基于安装性能的航空发动机中间状态喷管调节计划优化  

Optimization of aero-engine nozzle control schedule under the maximum dry thrust condition based on installation performance

作　　者：谢业平[1] 尚守堂[1,2] 李建榕[1] 施磊[1] 

机构地区：[1]中国航空工业集团公司沈阳发动机设计研究所,沈阳110015 [2]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《航空动力学报》2014年第1期175-180,共6页Journal of Aerospace Power

摘　　要：以Matlab为平台,结合MS-DOS命令和计算流体动力学(CFD)软件操作日志,成功实现将发动机零维总体性能计算程序和二维喷管内外流场CFD软件结合的数值缩放技术.为优化飞机推进系统巡航状态性能,耦合飞机后体阻力优化航空发动机喷管喉道面积、喷管出口面积的调节计划.计算结果表明:在保持发动机稳定裕度的前提下,如仅优化喷管出口面积,在大马赫数飞行状态时安装推力提高超过1%.A zooming technology was implemented by combining aero-engine zero dimensional performance code and computational fluid dynamics （CFD） software for simulating two-dimensional nozzle inner/outer flow. The research was conducted based on Matlab with the incorporation of MS-DOS command and CFD operational log. To optimize the cruise per- formance of aircraft propulsion system and aircraft afterbody drag, the control schedule of aero-engine nozzle throat area and exit area was investigated. The results show that the installed thrust of aero-engine is improved over 1% in the flight condition of high Mach number only by optimizing the schedule of nozzle exit area, while maintaining the stability margin of aero-engine.

关 键 词：数值缩放技术 航空发动机喷管 非安装推力 后体阻力 调节计划 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]