基于正交设计的分级分区头部流动特性研究  

Flow Characteristics of Staged Combustor based on Orthogonal Design

作　　者：金九生 刘云鹏 颜应文[1] 赵宁波[2] JIN Jiu-sheng;LIU Yun-peng;YAN Ying-wen;ZHAO Ning-bo(College of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing,China,210016;College of Power and Energy Engineering,Harbin Engineering University,Harbin,China,150001)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016 [2]哈尔滨工程大学动力与能源工程学院,哈尔滨150001

出　　处：《热能动力工程》2023年第5期80-87,共8页Journal of Engineering for Thermal Energy and Power

基　　金：国家科技重大专项(2017-Ⅲ-0006-0031)。

摘　　要：针对某两级中心分级分区单头部燃烧室结构参数对头部下游流场结构的影响,采用数值模拟结合正交设计的方法研究了头部结构参数(一/二级旋流数、值班级套筒张角、隔离段高度比)的变化对燃烧室流动特性的影响规律和程度。结果表明:中心回流区最大宽度随着二级旋流数、隔离段高度比、一级旋流数、值班级套筒张角4个结构参数的增大而增大,并且影响程度依次降低;中心回流区长度随着一/二级旋流数的增大而增大,套筒张角和隔离段高度比则对中心回流区长度的影响程度较小;值班级和主燃级旋流器的旋流数偏大以及值班级套筒张角偏大都会导致台阶回流区消失。Aiming at a two-stage central-staged single-dome combustor,in order to investigate the effects of its structural parameters on the downstream flow field structure of dome,numerical simulation combined with orthogonal design was used to obtain the influence law and influence degree of the changes of each structural parameter(pilot swirl number,main swirl number,the expansion angle of the pilot′s sleeve and lip height)on the flow characteristics of the combustor.The results show that the maximum width of the primary recirculation zone increases with the increase of the four structural parameters such as swirl number of main stage swirler,lip height,swirl number of pilot stage swirler and expansion angle of the pilot′s sleeve,and the influence degree decreases in turn;the length of the primary recirculation zone increases with the increase of pilot swirl number and main swirl number,and the expansion angle of the pilot′s sleeve and lip height have little effect on the length of the primary recirculation zone;the larger swirl number of pilot stage and main stage swirlers and the larger expansion angle of the pilot′s sleeve will lead to the disappearance of the lip recirculation zone.

关 键 词：中心分级分区燃烧室 正交设计 数值模拟 冷态流场 结构参数 

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]