Author:
Changbao Yang,Hui Zhou,Jingyang Zhang
Abstract
Abstract
A hybrid thermal management system model of hypersonic vehicle with liquid hydrogen as heat sink and thermoelectric conversion of Brayton cycle was established. The cooling effect, fuel flow demand and thermoelectric conversion characteristics of the thermal management system in flight envelope were studied by numerical simulation. The results show that the cooling fuel demand of refrigerant loop is about 0.22g/kW.s~0.24g/kW·s, that of aerothermal cooling fuel is about 0.11g/kW·s, and that of engine wall cooling fuel is about 0.08g/kW·s. The flow rate of engine wall cooling fuel can be saved by 25%∼40% during thermoelectric conversion. Thermoelectric conversion cycle efficiency and generation efficiency can reach up to 38% and 30%. When Mach number is 3.7∼4.2 under the condition of large aerodynamic heat load, the flow rate required for engine combustion is not enough to meet the cooling flow rate, and the maximum difference is 10%.
Reference18 articles.
1. Overview of Hypersonic Combat Platform [J];Mingsong;Avionics Technology,2016
2. A carbon dioxide purge and thermal protection system for liquid hydrogen tanks of hypersonic airplanes.[J];Anderson;Adv.cryog.eng,1967
3. Conceptual Study on Heat Resistant and Cooling System of Hypersonic Airplanes[C];Kojima,2011
4. Evaluation of thermal management for a Mach 5.5 hypersonic vehicle[J];Gasner,2013
Cited by
3 articles.
订阅此论文施引文献
订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献