旋转爆震燃烧室梯度复合热防护结构热分析模型及验证

doi:10.7527/S1000-6893.2021.25271

流体力学与飞行力学

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旋转爆震燃烧室梯度复合热防护结构热分析模型及验证

田佳, 张靖周, 谭晓茗, 王元帅

南京航空航天大学能源与动力学院航空飞行器热管理与能量利用工信部重点实验室, 南京 210016

收稿日期:2021-01-15 修回日期:2021-02-09 出版日期:2022-03-15 发布日期:2021-04-29
通讯作者: 张靖周 E-mail:zhangjz@nuaa.edu.cn
基金资助:
国家级项目

Thermal analysis model and validation for graded-composite thermal protection structure of rotating detonation combustor

TIAN Jia, ZHANG Jingzhou, TAN Xiaoming, WANG Yuanshuai

Key Laboratory of Thermal Management and Energy Utilization, Ministry of Industry and Information Technology, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received:2021-01-15 Revised:2021-02-09 Online:2022-03-15 Published:2021-04-29
Supported by:
National Project

摘要/Abstract

摘要： 针对旋转爆震燃烧室高热流密度的热防护需求，提出了一种碳化硅耐烧蚀层-高硅氧烧蚀层-气凝胶隔热层-不锈钢金属基体层的梯度复合热防护结构，建立了考虑烧蚀的多层平壁一维瞬态热分析模型，结合旋转爆震燃烧室的典型热环境，采用动边界隐式差分计算格式求解获得了壁面输入热流密度和高硅氧烧蚀层主要参数对热防护结构内部温度分布的影响；同时开展了旋转爆震燃烧室梯度复合热防护结构热考核试验，对热分析模型进行了试验验证。研究结果表明:旋转爆震燃烧室壁面沿轴向温度分布存在着内在的不均匀性，前端由于预混气的及时补充而得到有效冷却，温度峰值出现在位于中截面和燃烧室出口的尾端区域。基于径向一维传热简化，从实测的旋转爆震燃烧室壁面轴向温度分布反演出时均热流密度沿程分布，并以此对特定轴向截面的热防护结构温度瞬态变化进行了分析，与试验结果的对比验证了所建立地考虑烧蚀过程的一维瞬态热分析模型可以较好地预测梯度复合热防护结构的温度变化特性。

关键词: 旋转爆震燃烧室, 热防护, 梯度复合结构, 热分析模型, 试验验证

Abstract: A graded-composite thermal protection structure composed of a SiC ablative layer, a high-silicon-oxygen ablation layer, an aerogels thermal insulation layer and a stainless-steel metal-based layer is proposed to meet the requirement of thermal protection on the high-heat-flux wall of rotating detonation combustors.A one-dimensional transient multi-layer thermal analysis model considering the ablation process is established.In combination with the typical thermal conditions of rotating detonation combustors and using the moving boundary implicit difference calculation scheme, we analyze the influences of input heat fluxes and main thermo-physical parameters of the high-silicon-oxygen ablation layer on temperature distribution of the graded-composite thermal protection structure.Furthermore, a thermal evaluation experiment is conducted for the specific graded-composite thermal protection structure on a rotating detonation combustor to validate the one-dimensional transient multi-layer thermal analysis model.It is revealed that the temperature distribution on the rotating detonation combustor wall exhibits an inherent un-uniformity along the axial direction.The front wall is effectively cooled because of the timely supplement of the premixed gas, and the peak temperature occurs in a specific region between the middle section and the combustor outlet.From the measured temperature distribution along the axial direction, the time-averaged thermal load distribution on the rotating detonation combustor wall is retrieved based on one-dimension radial heat transfer simplicity.With the retrieved thermal load, the temperature variation with time at a specific axial location is calculated and compared with the measured results.The comparison proves that the present one-dimensional transient multi-layer thermal analysis model with the integrity of the ablation process is able to provide a better prediction for temperature distribution on the graded-composite thermal protection structure.

Key words: rotating detonation combustors, thermal protection, graded-composite structure, thermal analysis model, experimental validation

中图分类号:

V231.1

田佳, 张靖周, 谭晓茗, 王元帅. 旋转爆震燃烧室梯度复合热防护结构热分析模型及验证[J]. 航空学报, 2022, 43(3): 125271.

TIAN Jia, ZHANG Jingzhou, TAN Xiaoming, WANG Yuanshuai. Thermal analysis model and validation for graded-composite thermal protection structure of rotating detonation combustor[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(3): 125271.

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旋转爆震燃烧室梯度复合热防护结构热分析模型及验证

Thermal analysis model and validation for graded-composite thermal protection structure of rotating detonation combustor

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