航空发动机高空压力畸变试验  

Experiment on aero-engine altitude simulated pressure distortion

作　　者：田金虎[1,2] 乔渭阳[1] 彭生红[2] 

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]中国航空工业集团公司中国燃气涡轮研究院航空发动机高空模拟航空科技重点实验室,四川江油621703

出　　处：《航空动力学报》2014年第4期817-823,共7页Journal of Aerospace Power

摘　　要：鉴于航空发动机高空压力畸变试验的重要性,详细介绍了试验方案,通过插板,进行了航空发动机高空压力畸变试验,获得了基于插板扰流条件下的航空发动机气动稳定性特性,并初步获取了压力畸变、高空低雷诺数、引气和功率分出等关键降稳因子对该发动机稳定性影响的数量关系.压力畸变、高空低雷诺数以及引气、功率分出因素对临界综合畸变指数影响为:高度1km至高度18km,临界综合畸变指数降低了11.11%,高度1km至高度20km,临界综合畸变指数降低了14.69%.为航空发动机高空气动稳定性提供验证平台和试验数据支持.Because of the importance of experiment on aero-engine altitude simulated pressure distortion,the experimental project was discussed in detail.The experiment on aero-engine altitude simulated pressure distortion was launched by moving flashboard.The aerodynamic stability characteristic of aero-engine based on turbulent condition of moving flashboard was obtained,and the magnitude relations of key destabilizing factors such as pressure distortion,altitude low Reynolds number,air bleeding and power extraction to engine stability were obtained preliminarily.The effects of pressure distortion,altitude low Reynolds number,air bleeding and power extraction on critical complex total-pressure distortion descriptor are a fall of 11.11% of complex total-pressure distortion descriptor from altitude 1km to 18km and a fall of 14.69%from altitude 1km to 20km.It provides a testified platform and experimental database for aero-engine altitude aerodynamic stability.

关 键 词：高空模拟 雷诺数 压力畸变 稳定性 降稳因子 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]