Numerical Simulation and Performance Analysis on Start Process of Missile Turbojet Engine Windmill

YANG Xin-yi;SHEN Wei;LIU Hai-feng;DONG Ke-hai;WANG Yong-hua

CN Submission Journal Articles Figures Search
Adv. Search

  • Sponsored by: China Association for Science and Technology (CAST)

    Editor-In-Chief: Xu Yida

    ISSN 1000-1093

    　

  • Hosted By: China Ordnance Society

    Published By: Acta Armamentarii

    CN 11-2176/TJ

Acta Armamentarii, a Chinese monthly journal, was first published in 1979. The journal is supervised by China Association for Science and Technology, sponsored by China Ordnance Society，and edited and published by Editorial Board of Acta Armamentarii. The Journal is included in all important domestic databases，and also collected by Engineering Index (EI, USA), Chemical Abstracts (CA, USA), Science Abstracts (SA, UK）, Abstract Journal (AJ, Russia), and Current Bibliography on Science and Technology(CBST).Acta Armamentarii has been selected into the journal Of Ordnance Science and Technology (Weapons Industry) Field Of High Quality Scientific and Technological Periodical Classification Catalogue (2022 edition), ranking T1, and the journal of Automotive Engineering Field of High Quality Scientific and technological Periodical classification Catalogue, ranking T2.
Acta Armamentarii ›› 2011, Vol. 32 ›› Issue (1) : 37-44. DOI: 10.3969/j.issn.1000-1093.2011.01.007
Paper

Numerical Simulation and Performance Analysis on Start Process of Missile Turbojet Engine Windmill

  • YANG Xin-yi， SHEN Wei， LIU Hai-feng， DONG Ke-hai， WANG Yong-hua
Author information +
History +

Abstract

A new simulation strategy was proposed for the start process of missile turbojet engine windmill according to its characteristic. The simulation consists of two phases: the windmill process before ignition and the acceleration process after ignition. The former is simulated using radial basis function networks (RBFN)，and the latter which model is a set of nonlinear equations is solved using particle swarm optimization (PSO) algorithm. The introduction of PSO helps to solve the divergence problem of nonlinear equations caused by traditional iteration method when the initial condition is far from real solution. The results are in agreement with test data, which shows that the presented model has a higher accuracy. The start processes at the different ignition times were simulated, and the results were analyzed synthetically. The analysis shows how the ignition time affects the acceleration performance of the engine windmill start, which provides a theoretical foundation for igniting time optimization.

Key words

propulsion system of aviation & aerospace / missile propulsion / turbojet engine / windmill / moving least square / particle swarm optimization / acceleration performance

Cite this article

EndNote

Ris (Procite)

Bibtex

Download Citations
YANG Xin-yi， SHEN Wei， LIU Hai-feng， DONG Ke-hai， WANG Yong-hua. Numerical Simulation and Performance Analysis on Start Process of Missile Turbojet Engine Windmill. Acta Armamentarii. 2011, 32(1): 37-44 https://doi.org/10.3969/j.issn.1000-1093.2011.01.007

References

［1］ 于军,于守志. 弹用涡喷发动机飞行试验启动加速性能仿真［J］. 推进技术
， 2001,22(6):454-457.
YU Jun, YU Shou-zhi. Starting and accelerating model of missile turbojet engine
in flight test［J］. Journal of Propulsion Technology, 2001, 22(6):454-457. （i
n Chinese）
［2］ ZhaoQ S. Calculation of wind milling characteristics of turb
ojet engines［J］. ASME Journal of Engineering for Power, 1981,103(1):1-12.
［3］ Chappell M A. Approach to modeling continuous turbine engine operation fr
om startup to shutdown［M］. Journal of Propulsion and Power, 1993，9(3):466-471
.
［4］ 于达仁，郭钰锋，牛军. 涡喷发动机风车启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. Turbojet modeling in windmilling based on rad
ial basis function net works［J］. Journal of Propulsion Technology, 2001, 22(3)
:183-186. （in Chinese）
［5］ 武志文，于达仁，牛军. 基于ANFIS的涡轮发动机风车工况建模仿真［J］.
推进技术, 2005,26(2):162-166.
WU Zhi-wen, YU Da-ren, NIU Jun. Turbojet modeling and simulation based on ANFI
S［J］. Journal of Propulsion Technology, 2005,26(2):162-166. （in Chinese）
)〗
［6］ 苏三买. 遗传算法及其在航空发动机非线性数学模型中的应用研究［D］.
西安：西北工业大学，2002.
SU San-mai. Research on Genetic algorithm and the application in aeroengine non
linear model［D］. Xi’an： Northwest Polytechnical University,2002. （in Chines
e）
［7］ Yang X Y, Pang S. The aeroengine model based on improved PSO algorithm［C］∥The 2nd International Symposium on Jet Propulsion and Power Engineering, Beijing: Beihang University, 2008, 2: 585-588.
［8］ 黄家骅, 冯国泰, 牛军，等. 涡轮效率改变对发动机加速特性的影响［J］.
推进技术，2003，24(4):368-372
HUANG Jia-hua, FENG Guo-tai, NIU Jun，et al. Effect of turbine efficiency chan
ging on turbo engine’s accelerating characteristic under closed loop control mo
del［J］. Journal of Propulsion Technology, 2003，24(4):368-372. （in Chinese）
［9］ 王占学, 刘增文. 某型燃气涡轮发动机风车状态内阻力的计算［J］. 燃气
涡轮试验与研究, 2006，19(3):8-10.
WANG Zhan-xue，LIU Zeng-wen. The calculation of windmilling characteristics of
a gas turbine engine［J］. Journal of Gas Turbine Experiment and Research, 2006
，19(3):8-10. （in Chinese）
［10］ 陆瑶, 张立堂,于守志. 吸气式发动机试验中空气流量的计算［J］. 推进
技术，2001，22(6):489-492
LU Yao, ZHANG Li-tang, YU Shou-zhi. Calculation of air mass flow in air breath
ing engine test［J］. Journal of Propulsion Technology, 2001，22(6):489-492. （i
n Chinese）
［11］ 杨欣毅，沈伟，刘海峰，等. 一种应用滑动最小二乘求解压气机特性的方
法［J］. 航空动力学报，2009，24(8):1741-1746.
YANG Xin-yi， SHEN Wei， LIU Hai-feng， et al. Compressor characteristics gene
ration method using moving least square［J］. Journal of Aerospace Power，2009，
24(8):1741-1746. （in Chinese）
［12］ KennedyJ， Eberhart R. Particle swarm optimization［C］∥Pr
oceedings of IEEE International Conference on Neural Networks，Piscataway： IEEE
Service Center，1995，4：1942-1948.

339

Accesses

0

Citation

Detail
Sections
Recommended

/

〈 〉