Analysis of Aircraft Fuel Thermal Management System Under Different Architectures

The increasing number and power of electronic equipment on the aircraft causes a large amount of heat loss inside the aircraft. It is particularly important to conduct a reasonable thermal analysis on the aircraft. In this paper, four architectures of fuel thermal management system are proposed and analyzed. The difference among these four architectures is the flow directions of the fuel. The mass conservation and energy analysis are carried out for different parts of the four structures, and the differential equations of mass and energy are established. The heated fuel temperature and the fuel mass flow rate are the focuses. The variation of the heated fuel temperature of four architectures is calculated under fixed flight conditions. Under different flight conditions, the variation law of fuel mass flow with the flow parameters in the four architectures is analyzed with the value of the heated fuel temperature satisfying 421. The results show that only the dual-tank architecture with fuel recirculation split into 2 parts can meet the requirements under different flight conditions.