摘要
对一种用于涡轮基组合发动机的扩压器进行了型面设计和性能分析。该扩压器进口与二维超声速进气道出口相连。设计过程中,将扩压器分为进口段、二维扩压段和出口等截面段,采用几何方法设计,并采用CFD数值模拟方法计算了扩压器流场,从设计和计算结果可以看出,扩压器出口总压和马赫数分布随着出口等截面段长度的增加而变得均匀,出口静压提高使得位于二维扩压段的正激波前移,在设计要求的反压范围内,正激波一直处于喉部之后,符合扩压器的设计要求。最后本文分析了采用"中襟翼"法控制流动分离并提高扩压器性能的方法。
A TBCC（Turbine Based Combined Cycle） engine used transonic diffuser is designed and its performance is analyzed. Diffuser entrance is connected to inlet throat. The whole diffuser is divided into three parts：entrance part,2D expand part and equal section part. Geometrical method is used in the design process. Diffuser flow fields are obtained with the same entrance condition and different back pressure by CFD numerical method, from which we can see that diffuser section total pressure distribution become more uniform with the exit equal section part length expanded. The increasing of exit static pressure would lead to the result that normal shock moves upstream and still keeps after the throat,which satisfy the diffuser design requirement. At last,diffuser performance is improved by adding mesoflap,and the result sustained their expectation.
出处
《空气动力学学报》
EI
CSCD
北大核心
2008年第4期523-525,543,共4页
Acta Aerodynamica Sinica
基金
国防基础科研预研基金(A0420060522)
关键词
扩压器
附面层
分离控制
diffuser
boundary layer
separation control
