Rotating Stall and Surge
Co-existing of Rotating Stall and Surge in an axial Compressor
Axial compressors are an essential component that supports various industries.Their uses are diverse, and they are particularly crucial for gas turbine engines, which are used in aviation jet engines and power generators.
In these engines, axial compressors are a significant component that deeply affects their performance.
Given these needs, improving the performance and efficiency of axial compressors has been a major challenge for some time.
Many research reports have been published on various topics such as optimizing blade shape and suppressing secondary flow.
One effective method to improve the performance and efficiency of axial compressors is to operate them near the maximum pressure rise.
However, at such high-load operating points, it is difficult to secure sufficient stall margin, making it easy to fall into unstable states such as rotating stall or surge due to external disturbances such as inlet distortion or abnormal combustion in the combustor.
These unstable phenomena not only cause a deterioration in compressor performance but also pose a risk of compressor damage or destruction.
Therefore, it is essential to clarify these unstable phenomena and develop control methods.
To tackle these issues, three research themes are being pursued in parallel:
１）Active stall control through jet injection
２）Fundamental research on surge and rotating stall
３）Computational fluid dynamics
Visuallization of Rotating Stall Cell by using exprimental and CFD results