摘要
在高超声速飞行器翼前缘的热防护技术方面,采用内置高温热管是一种新型高效的热防护方法,其中C/C复合材料结构与内置高温热管之间的界面接触热阻对传热效率及热力耦合起着至关重要的作用。本文自主搭建了一套高温接触热阻试验平台,并针对三维编织C/C复合材料与高温合金GH600在不同界面应力、界面粗糙度及界面温度下的接触热阻进行了试验研究。研究结果表明本平台在进行高温接触热阻试验研究上是切实可行的,利用该试验平台得到了三维编织C/C复合材料与高温合金GH600之间接触热阻的变化规律,有关结果可以为中国新型内置高温热管热防护结构的设计及安全评估提供参考。
The heat pipe cooled leading edge is a novel and efficient thermal protection method in hypersonic aircraft design,and the thermal contact resistance between the C/C composite material structure and high-temperature heat pipes plays a very important role in heat transfer efficiency and thermomechanical coupling.A testing platform of high-temperature thermal contact resistance is established,with which the thermal contact resistance between a three-dimensional braid C/C composite material and a superalloy GH600specimen is tested under different interface pressures,interface roughnesses and temperatures.The results show that the present testing platform is feasible for the experimental investigation of high-temperature thermal contact resistance,and the thermal contact resistance between three-dimensional braid C/C composite material and superalloy GH600is obtained,which can be an important reference for the design and safety evaluation of heat pipe cooled thermal protection structures.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2010年第11期2189-2194,共6页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(10872104)
关键词
接触热阻
C/C复合材料
高温合金
试验研究
thermal contact resistance
C/C composite material
superalloys
experimental investigation
