采用CARS试验技术与UFPV数值方法研究航空发动机燃烧室（英文）  

Experimental and simulation study of aeroengine combustor based on CARS technology and UFPV approach

作　　者：熊模友 乐嘉陵[2] 黄渊[2] 宋文艳[1] 杨顺华[2] 郑忠华[2] Xiong Moyou;Le Jialing;Huang Yuan;Song Wenyan;Yang Shunhua;Zheng Zhonghua(School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China;Science and Technology on Scramjet Laboratory of Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China)

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术重点实验室,四川绵阳621000

出　　处：《实验流体力学》2017年第5期15-23,共9页Journal of Experiments in Fluid Mechanics

基　　金：Supported by NSFC(91641205)

摘　　要：在自主开发的软件平台上,采用基于URANS的方法计算航空发动机燃烧室的三维两相燃烧流动,考虑了液态燃油从液膜-液滴-燃气-燃烧的完整物理化学过程。其中,颗粒相采用LISA一次破碎模型,KH-RT二次破碎模型和标准的蒸发模型,湍流燃烧模型采用可以考虑非稳态燃烧特性的非稳态火焰面/反应进度变量方法,得到了航空发动机燃烧室中温度、组分浓度和燃油液滴的颗粒直径分布规律。同时,采用CARS光学手段测量燃烧室主燃区的温度分布,并将数值计算结果与光学试验测量值进行比较,数值计算结果和试验值吻合较好,数值计算误差小于7.3%。说明了本文的数值计算方法和UFPV方法在计算航空发动机燃烧室的两相燃烧流动时具有较高的精度。Based on the U nsteady R eynolds A veraged N avier Stokes(URANS)method,a three-dim ensional tw o-phase turbulent com bustion num erical softw are for aeroengine com bustor has been developed.T he physical and chem ical processes taking place in the liquid fuel are simulated com pletely?including liquid film form ation,breakup,evaporation and com bustion.LISA and KH-RT are used as the primary and second atomization model respectively,and also the standard evaporation m odel is used to sim ulate the evaporation process.Besides?detailed chemical mechanism of kerosene is used for reaction kinetics?and the Unsteady Flam elet/Progress Variable(UFPV)approach in w hich the unstable com bustion characteristics of the flame could be simulated is used as the com bustion model.The tem perature and species of the flow field and the diameter of fuel droplets in the aeroengine com bustor are obtained.At the same time,the Coherent A nti-stokes R am an Scattering(CARS)technology is used to m easure the tem perature in the primary zone of the aeroengine com bustor.T hen the tem perature of the sim ulation is com pared with that m easured by CARS technology,and the calculation error of num erical results is less than7.3%.T he studies have show n that the num erical m ethod in this paper and UFPV approach can sim ulate the tw o-phase turbulent com bustion process appropriately in the aeroengine com bustor.

关 键 词：航空发动机燃烧室 两相燃烧 UFPV方法 CARS技术 

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]