摘要
为提升平流层飞艇高度调节性能,针对低压环境下向副气囊充入超压空气的需求,设计了平流层低压涡轮空压风机。采用数值计算和有限元分析,通过一维风机气动计算分析、NREC软件参数设计等方法,对风机的关键参数进行初步设计与优化;通过CFD气动分析,进一步确认参数设计。完成低压涡轮空压风机样机的试制后,在模拟环境试验箱内进行了低温低压充气试验。试验结果表明:该风机能在低温低压环境下正常工作,充气速度完全满足副气囊充气要求。相较于传统设计,优化后的风机性能显著提升,为平流层飞艇气囊风机设计提供了有效借鉴和思路。
In order to improve the altitude adjustment performance of stratospheric airships and meet the demand for injecting overpressure air into the auxiliary gas bag in low-pressure environments,a stratospheric low-pressure turbine air compressor fan was designed.Using numerical calculations and finite element analysis,preliminary design and optimization of key parameters of the fan are carried out through one-dimensional aerodynamic calculation analysis and NREC software parameter design method.Further confirm the parameter design through CFD aerodynamic analysis.After completing the prototype of the low-pressure turbine air compressor,a low-temperature and low-pressure inflation test was conducted in a simulated environment test chamber.The test results indicate that the fan can operate normally in low-temperature and low-pressure environments,and the inflation rate fully meets the requirements for auxiliary gas bag inflation.Compared to traditional designs,the optimized fan performance has significantly improved,providing effective reference and ideas for the design of stratospheric airship gas bag fans.
作者
杨永强
黄宇
祖金戈
YANG Yongqiang;HUANG Yu;ZU Jin'ge(School of Mechanical and Electrical Engineering,Beijing Polytechnic College,Beijing 100042,China;Xi'an Jiazhong Electronics Technology Co.,Ltd.,Xi’an Shaanxi 710075,China)
出处
《北京工业职业技术学院学报》
2025年第2期5-9,共5页
Journal of Beijing Polytechnic College
基金
2024年北京工业职业技术学院重点科研课题(BGY2024KY-09Z)。
关键词
平流层飞艇
低压涡轮空压风机
低温低压环境
性能提升
stratospheric airship
low-pressure turbine air compressor
low-temperature and low-pressure environment
performance improvement
