高温燃气流风洞全尺寸舱段热结构试验技术研究

利用200 MW高温燃气流风洞，开展1:1全尺寸舱段模型热结构/热匹配试验.围绕风洞试验状态调节、介质影响热流设计评估、多台阶长时间热流校测等技术问题，开展高温燃气流风洞舱段类模型试验设计方法研究.引入新的燃气流风洞试验状态调节方法和考虑燃气介质差异的等效冷壁热流修正方法，并通过长时间变工况表面热流测试方法的建立，实现了多工况同步流场校测.试验设计方法有效应用于全尺寸舱段模型热结构/热匹配试验研究中.经试验验证，所建立的长时间大功率燃气流风洞试验设计方法有效可行，实现了全尺寸舱段飞行热环境的有效模拟. 

Thermal Structure Test of Full-Scale Cabin Component in 200 MW High Temperature Tunnel

A thermal structure and thermal match test of a full-scale cabin component was conducted in a 200 MW high temperature combustion-heated tunnel. New test methods were developed for some key techniques like tunnel state adjustment, effect of test medium and long term heat flow measurement. New methods of combustion-heated tunnel operation design and equivalent cold-wall heat-flux correction considering combustion gas effects were applied. Long term heat flow evaluation method was also used to simulated variable heat flux boundary conditions at the same test trajectory. The technology method was applied to a full-scale cabin component test successfully. The experiment results show that the aero-heating environments were exactly simulated and the technique was effective and feasible.