Numerical simulation of Steady Air injection flow control effects on a transonic axial flow compressor

摘要：

In this work, steady air injection upstream of the blade leading edge was used in a transonic axial flow compressor, NASA rotor 37. The injectors were placed at 27 ％ upstream of the axial chord length at blade tip, the injection mass flow rate is 3％ of the chock mass flow rate, and 3 yaw angles were used, respectively -20°, -30°, and -40°. Negative yaw angles were measured relative to the compressor face in opposite direction of rotational speeds. To reveal the mechanism, steady numerical simulations were performed using FINE/TURBO software package. The results show that the stall mass flow can be decreased about 2.5 ％, and an increase in the total pressure ratio up to 0.5％.

关键词： tip injection flow control transonic axial flow compressor numerical simulation

作者: BENHEGOUGA lslem YANG Ce

作者单位: School of Mechanical Engineering, Beijing Institute of Technology, Beijing 100081, China

会议类型: 国际会议

会议名称: 2012 International Conference on Industiial Design and Mechanical Power(2012工业设计与机械动力国际会议 ICIDMP 2012)

会议地点: 黄山

会议语种:英文

页码: 352-357

在线出版日期: 2012-07-10（万方平台首次上网日期，不代表论文的发表时间）