截面渐变稳态射流燃烧室燃烧与排放数值模拟  

Combustion and emission numerical simulation of shape morphing jet-stabilized combustor

作　　者：祁治伟 王骥飞 刘秋洪[1,3] QI Zhiwei;WANG Jifei;LIU Qiuhong(School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China;College of Energy and Power Engineering,Inner Mongolia University of Technology,Hohhot 010051,China;National Key Laboratory of Aircraft Configuration Design,Xi’an 710072,China)

机构地区：[1]西北工业大学航空学院,西安710072 [2]内蒙古工业大学能源与动力工程学院,呼和浩特010051 [3]飞行器基础布局全国重点实验室,西安710072

出　　处：《航空动力学报》2024年第9期285-294,共10页Journal of Aerospace Power

摘　　要：针对近年来对燃气轮机低污染排放的要求,为了利用某椭圆形燃烧室低排放的优势,改善其出口不易匹配后方燃气涡轮的不足,提出了一种截面渐变概念,使稳态射流燃烧室入口为椭圆形截面,出口为圆形截面。使用数值模拟方法对其燃烧特性和出口处的流动与排放特性进行了研究,探究了截面渐变技术对燃烧室排放特性和流动特性的影响。与圆形燃烧室对比,截面渐变稳态射流燃烧室NO排放量降低了51.26%,保持了椭圆形燃烧室低排放的优势;与椭圆形燃烧室对比,有2.85%的NO排放量增加,但出口温度的均匀性提高了4.27%,同时能为后方燃气涡轮中的叶片提供更匹配的温度分布,证明了该截面渐变概念的可行性,可以为后续更多截面渐变技术研究作参考。According to the requirements of low pollution emission of gas turbine in recent years,in order to take advantage of an elliptical combustor and improve poor matching between its outlet and the gas turbine,a concept of shape morphing was proposed,which made the inlet of the jet-stabilized combustor elliptical and the outlet circular.Using numerical simulation methods,the combustion characteristics and flow and emission characteristics at the outlet of the combustor were studied.The influence of shape morphing on the emission and flow characteristics of the combustor was investigated.Shape morphing combustor reduced NO emission by 51.26%compared with circular combustor,maintaining the advantage of low emissions from the elliptical combustor;compared with the elliptical combustor,2.85%of NO emission was sacrificed,but the uniformity of outlet temperature was improved by 4.27%.At the same time,it can provide a more matched temperature distribution for the blades in the rear gas turbine,and prove the feasibility of the cross section gradual change concept,which can serve as a reference for further research on cross section gradual change technology.

关 键 词：截面渐变 稳态射流燃烧室 NO排放 液雾燃烧 数值模拟 

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]