時選取部分典型實驗工況進行數(shù)值模擬對比,實驗結(jié)果與數(shù)值模擬吻合較好。
[Abstract]:Increase the turbine inlet temperature can effectively improve the engine thrust and thermal efficiency. Since 1960s the turbine inlet gas temperature has increased year by year, far higher than the thermal limit. The blade material blade leading edge region directly under the impact of high temperature gas turbine, in the highest temperature, often with gas film cooling in this area should be protected. This method of combining through experimental and numerical studies on the cooling characteristics of leadingedge film, the effect of the pass analysis film holes and holes on the blade surface heat transfer characteristics, to provide data support for the optimization of turbine blade cooling. The specific contents are as follows: (1) on the blade surface cooling efficiency and convective heat transfer coefficient experimental study and analysis of the different type and hole position of leaf surface cooling efficiency and heat transfer coefficient law. The results show that under the experimental conditions, The blade cooling efficiency and the convective heat transfer coefficient decreased with the increase of blowing ratio increased; cooling efficiency and heat transfer coefficient at the outlet of film hole area, along the flow direction due to the film cooling effect decreased and decreased to the trailing edge reaches the minimum value; if the leading edge of the suction side and pressure side at the same time there the film hole, the same blowing ratio, the suction side of the cooling efficiency and the convective heat transfer coefficient are larger than the pressure surface; in the film flow region, cross hole vane cooling efficiency and heat transfer coefficient was higher than that of circular blade. (2) using Fluent software on the real working condition of turbine blade by numerical the simulation to analyze the film cooling characteristics, influence of blade leading edge film holes on the blade cooling efficiency and heat transfer coefficient, compared with the pass hole position. At the same time, select some typical experimental conditions for numerical simulation The experimental results are in good agreement with the numerical simulation.

【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2016
【分類號】：V231.1

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