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康思昭,奚修智,李波.基于Flowmaster的航空发动机燃油系统温度仿真及分析[J].航空动力学报,2020,(4):722~731
基于Flowmaster的航空发动机燃油系统温度仿真及分析
Simulation and analysis of temperature of aviation engine fuel system based on Flowmaster software
投稿时间:2019-10-30  
DOI:10.13224/j.cnki.jasp.2020.04.006
中文关键词:  航空发动机燃油系统  温度仿真  Flowmaster软件  飞机回油  燃油温度
英文关键词:aviation engine fuel system  temperature simulation  Flowmaster software  return fuel to the aircraft  fuel temperature
基金项目:
作者单位
康思昭 Key Laboratory of Complex Energy Conversion and Utilization,School of Energy and Power Engineering,,Dalian University of Technology,Dalian Liaoning 116024,China
 
奚修智 Key Laboratory of Complex Energy Conversion and Utilization,School of Energy and Power Engineering,,Dalian University of Technology,Dalian Liaoning 116024,China
 
李波 Aero Engine Control System Institute,,Aero Engine Corporation of China,Wuxi Jiangsu 214063,China 
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全文下载次数: 186
中文摘要:
      采用大庆RP-3型燃油,利用Flowmaster软件对某型航空发动机燃油系统进行建模,计算定、变转速工况下燃油温升情况,开展了发动机变转速下的温度仿真,将仿真温度与实验温度值进行对比验证模型准确性。结果表明:模型精度主要受元件的性能曲线影响;某些工况下主燃烧室前的燃油温度可达145 ℃以上,影响发动机安全,必须加以控制;仿真发现向飞机回油可以降低燃油温度,但对于阶跃回油质量流量信号,温度响应具有延迟性;设计回油质量流量为0 kg/s,不同工况的离心泵效率相同,各工况的燃油温度与主燃烧室燃油质量流量的关系,质量流量增大,温度降低,质量流量稳定时,温度也会达到稳定值。该仿真主要是建立了燃油温度的求解模型,提出了燃油泵加热的计算方法,对于航空发动机系统一维仿真研究有一定的指导作用。
英文摘要:
      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 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.
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