本文選題：渦輪葉片　切入點(diǎn)：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(lèi)型：學(xué)位論文

【摘要】：提高渦輪前燃?xì)鉁囟瓤捎行岣吆娇瞻l(fā)動(dòng)機(jī)推力和熱效率。自20世紀(jì)60年代以來(lái)渦輪前燃?xì)鉁囟戎鹉暝鲩L(zhǎng),目前已遠(yuǎn)高于葉片材料耐熱極限。葉片前緣區(qū)域直接承受高溫燃?xì)鉀_擊,在整個(gè)渦輪中溫度最高,常采用氣膜冷卻對(duì)此區(qū)域加以保護(hù)。本文通過(guò)實(shí)驗(yàn)和數(shù)值計(jì)算相結(jié)合的方法對(duì)葉片前緣氣膜冷卻特性開(kāi)展研究,分析了氣膜孔的孔型與孔位置對(duì)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?jī)?nèi)容如下:(1)對(duì)葉片表面冷卻效率和對(duì)流換熱系數(shù)進(jìn)行實(shí)驗(yàn)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(duì)流換熱系數(shù)規(guī)律。研究得出:在實(shí)驗(yàn)工況下,葉片的冷卻效率和對(duì)流換熱系數(shù)均隨吹風(fēng)比的增大而升高;冷卻效率和對(duì)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(dá)到最小值;若葉片前緣吸力面和壓力面同時(shí)開(kāi)有氣膜孔,相同吹風(fēng)比條件下,吸力面的冷卻效率和對(duì)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(duì)流換熱系數(shù)均高于圓孔葉片。(2)運(yùn)用Fluent軟件對(duì)渦輪葉片的真實(shí)工況進(jìn)行數(shù)值模擬來(lái)分析其氣膜冷卻特性,研究葉片前緣氣膜孔對(duì)葉片冷卻效率和對(duì)流換熱系數(shù)的影響,并進(jìn)行孔型與孔位置的對(duì)比。同時(shí)選取部分典型實(shí)驗(yàn)工況進(jìn)行數(shù)值模擬對(duì)比,實(shí)驗(yàn)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(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類(lèi)號(hào)】：V231.1

【參考文獻(xiàn)】

相關(guān)期刊論文 前10條

1 張宗衛(wèi);朱惠人;劉聰;孟慶昆;;全氣膜冷卻葉片表面換熱系數(shù)和冷卻效率研究[J];西安交通大學(xué)學(xué)報(bào);2012年07期

2 游良平;陶毓伽;蔡軍;梁世強(qiáng);淮秀蘭;顧維藻;;渦輪葉片前緣復(fù)合冷卻實(shí)驗(yàn)[J];航空學(xué)報(bào);2009年09期

3 吳宏;孟恒輝;趙振明;吳宏偉;;吹風(fēng)比和曲率對(duì)旋轉(zhuǎn)曲面氣膜冷卻效率影響[J];北京航空航天大學(xué)學(xué)報(bào);2009年07期

4 李廣超;朱惠人;廖乃冰;許都純;;帶單排氣膜孔的葉片前緣氣膜冷卻換熱實(shí)驗(yàn)[J];推進(jìn)技術(shù);2008年03期

5 孫兆文;朱惠人;周雷聲;張永科;;渦輪葉片表面全氣膜冷卻傳熱實(shí)驗(yàn)研究[J];汽輪機(jī)技術(shù);2008年02期

6 朱惠人,向安定,許都純,劉松齡,郭文;渦輪葉片表面氣膜冷卻效率的實(shí)驗(yàn)研究[J];推進(jìn)技術(shù);2003年06期

7 林宇震,俞文利,劉高恩,許全宏;沖擊加發(fā)散雙層壁冷卻方式壓降分配對(duì)斜孔內(nèi)對(duì)流換熱影響的研究[J];航空學(xué)報(bào);2003年02期

8 許全宏,林宇震,劉高恩;沖擊加多斜孔雙層壁冷卻方式流量系數(shù)研究[J];推進(jìn)技術(shù);2000年05期

9 吳宏,鄧宏武,陶智;氣膜出流對(duì)葉片內(nèi)表面換熱系數(shù)影響的實(shí)驗(yàn)研究和計(jì)算[J];航空動(dòng)力學(xué)報(bào);1999年03期

10 林宇震,宋波,李彬,劉高恩;多斜孔壁冷卻方式小孔內(nèi)對(duì)流換熱研究[J];航空動(dòng)力學(xué)報(bào);1999年01期

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