高超声速飞行器的热电技术热管理系统参数

Parametric of an integrated thermoelectric generation thermal management system for hypersonic vehicle

提出了集成热电发电装置的超燃冲压发动机热管理系统,将热电发电器与发动机壁面结构相结合。集成的热电发电热管理系统可以将传入发动机壁面的热量部分转换为电能,同时减少了冷却用燃料流量,"间接"提高了燃料的吸热能力。燃料在冷却过程中提高了自身温度和焓值,具有一定的做功能力。高温高压的燃料经过涡轮机膨胀做功,输出可以被高超声速飞行器利用的能量。采用热力学的分析方法对集成热电发电热管理系统的相关参数进行研究,结果表明其比传统的再生冷却防热具有极好的潜在优势,提升了燃料的吸热能力,同时对外输出了可用功。

An integrated thermoelectric generation thermal management system for a regenerative cooling scramjet was proposed. Thermoelectric power generators were integrated in the scramjet structure. The integrated thermoelectric generation thermal management system reduces the fuel flux for cooling, through converting part of the energy by heat conduction on the scramjet structure to electric power. The heat that must be taken away by fuel is decreased and the fuel cooling capacity is indirectly increased. At the same time, high temperature and high pressure fuel also has the capacity for doing work. It flows through a turbine and get additional power output for the use of hypersonic vehicle. A parametric study of the integrated thermoelectric generation thermal management system for scramjet was performed. It is known through performance analysis that the integrated thermoelectric generation thermal management system has excellent potential performance over the conventional regenerative cooling. The fuel flux is reduced while the integrated thermoelectric generation thermal management system gives power output.