In order to study temperature rise of the fuel system under constant and variable speeds

based on the Flowmaster software and the Daqing RP-3

the aeroengine fuel system simulation model was established

the temperature simulation of engine was carried out

and experiment and simulation results were compared to verify the accuracy. Results showed that: the performance curve of components led to the calculation error. The maximum temperature was in the front of the main combustion chamber

up to 145 ℃ in some working cases

which could affect the safety of aeroengine

so the temperature of fuel must be controlled. The measure of taking fuel returning to the aircraft was useful. The temperature could not immediately achieve steady when the mass flow was instantly changed. With the rise of main combustion chamber flow

the fuel temperature declined when the returning mass flow was 0 kg/s and the centrifugal pump efficiency under different working conditions was equal. The temperature also achieved steady when mass flow was at a steady state. The calculation method of fuel temperature and fuel pump is proposed for the one-dimensional simulation further research of aviation engine system level.