大直径小环腔燃烧室设计及试验  

Design and experiment of grand scale diameter and small annular cavity combustor

作　　者：邬俊 陈敏敏 陈翔 张险 康尧 汤姣 刘达兵 郭青林 杨志 WU Jun;CHEN Minmin;CHEN Xiang;ZHANG Xian;KANG Yao;TANG Jiao;LIU Dabing;GUO Qinglin;YANG Zhi(Hunan Aviation Powerplant Research Institute,Aero Engine Corporation of China,Zhuzhou Hunan 412002,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002

出　　处：《航空动力学报》2023年第11期2711-2717,共7页Journal of Aerospace Power

摘　　要：针对某创新构型的涡轮发动机,在国内首次开展大直径小环腔燃烧室的设计及试验研究。提出基于扩压器逆向进气条件下的环涡流场匹配切向燃油喷射的燃烧室设计方案,开展不同状态下燃烧室冷态及热态性能试验,得到燃烧室流阻特性、地面点火特性、贫油熄火特性以及燃烧效率、出口温度场等特性,结果表明:(1)该设计方案可以满足燃烧室的设计要求;(2)与常规燃烧室相比,该方案的喷嘴间距比设计达到1.65;(3)该方案燃烧室的点火性能优异,最低贫油点火油气比达到0.016,点火联焰时间可在4 s以内;(4)该方案燃烧室的总压损失、燃烧效率、出口温度分布系数(OTDF)、出口径向温度分布系数(RTDF)等综合性能优异,其中慢车状态的燃烧效率能够达到98.6%,设计点的OTDF达到0.16。Design and experiment study of a grand scale diameter and small annular cavity combustor were carried out for the first time interiorly,considering the turbine engine with innovated structure.A combustor design scheme based on annular vortex field matching tangential fuel injection under the condition of diffuser with reverse air intake was proposed.Cold and hot performance experiments of combustor under different conditions were carried out,the combustor characteristics including flow resistance characteristics,ignition characteristics at ambient temperature and pressure,lean blow out characteristics,combustion efficiency,as well as the outlet temperature field,were obtained.The results showed that:(1)the design scheme met the design requirements of combustor;(2)compared with conventional combustor,the nozzle spacing ratio of the scheme reached 1.65;(3)the ignition performance of the designed combustor was excellent,as its minimum lean ignition fuel-air-ratio reached 0.016 and its ignition and flame combination time was within 4 s;(4)the total pressure loss,combustion efficiency,out temperature distribution factor(OTDF)and radial temperature distribution factor(RTDF)of the designed combustor had outstanding performance;as the combustion efficiency of idle state reached 98.6%,the OTDF of design point reached 0.16 as well.

关 键 词：涡轮发动机 大直径 小环腔 燃烧室设计 性能试验 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]