一种通用涡轴发动机起动过程建模方法研究

推进技术 ›› 2017, Vol. 38 ›› Issue (6): 1386-1394.

一种通用涡轴发动机起动过程建模方法研究

居新星,张海波,陈浩颖

南京航空航天大学能源与动力学院，江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院，江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院，江苏省航空动力系统重点实验室，江苏南京 210016

发布日期:2021-08-15
作者简介:居新星，男，硕士生，研究领域为航空发动机控制。E-mail:15705186380@163.com 通讯作者:张海波，男，教授，研究领域为航空发动机建模及控制。
基金资助:
国家自然科学基金(51576096)；江苏省普通高校研究生科研创新计划项目(SJLX16_0095)；中国高校基本科研

A Research on Start-Up Modeling for Turbo Shaft Engines

Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power System，Nanjing 210016，China,Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power System，Nanjing 210016，China and Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power System，Nanjing 210016，China

Published:2021-08-15

摘要/Abstract

摘要： 涡轴发动机可靠、快速的起动过程是进入驱动旋翼飞行器安全工作的前提，高置信度的发动机起动过程模型不仅可以对起动过程进行分析与优化控制，而且减少了代价昂贵的发动机台架试车次数。本文针对起动过程复杂非线性特性的建模难题，提出一种通用的建模方法:即基于级累叠方法，根据进口条件计算各级气体流动参数来获得压气机低转速特性数据，同时根据相似原理外推出燃气涡轮、自由涡轮低转速部件特性，并将冷转动模型和部件级模型相结合。最后，建立了涡轴发动机起动模型，进行了地面状态起动过程的数字仿真，并与试车数据进行对比，最大误差小于10%，结果表明所建立的模型能准确模拟涡轴发动机的起动过程。

关键词: 涡轴发动机；起动建模；部件级模型；级累叠法

Abstract: A reliable and quick starting process of turbo shaft engines is the premise of safety work into the drive of rotor aircraft，a starting process model with high fidelity can help to analyze and optimize the starting process of engines and the cost of rig tests will be reduced. To solve complex nonlinear characteristics of modeling problems in the starting process，a general modeling method named stage-stacking method is put forward，according to the inlet conditions，to obtain the low-speed characteristics data of compressor，the flow parameters of all stages are calculated .On the basis of similarity principle，the low-speed characteristics data of gas turbine and free turbine is calculated. The startup model proposed is a combined calculation for component level cooperated-working and cold working before ignition. Finally a startup model for some turbo-shaft engine is established，and the digital simulation under the standard ground state is conducted. Compared with the rig test data，the maximum error is less than 10%. The results show that the established model can be applied to simulate the starting process for the turbo shaft engine.

Key words: Turbo shaft engine；Startup modeling；Component-level model；Stage-stacking method

居新星,张海波,陈浩颖. 一种通用涡轴发动机起动过程建模方法研究[J]. 推进技术, 2017, 38(6): 1386-1394.

JU Xin-xing,ZHANG Hai-bo,CHEN Hao-ying. A Research on Start-Up Modeling for Turbo Shaft Engines[J]. Journal of Propulsion Technology, 2017, 38(6): 1386-1394.

