基于双旋流全环燃烧室的出口温度分布试验研究  

Experimental study on the outlet temperature distribution of double swirler combustor

作　　者：门玉宾 郑龙席[1] 柴昕 张燚 张宝华 马宏宇 MEN Yubin;ZHENG Longxi;CHAI Xin;ZHANG Yi;ZHANG Baohua;MA Hongyu(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China;Shenyang Engine Research Institute,Aero Engine Corporation of China,Shenyang 110015,China)

机构地区：[1]西北工业大学动力与能源学院,西安710129 [2]中国航发沈阳发动机研究所,沈阳110015

出　　处：《航空动力学报》2024年第6期125-134,共10页Journal of Aerospace Power

基　　金：国家两机专项项目。

摘　　要：以双旋流全环燃烧室为试验对象,分别在高温高压、高温中压和发动机整机条件下开展试验研究。分别设计了带有环腔引气和模拟型喷嘴等模拟发动机边界条件的试验方案,并分析不同试验条件下的出口温度分布规律。试验结果表明:中、高压试验条件下的出口温度分布规律基本一致,热点区域基本一致;中压试验周向出口温度分布水平明显优于高压试验;高压试验温度分布曲线呈中心波峰形式,而中压试验中心波峰形式不明显。设计的高压试验出口温度分布规律和数值更接近发动机整机测试结果,设计的中压试验出口温度分布数值与高压试验相比存在一个比例系数,系数为1.3~1.4。The double swirler full annual combustor was taken as the experiment object,the outlet temperature distribution under different experiment conditions was compared and analyzed under high temperature/high pressure,high temperature/medium pressure and engine experiment conditions.The experimental schemes with annular bleed and simulated nozzle were designed to simulate the boundary conditions of the engine,and the outlet temperature distribution under different experimental conditions was analyzed.The experimental results showed that the outlet temperature distribution under the medium and high pressure experimental conditions was basically the same,and the hot spot area was basically the same;the outlet temperature distribution level of the middle pressure experiment was obviously better than that of the high-pressure experiment;the temperature distribution curve of high-pressure experiment was in the form of central peak,while that of medium pressure experiment was not obvious.The designed high-pressure experiment outlet temperature distribution law and value were closer to the engine experiment results;compared with the high-pressure experiment,the outlet temperature distribution value of the medium pressure experiment designed regularly had a proportional coefficient of 1.3—1.4.

关 键 词：双旋流 全环燃烧室试验 高温高压 发动机试验 出口温度分布 

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]