出口宽高比对S弯喷管热固耦合响应的影响  

Investigation on influence mechanism of exit aspect ratio on thermal-solid interaction response of serpentine nozzle

作　　者：程经理 黄盛 周莉 王占学[1] CHENG Jingli;HUANG Sheng;ZHOU Li;WANG Zhanxue(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2025年第2期81-98,共18页Journal of Aerospace Power

基　　金：国家自然科学基金(51876176,52076180,51906204);国家科技重大专项(J2019-Ⅱ-0015-0036);陕西省杰出青年基金(2021JC-10)。

摘　　要：为了明晰出口宽高比对S弯喷管流动传热和结构响应影响,采用基于计算结构动力学/计算流体力学(CSD/CFD)串行双向松耦合方法,研究了不同出口宽高比下的热固耦合响应影响。结果表明:弯曲构型作用下喷管整体热流密度分布不均匀,各处差异性较大,而各个喷管分布类似;随着出口宽高比增加,第二弯处热流密度不断增加;喷管出口等直段存在旋涡结构,使得传热受阻。结构响应中,各个S弯喷管应力分布类似,但应力最大值位置存在包括喷管出口端和第二弯通道上壁面棱边两处。随着出口宽高比增加,最大应力不断增大,出现时刻提前,出口宽高比为10的喷管应力最大,相对于最小的应力最大值增加了28%,出现时刻提前23.84 s。In order to clarify the effect of exit aspect ratio on the flow heat transfer and structural response of serpentine nozzle,a serial two-way loose coupling method based on computational structural dynamics/computational fluid dynamics(CSD/CFD)was used to study the effect of thermal-solid coupling response at different aspect ratios.Results were obtained as follows:the overall heatflux distribution of the nozzle under the action of the bending configuration was not uniform,with large variability at each location,while the heatflux distribution of individual nozzles was similar;the heatflux increased continuously at the second bend as exit aspect ratio increased;the vortex structure was generated at the exit isometric section,and the presence of the vortex structure hindered the heat transfer;in structural response,the distribution of stress in each serpentine nozzle was similar,but the maximum stress existed in two locations,including the nozzle exit end and the upper wall of the second bend channel.As the exit aspect ratio rose,the maximum stress also rose,and appeared in advance.Maximum stress with aspect ratio of 10 increased by 28%compared with the minimum stress,and the moment of appearance was 23.84 s earlier.

关 键 词：出口宽高比 热固耦合 串行双向松耦合方法 S弯喷管 流动传热分析 结构响应 

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]