航空燃油柱塞泵热模型及生热机理分析

Analysis of Thermal Model and Heat Generation of Aero Fuel Piston Pump

针对航空柱塞泵全工况下生热温升等问题,通过泄漏分析和机械损失分析等给出了热力学建模方法与生热原因分析。首先建立燃油柱塞泵三维模型和动力学模型,进而采用液压平衡油温方法建立考虑泄漏和增压的热力模型,并且建立考虑机械损失方面的动力学热力模型。通过试验与仿真对比表明,试验数据与仿真结果误差不大于1%,且泵后压力脉动在2MPa范围内,符合柱塞泵实际情况,该模型能够实现燃油柱塞泵生热机理研究。最后进行柱塞泵生热机理分析,表明泄漏生热和增压生热不会引起航空燃油柱塞泵异常发热,主要通过机械损失引起,且机械功率损失越大,柱塞泵壳体和转动部件温度越高。

Aiming at the heat rise of aero piston pump on full conditions, the paper gave a thermodynamic modeling method and heat cause analysis by studying mechanical losses and leakage analysis. Firstly, the fuel piston pump＇s 3 - D and dynamic models were given. Furthermore, hydraulic balance method was used to establish the oil leakage and pressurized thermal model, and also the thermodynamic and kinetic model considering the mechanical loss aspects. The experiments and simulation results show that the error of experimental data is less than 1%, and the pump pressure pulsation is within 2MPa, in line with the actual situation of piston pump. Finally, the analysis of heat mechanism shows that the leak heat and pressurization heat do not cause abnormal heat which is mainly caused by mechanical damage, and the greater the loss of mechanical power is, the higher the temperature of the piston housing and the rotational component is.