| 本文已被：浏览 2217次 下载 604次 |
码上扫一扫！ |
|
|
| 航空发动机部件级模型实时性提高方法研究 |
|
殷 锴1,周文祥2,3,乔 坤2,4,王鸿钧1,黄金泉2,3
|
|
(1. 中航商用航空发动机有限责任公司，上海 200241;2. 南京航空航天大学 江苏省航空动力系统重点实验室，能源与动力学院，江苏 南京 210016;3. 先进航空发动机协同创新中心，北京 100191;4. 中航工业航空动力控制系统研究所，江苏 无锡 214063)
|
|
| 摘要: |
| 基于大涵道比涡扇发动机部件级模型，从减少单次流路计算耗时和降低单步流路计算次数两方面研究提高模型实时性的方法。测试并分析了发动机各模块单步计算耗时，通过建立气体热力属性插值表，使模型单次流路计算耗时减少80%，在3.3GHz Intel CPU平台下模型单次流路计算耗时0.02ms，在168MHz STM32F407硬件平台下耗时1.55ms。研究了不同收敛残差对模型流路计算次数及仿真精度的影响。仿真结果表明:相比Newton-Raphson法，Broyden法流路计算次数更少；将迭代求解残差由0.0001调整至0.001或0.005，模型流路计算次数显著减少，低压转速仿真偏差在0.2%以内。 |
| 关键词: 涡扇发动机 部件级模型 实时性 流路计算 Broyden法 |
| DOI： |
| 分类号: |
| 基金项目:国家自然科学基金面上项目(51276087)；中央高校基本科研业务费专项资金(NS2015027)。。 |
|
| Research on Methods of Improving Real-Time Performance for Aero-Engine Component-Level Model |
|
YIN Kai1,ZHOU Wen-xiang2,3,QIAO Kun2,4,WANG Hong-jun1,HUANG Jin-quan2,3
|
|
(1. AVIC Commercial Aircraft Engine Co.，Ltd，Shanghai 200241，China;2. Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of
Aerospace Power System，Nanjing 210016，China;3. Collaborative Innovation Center for Advanced Aero-Engine，Beijing 100191，China;4. Aviation Motor Control System Research Institute，Wuxi 214063，China)
|
| Abstract: |
| Based on the Component-Level Model(CLM)of a high-bypass-ratio turbofan engine，the ways to improve the real-time performance of CLM were achieved through reducing one flow path calculation time and decreasing the number of one-step calculations. The calculation time of each computation module during one flow path calculation was tested and analyzed. By setting up an interpolation table of gas thermodynamic properties，the one flow path calculation time has been reduced by 80%，which is about 0.02ms on the platform of 3.3GHz Intel CPU and 1.55ms on that of 168MHz TM32F407. Besides，the effects of different convergence residuals on the model flow path calculations number and simulation accuracy were compared and analyzed. Simulation results show that the number of model one-step calculations using Broydenmethod is less than that of using Newton-Raphson method.By adjusting the iterative solving residual from 0.0001 to 0.001 or 0.005，the number of model one-step calculations could be significantly reduced while keeping the simulation error of low pressure rotor speed within 0.2%. |
| Key words: Turbofan engine Component-level model Real-time performance Flow path calculation,Broyden method |
