燃烧室头部激励的等离子体强化燃烧特性实验研究  

Experimental Research on Characteristics of Plasma-Enhanced Combustion Excited by Combustor Dome

作　　者：胡长淮 何立明[1] 陈一 张磊[1] 费力 赵志宇 HU Chang-huai;HE Li-ming;CHEN Yi;ZHANG Lei;FEI Li;ZHAO Zhi-yu(Aeronautics Engineering College,Air Force Engineering University,Xi’an 710038,China)

机构地区：[1]空军工程大学航空工程学院,陕西西安710038

出　　处：《推进技术》2021年第12期2762-2771,共10页Journal of Propulsion Technology

基　　金：国家自然科学基金(51436008,91741112)。

摘　　要：等离子体助燃是一种新型的强化燃烧技术。因此本文创新性地研制了基于旋转滑动弧等离子体的强化燃烧头部,建立了航空发动机三头部燃烧室实验件的等离子体助燃实验平台,验证了该等离子体强化燃烧技术应用于型号发动机燃烧室的可行性。实验研究等离子体助燃在不同余气系数和不同输入电压条件下对平均出口温度、燃烧效率、温度分布系数以及熄火边界的影响。实验结果表明,与正常燃烧相比,施加等离子体助燃后的燃烧效率有明显的提高,在输入电压U_(0)=240V,余气系数α=0.8的工况下,等离子体助燃的燃烧效率提高3.24%。实施等离子体助燃后,燃烧室出口温度分布场分布得到明显的改善,在α=0.8的富油工况下,出口温度分布系数减少39.8%。等离子体助燃输入电压越高,熄火边界扩展程度越明显,相比于正常工况条件下,施加等离子体助燃后,输入电压为240V时的熄火边界扩宽了7.34%。Plasma-assisted combustion is a new technology of enhancing combustion. Therefore,in this paper,the plasma-enhanced combustion dome has been developed creatively based on the rotating gliding arc discharge technology,meanwhile a combustor with triple plasma-enhanced combustion dome test platform was established to validate the feasibility of applying plasma-enhanced combustion technology to the aero-engine combustor. Experiments were carried out to study the effects of plasma-assisted combustion on average outlet temperature,combustion efficiency,outlet temperature distribution factor(OTDF)and lean blowout performance under different excess air coefficients α and input voltages U_(0). Compared with normal combustion,the combustion efficiency is significantly improved after applying plasma-assisted combustion,and the increment reaches 3.24% at U_(0)=240 V and α=0.8. The uniformity of outlet temperature field is also improved after applying plasma-assisted combustion and the decrease of OTDF is more than 39.8% in the rich fuel condition of α=0.8. The expansion of lean blowout limit rises with the increase of input voltages,and reaches to 7.34% compared with normal conditions at U_(0)=240 V.

关 键 词：航空发动机 燃烧室 等离子体助燃 强化燃烧头部 旋转滑动弧放电 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]