掺混孔结构对大曲率受限空间出口温度分布的影响  

Effects of Dilution Hole Structure on Exit Temperature Distribution Characteristic in Large Curvature Limited Space

作　　者：蔡文哲 代威[3] 薛鑫 张弛[1] 林宇震[1] CAI Wen-zhe;DAI Wei;XUE Xin;ZHANG Chi;LIN Yu-zhen(National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,Research Institute of Aero-Engine,Beihang University,Beijing 100191,China;Beijing Power Machinery Institute,Beijing 100074,China;Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China;Research Institute for Frontier Science,Beihang University,Beijing 100191,China)

机构地区：[1]北京航空航天大学,航空发动机研究院,航空发动机气动热力国家级重点试验室,北京100191 [2]北京动力机械研究所,北京100074 [3]北京宇航系统工程研究所,北京100076 [4]北京航空航天大学前沿科学技术创新研究院,北京100191

出　　处：《推进技术》2022年第3期208-215,共8页Journal of Propulsion Technology

基　　金：国家科技重大专项(2019-III-0014)。

摘　　要：回流燃烧室的掺混射流在大曲率受限的弯管中与主流掺混,回流导致沿径向的压力梯度变化,增加了掺混流动的复杂性。为了研究不同掺混孔结构对掺混射流与主流在大曲率弯曲通道内的掺混规律,在有收缩比弯曲通道中多孔射流的出口温度分布测试中,对影响掺混冷却的各变化参数按照单一变量进行比对研究,对孔径、孔间距等掺混孔结构变量弯曲通道内的掺混效果进行分析,选择一种结构在三头部回流燃烧室进行了出口温度场的分布初步验证,得到了比较均匀的燃烧室出口温度分布,所得的规律可以作为回流燃烧室的掺混结构设计和优化的参考依据。The dilution jet in small reverse flow combustor is mixing with the main flow in a large curvature limited space. The gas flow accelerates and flow direction turns sharply which results in complicated flow condition by a variation of radial pressure gradient. In order to study effects of structure of the dilution hole on transverse jet mixing,the exit temperature distribution of multiple jets in large curvature limited space has been studied. The parameters of diameter of dilution hole,spacing between jets have been analyzed and summarized for the design experience. At last one of the dilution hole structure has been validated in a three injector reverse flow combustor,the preliminary results show that a relatively uniform exit temperature distribution of the combustor was achieved. The qualitative results of the dilution hole structure effect on the mixing could be a reference for the reverse flow combustor design and optimization.

关 键 词：大曲率受限空间 掺混射流 回流燃烧室 掺混孔结构 出口温度分布 

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]