论文部分内容阅读
为揭示径向进气总压畸变对压气机气动稳定性影响的物理机制,分别开展了尖部和根部进气总压畸变对压气机稳定边界以及动态失速过程影响的试验研究。结果表明,均匀进气时,压气机在叶尖区域首先形成失速团;径向总压畸变会引起气流参数的径向分布发生变化,其中尖部进气总压畸变会增加叶尖区域的攻角,导致压气机失速提前,而根部进气总压畸变则会改善叶尖区域的流场,降低攻角,使压气机失速延迟;气流参数径向分布变化也会影响动态失速过程中模态波扰动和失速团的三维扩散过程。
In order to reveal the physical mechanism of the total pressure distortion of the radial inlet on the aerodynamic stability of the compressor, experimental studies on the effects of tip pressure and total inlet air pressure on the stability of the compressor and the dynamic stall process are carried out. The results show that the compressor will firstly form a stalled mass in the tip region when the air is uniformly injected. The radial total pressure distortion will cause the radial distribution of the air flow parameters to change. The total pressure distortion at the tip will increase the attack of the tip region Angle, leading to the compressor stall ahead of time, while the root of the total pressure distortion of the inlet tip area will improve the flow field and reduce the angle of attack, the compressor stall delay; changes in the radial distribution of airflow parameters will also affect the dynamic stall mode Wave disturbance and the three-dimensional diffusion process of the group.