Simulation and analysis of temperature of aviation engine fuel system based on Flowmaster software

被引：0
|
作者：
Kang S. [1 ]
Xi X. [1 ]
Li B. [2 ]
Zhang B. [1 ]
机构：
[1] Key Laboratory of Complex Energy Conversion and Utilization School of Energy and Power Engineering, Dalian University of Technology, Dalian, 116024, Liaoning
[2] Aero Engine Control System Institute, Aero Engine Corporation of China, Wuxi, 214063, Jiangsu
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2020年 / 35卷 / 04期
关键词：
Aviation engine fuel system; Flowmaster software; Fuel temperature; Return fuel to the aircraft; Temperature simulation;
D O I：
10.13224/j.cnki.jasp.2020.04.006
中图分类号：
学科分类号：
摘要：
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 0kg/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. © 2020, Editorial Department of Journal of Aerospace Power. All right reserved.
引用
收藏
页码：722 / 731
页数：9
相关论文
共 18 条
  • [11] Liu Q., Investigation on 1D/3D coupling simu lation on pump system during transient process, (2013)
  • [12] Wang L., The simplified technology of fuel system model based on the flowmaster software, China Science and Technology Information, 9, pp. 68-71, (2014)
  • [13] Chen Y., Heat sink calculation and the analysis of thermal management for aircraft fuel system, (2014)
  • [14] Tang M., Hu Y., Wang Q., Et al., Unsteady simulation of thermal management system of a simplified aircraft model, Journal of Chongqing Institute of Technology (Natural Science), 31, 3, pp. 58-65, (2017)
  • [15] Deng H., Zhang C.B., Xu G., Et al., Den sity measurements of endothermic hydrocarbon fuel at sub and supercritical conditions, Journal of Chemical and Engineering Data, 56, 6, pp. 2980-2986, (2011)
  • [16] Deng H., Zhu K., Xu G., Et al., Isobaric specific heat capacity measurement for kerosene RP-3 in the near-critical and supercritical regions, Journal of Chemical and Engineering Data, 57, 2, pp. 263-268, (2012)
  • [17] Zhou H., Wen J., Deng H., Et al., Ex periment of multi-component hydrocarbon fuels RP-3 thermal conductivity, Journal of Beijing University of Aeronautics and Astronautics, 39, 10, pp. 1387-1391, (2013)
  • [18] Jia Z., Xu G., Deng H., Et al., Dy namic viscosity measurements of aviation hydrocarbon fuel RP-3 at sub-critical pressures, Journal of Beijing University of Aeronautics and Astronautics, 40, 7, pp. 934-938, (2014)
12