一种CARET进气道喉部附面层抽吸数值研究

何天喜; 王强

doi:10.13224/j.cnki.jasp.2018.09.026

一种CARET进气道喉部附面层抽吸数值研究

doi: 10.13224/j.cnki.jasp.2018.09.026

何天喜¹,
王强²

1.
北京航空航天大学能源与动力工程学院,北京 100191
2.
北京航空航天大学能源与动力工程学院,北京 100191；先进航空发动机协同创新中心,北京 100191

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出版历程
- 收稿日期: 2017-04-10
- 刊出日期: 2018-09-28

Numerical study on boundary layer suction at throat of a CARET inlet

摘要

摘要: 以一种CARET(后掠双斜切双压缩面)进气道为研究对象,设计喉道附面层抽吸槽以控制流动分离。采用CFD数值计算软件对进气道在设计点工况下（马赫数为2.0)下内、外流场进行计算,以总压恢复系数和进气道出口总压畸变为评价指标分析不同抽吸方案的效果。结果表明:喉道附面层抽吸能够稳定结尾正激波,削弱激波/附面层干扰,抑制流动分离,显著改善流场,提高总压恢复系数,减小出口畸变；喉道段抽吸槽位置靠前能够明显降低出口畸变；随着抽吸量的增大,附面层抽吸对进气道内特性性能提升的贡献越来越小。
- CARET进气道 /
- 附面层抽吸 /
- 流动控制 /
- 总压恢复系数 /
- 总压畸变
Abstract: To control the flow separation of a CARET inlet, the boundary layer suction slots at the throat of the inlet were designed. The commercial CFD software Fluent was used to simulate the flow field at the design point (Mach number of 2.0). Total pressure recovery and distortion at exit of inlet were used to evaluate the effectiveness of different devices. Simulation results indicated that boundary layer suction in throat can fix the normal shock in the throat and form a stable flow field. It can weaken the shockwave/ boundary layer interaction, suppress flow separation, remarkably increase the total pressure recovery and reduce the total pressure distortion at exit surface of inlet. The front placing slots at the throat section can decrease the distortion of exit surface obviously compared with a rear position. As the suction mass flow increased, the inlet performance firstly became better, and then leveled off.
- CARET inlet /
- boundary layer suction /
- flow control /
- total pressure recovery coefficient /
- total pressure distortion

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参考文献(18)

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