空气涡轮起动机优化设计和匹配特性  

Optimization Design and Matching Performance of Air Turbine Starter

作　　者：陈靖华 徐伟祖 李传鹏[4] CHEN Jinghua;XU Weizu;LI Chuanpeng(Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration,Nanjing 211106,China;Nanjing Engineering Institute of Aircraft System,Jincheng Corporation,AVIC,Nanjing 211106,China;Nanjing Puguo Technology Co.,Ltd.,Nanjing 210000,China;College of Energy and Power Engineering,Nanjing University of Aeronautics&Astronautics,Nanjing 210016,China)

机构地区：[1]航空机电系统综合航空科技重点实验室,南京211106 [2]中国航空工业集团公司金城南京机电液压工程研究中心,南京211106 [3]南京普国科技有限公司,南京210000 [4]南京航空航天大学能源与动力学院,南京210016

出　　处：《南京航空航天大学学报》2023年第2期226-232,共7页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：为改善某型空气涡轮起动机的性能,并使其与辅助动力装置的引气特性匹配,采用数值仿真和试验相结合的方法,开展了某型空气涡轮起动机气动性能和流场细节的研究,并完成了导向器和涡轮级叶型优化设计,改型后涡轮流量增大了23.2%,效率提升了3.4%,功率增加了18.0%。数值仿真和试验结果的对比表明,流量整体差别较小,波动范围在±3%以内,均值为0.17%;功率差别最大为2.38%,最小为0.1%,符合性较好。数值仿真结果表明,空气涡轮起动机改型后与辅助动力装置的引气特性线存在共同工作点,实现了两者的匹配工作,改善了辅助动力装置的工作状况。In order to improve the performance of an air turbine starter and match it with the bleed characteristics of the auxiliary power unit,the aerodynamic performance and flow field details of the air turbine starter are studied by means of numerical simulation and experiment,and the optimal design of the guide and turbine stage blade is completed.After the modification,the mass flow,the efficiency and the power increase by 23.2%,3.4%and 18.0%,respectively.The comparison between numerical simulation and test results shows that the overall difference of flow is small,the fluctuation range is within±3%,and the mean value is equal to 0.17%.The maximum power difference is equal to 2.38%and the minimum is equal to 0.1%.The numerical simulation results show that there are common working points between the modified air turbine starter and the bleed characteristic line of the auxiliary power unit,and the working performance of the auxiliary power unit has been significantly improved.

关 键 词：空气涡轮起动机 数值仿真 试验 匹配性能 

分 类 号：V225[航空宇航科学与技术—飞行器设计] V228