加力燃烧室试验燃气分析取样探针设计与验证  

Design and Verification of Gas Sampling Probe for Afterburner Test

作　　者：刘重阳 齐东东 冯大强 宋文艳[1] 张杰 LIU Chong-yang;QI Dong-dong;FENG Da-qiang;SONG Wen-yan;ZHANG Jie(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China;AECC Sichuan Gas Turbine Establishment,Mianyang 621000,China)

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072 [2]中国航发四川燃气涡轮研究院,四川绵阳621000

出　　处：《推进技术》2023年第5期131-141,共11页Journal of Propulsion Technology

基　　金：中国航发集团自主创新专项资金(ZZCX-2018-021);航空发动机及燃气轮机重大专项基础研究(J2019-Ⅴ-0005-0097)

摘　　要：为了满足航空发动机加力燃烧室高温低压环境下燃气分析测试对取样探针的应用要求,设计了一种双层冷却腔结构的混合取样探针,采用增材制造技术加工成型,通过试验和数值模拟,对其取样性能进行了验证和分析。研究结果表明:内、外腔分别采用空气和水作为冷却介质,可获得满足标准要求的样气,燃烧性能测试结果满足工程应用需求;探针取样性能与流场环境参数存在较强的线性相关性,其中压力影响最大,采用多元线性最佳子集回归分析方法获得的多个拟合方程拟合偏差最大不超过4%,可用于一定范围内该类探针取样性能的预测;本文采用的取样探针流-固热耦合数值模拟方法可信度较高,各性能参数计算误差在8%以内,可辅助探针流动与换热结构设计。In order to satisfy the application requirements of gas sampling probe for aero-engine afterburner test under the high temperature and low pressure condition,a composite samples probe with double-layer cooling cavity was designed,and it was manufactured applying additive manufacturing technology,the sampling perfor⁃mance was verified and analysed by test and numerical simulation.The research shows that the sample gas of stan⁃dard requirement can be obtained using air and water as cooling medium respectively in the inner and outer cool⁃ing cavity,the test results of combustion performance also meet the engineering application requirements.The lin⁃ear correlation between gas flow field parameters and sampling performance were found,in which the pressure is the most important parameter,the maximum fitting deviation of some fitting equations obtained from optimal sub⁃set model in the multiple linear regression analysis is not more than 4%,which can be applied for sampling per⁃formance prediction of the same type probe within a certain range.The method for probe numerical simulation of 3D fluid-solid coupling heat transfer in this paper is proved to be highly reliable,the calculation errors of each performance parameter are no more than 8%,which can be used for aided design of sampling probe on flow and heat transfer structure.

关 键 词：航空发动机 加力燃烧室 燃气分析 取样探针 双腔冷却 多元线性回归 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]