本文選題：渦輪葉片 + 無網(wǎng)格方法��； 參考：《中國工程物理研究院》2016年碩士論文

【摘要】：隨著現(xiàn)代航空發(fā)動機的快速發(fā)展,為了追求高推重比和高熱效率,現(xiàn)代先進渦輪的進口溫度越來越高。在持久的高溫環(huán)境下渦輪葉柵必然會出現(xiàn)一定范圍的燒蝕現(xiàn)象,嚴重影響其壽命和可靠性,燒蝕對發(fā)動機運行工況造成的影響在實驗難以開展的情況下不易評估,因此利用數(shù)值模擬工具對渦輪葉柵的燒蝕現(xiàn)象進行研究,探討不同的運行工況下葉片燒蝕特點和規(guī)律,進而有效預(yù)防葉片燒蝕引起的發(fā)動機故障,對于實現(xiàn)我國航空發(fā)動機和燃氣輪機的可靠、安全運行來說具有非常重要的意義。本文圍繞如何準確預(yù)測航空發(fā)動機中渦輪等熱端部件的燒蝕這一核心問題,采用無網(wǎng)格SPH數(shù)值模擬方法進行研究。在馬智博研究員的指導(dǎo)下,基于物質(zhì)團無網(wǎng)格方法的理論和面向?qū)ο蟮某绦蛟O(shè)計技術(shù),對已有的無網(wǎng)格程序框架繼續(xù)開發(fā),添加了湍流、轉(zhuǎn)捩、氣固兩相流以及燒蝕模塊,并完善了流/固/熱耦合和邊界條件模塊。針對航空發(fā)動機渦輪內(nèi)的復(fù)雜流動、傳熱和燒蝕現(xiàn)象,基于飛行器再入燒蝕模型,引入邊界層厚度將葉片表面熱邊界層邊界條件替換遠場自由來流邊界條件,建立了適用于內(nèi)流問題的渦輪葉片氣動熱力燒蝕模型。此外,在充分調(diào)研國內(nèi)外最新無網(wǎng)格SPH方法研究成果的基礎(chǔ)上,給出了以下3部分改進工作：(1).基于小波分析和多尺度再生核函數(shù)理論研究了初始光滑長度的最優(yōu)選取準則并討論了計算過程中光滑長度的自適應(yīng)方法。(2).基于近似黎曼求解器改善了傳統(tǒng)的Monaghan人工粘性,構(gòu)造了隨流場自適應(yīng)的無人工參數(shù)的人工粘性,在此基礎(chǔ)上,采用類比方法構(gòu)造了NS能量方程離散形式中的耗散項。(3).基于文獻中關(guān)于NS動量方程的守恒型SPH離散格式的研究成果,采用類比粘性項離散的方法統(tǒng)一了傳質(zhì)、傳熱方程中擴散項的數(shù)值離散格式。利用該程序?qū)σ粋�較為復(fù)雜的內(nèi)冷高壓渦輪葉片進行了燒蝕問題的數(shù)值模擬,研究結(jié)果表明：(1).葉片壓力面和吸力面主要發(fā)生小尺度燒蝕,造成的材料流失很小可以忽略不計,僅改變?nèi)~片表面的粗糙度；發(fā)生在葉片前/尾緣的大尺度燒蝕造成材料的流失較多,甚至出現(xiàn)掉塊等現(xiàn)象,帶來渦輪葉片形狀的顯著變化。(2).離心力和哥氏力的作用造成了動葉表面換熱和燒蝕特點與靜葉存在一定的差異。隨后,將研究對象由單個葉片擴展到渦輪級環(huán)境,研究了動靜干涉下渦輪葉柵的燒蝕特點,研究結(jié)果表明：(1).不同動葉轉(zhuǎn)速下,導(dǎo)葉吸、壓力面之間橫向壓差發(fā)生了變化從而改變了導(dǎo)葉通道中馬蹄渦壓力面分支的傳播規(guī)律,進而影響了導(dǎo)葉壓力面的傳熱和燒蝕特點。(2).在中等轉(zhuǎn)速情形下動葉前緣燒蝕較低；當轉(zhuǎn)速很高時,由于相對運動牽引的流場變化比較劇烈,動葉前緣的通道渦和馬蹄渦從動靜之間的大變形流場中吸收能量不斷壯大,強化前緣換熱,燒蝕程度增加；轉(zhuǎn)速很低時,導(dǎo)葉尾緣激波的持續(xù)作用導(dǎo)致動葉前緣燒蝕同樣相對嚴重。最后,本文針對不同的主流參數(shù)研究了不同工況下渦輪葉片的燒蝕特點,并展望了后續(xù)燒蝕研究需要開展的研究內(nèi)容。
[Abstract]:With the rapid development of modern aviation engine , in order to pursue high - weight ratio and high thermal efficiency , the inlet temperature of modern advanced turbine is getting higher and higher . Based on the approximate Riemann solver , the traditional Monaghan artificial viscosity is improved , and the artificial viscosity of the artificial parameters with self - adaptation of the flow field is constructed . On the basis of this , the dissipation term in the discrete form of NS energy equation is constructed by analogy method . Based on the research results of the conserved SPH discrete form of NS momentum equation in literature , the numerical simulation of diffusion term in mass transfer and heat transfer equation is unified by means of discrete method of analogy viscous term . The numerical simulation of the ablation problem of a complicated internal cooling high pressure turbine blade is carried out by using the program . The results show that : ( 1 ) The blade pressure surface and the suction surface mainly occur small - scale ablation , and the loss of material is negligible , only the roughness of the surface of the blade is changed ;
Large - scale ablation occurs at the front / trailing edge of the blade , resulting in more loss of material , even falling out of the block , resulting in a significant change in turbine blade shape . The effects of centrifugal force and Coriolis force on the surface heat transfer and ablation characteristics of the rotor blade are different from that of the stator blade . Then , the research object is extended from a single blade to the turbine stage environment . The experimental results show that : ( 1 ) the transverse pressure difference between the guide vane and the pressure surface changes under different moving blade rotating speeds , which changes the propagation law of the branch of the horseshoe vortex pressure surface in the guide vane passage , and then the heat transfer and ablation characteristics of the guide vane pressure surface are affected . in that case of moderate rotate speed , the ablation of the leading edge of the rotor blade is low ;
When the rotating speed is very high , due to the violent change of the flow field drawn by the relative motion , the channel vortex and the horseshoe vortex in the leading edge of the moving blade absorb energy continuously from the large deformation flow field between the dynamic and static , so as to strengthen the heat exchange of the leading edge and increase the ablation degree ;
In the end , the ablation characteristics of turbine blades under different working conditions are studied for different main flow parameters , and the research contents of subsequent ablation research are forecasted .
【學(xué)位授予單位】：中國工程物理研究院
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2016
【分類號】：V235.1

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