The University of Tokyo
The University of Tokyo
Japan Aerospace Exploration Agency (JAXA)
Japan Aerospace Exploration Agency (JAXA)
The University of Tokyo
47th Fluid Dynamics Conference /the 33rd Aerospace Numerical Simulation Symposium (July 2-3, 2015. Institute of Industrial Science , the University of Tokyo), Meguro-ku, Tokyo, Japan
抄録（英）
It is known that the microjet blowing secondary air to the jet shear layer is effective in reducing jet mixing noise. One of the considerations for the microjet is a nozzle shape for injecting the secondary air. In the previous studies, the flow rate and the arrangements of microjet nozzles under cold jet were investigated. Considering the application of the microjet to the actual engine, however, it is necessary to grasp the acoustic characteristics under heated jet. In this paper, we applied the microjet nozzle of annular slit shape to the model-scale turbojet engine with changing the split number and cross sectional area of microjet and evaluated the far-field noise reduction effect.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
環状スリットノズルからの二次空気によるジェット騒音低減の試み
AA1630005003.pdf
(694.96KB)