参考文献

[1] 张书刚, 郭迎清, 陆军. 基于GasTurb/MATLAB的航空发动机部件级模型研究[J]. 航空动力学报, 2012, 27(12): 2850-2856.
[2] 黄开明, 周剑波, 刘杰, 等. 涡轴发动机起动过程的一种气动热力学实时模型[J]. 航空动力学报, 2004, 19(5): 703-707.
[3] Lietzau K, Kreiner A. Model Based Control Concepts for Jet Engines[C]. Louisiana: Proceedings of ASME Turbo Expo, 2001.
[4] Myers L P, Walsh K R. Performance Improvements of an F-15 Airplane with an Integrated Engine-Flight Control System[J]. Journal of Aircraft, 1992, 28(12): 812-817.
[5] Kern J M, Qu R, Young C D. Integrated Boost Cavity Ring Generator For Turbofan and Turbo Shaft Engines[P]. US: US8198744, 2012.
[6] 于达仁, 郭玉锋, 牛军, 等. 涡喷发动机风车起动工况的神经网络建模[J], 推进技术, 2001, 22(3):183-186 . (YU Da-ren, GUO Yu-feng, NIU Jun, et al. Turbojet Modeling in Windmilling Based on Radial Basis Function Networks[J]. Journal of Propulsion Technology, 2001, 22(3): 183-186.)
[7] 卓刚. 航空发动机智能建模与故障诊断研究[D]. 南京:南京航空航天大学, 2004.
[8] 刘建勋, 王剑影, 李应红. 某型发动机起动建模的支持向量机辨识及应用[J]. ?推进技术, 2004, 25(5):401-404. (LIU Jian-xun, WANG Jian-ying, LI Ying-hong, et al. An Identification Model of Aero Engine Starting Based on Support Vector Machine and Its Application[J]. Journal of Propulsion Technology, 2004, 25(5): 401-404.)?
[9] 李永进, 张海波, 张天宏. 一种考虑非线性余项的机载发动机自适应模型建立及其在寻优控制中的应用[J]. 推进技术, 2016, 37(1): 172-180. (LI Yong-jin, ZHANG Hai-bo, ZHANG Tian-hong. Establishment and Application in Performance Seeking Control of an on-Board Adaptive Aero-Engine Model Considering Nonlinear Remainders [J]. Journal of Propulsion Technology, 2016, 37(1): 172-180.)
[10] 郑前钢, 张海波, 李永进. 基于单纯B样条的航空发动机机载稳态模型研究[J], 推进技术, 2015, 36(12): 1889-1893. ( ZHENG Qian-gang, ZHANG Hai-bo, LI Yong-jin. Research on Simplex B-Splines Algorithm in on-Board Steady State Modeling of Turbofan Engines[J]. Journal of Propulsion Technology, 2015, 36(12): 1889-1893.)
[11] 孙丰勇, 张海波, 叶志锋, 等. 航空发动机超声速巡航性能寻优控制研究[J], 推进技术, 2015, 36(8): 1248-1256. (SUN Feng-yong, ZHANG Hai-bo, YE Zhi-feng, et al. A Study of Aero-Engine Supersonic Cruise Performance Seeking Control [J]. Journal of Propulsion Technology, 2015, 36(8): 1248-1256.)
[12] 周文祥. 航空发动机及控制系统建模与面向对象的仿真研究[D]. 南京:南京航空航天大学, 2006.
[13] 姚文荣. 涡轴发动机/旋翼综合建模控制及优化研究[D]. 南京:南京航空航天大学, 2008.
[14] 杨刚, 孙健国, 黄向华, 等. 一种不需要迭代的发动机辅助变量建模方法[J]. 航空动力学报, 2003, 18(2): 289-294.
[15] Snyder C A, Thurman D R. Gas Turbine Characteristics for a Large Civil Tilt-Rotor (LCTR)[M]. Cleveland: National Aeronautics and Space Administration, Glenn Research Center, 2010.
[16] Yazar I, Kiyak E, Caliskan F. A New Approach for Compressor and Turbine Performance Map Modeling Using ANFIS Structure[M]. GER: Progress in Exergy, Energy, and the Environment, Springer International Publishing, 2014: 541-551.
[17] Vance J M, Royal A C. High-Speed Rotor Dynamics- an Assessment of Current Technology for Small Turboshaft Engines[J]. Journal of Aircraft, 2012, 12(4).
[18] Ryan D May, Jeffrey Csank, Thomas M Lavelle, et al. A High- Fidelity Simulation of a Generic Commercial Aircraft Engine and Controller[R]. AIAA 2010-6630.
[19] Karpman B, Shade J L, Kane D E. Controlling Turbine Blade Tip Clearance According to Thermal Growth Model[P]. EP: EP1314857, 2006.(编辑:梅瑛)　　　　　　　　　　　　　*　收稿日期:2016-01-26；修订日期:2016-03-25。基金项目:国家自然科学基金(51576096)；江苏省普通高校研究生科研创新计划项目(SJLX16_0095)；中国高校基本科研业务费专项资金资助。作者简介:居新星,男,硕士生,研究领域为航空发动机控制。E-mail:15705186380@163.com通讯作者:张海波,男,教授,研究领域为航空发动机建模及控制。E-mail: zh_zhhb@126.com