基于安装性能的航空发动机中间状态喷管调节计划优化

谢业平; 尚守堂; 李建榕; 施磊

doi:10.13224/j.cnki.jasp.2014.01.023

基于安装性能的航空发动机中间状态喷管调节计划优化

doi: 10.13224/j.cnki.jasp.2014.01.023

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

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出版历程
- 收稿日期: 2012-11-30
- 刊出日期: 2014-01-28

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

1.
Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China
2.
School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

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%.
- 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
Abstract: 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 performance 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.
- numerical zooming technology /
- aero-engine nozzle /
- uninstalled thrust /
- afterbody drag /
- control schedule

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参考文献(15)

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