Axial Compressor
Sweep Effect and Rotating Instability in an Axial Compressor
From the perspective of energy efficiency such as fuel economy and environmental consideration, aircraft engines require high efficiency.In the case of the axial compressor, one of the main components, reducing the number of stages and increasing the blade loading per stage is necessary for downsizing and weight reduction.
However, in high-load conditions, unstable operating states such as stall, surge, and blade row flutter are more likely to occur.
These unsteady phenomena not only lead to a decrease in compressor performance but also impose significant loads on the shaft and blade rows, potentially causing destruction due to increased vibration.
Therefore, for high-load operation of the axial compressor, improving stall margin to ensure stable operating conditions is urgently needed.
Our research is being conducted on phenomena such as leakage vortices from blade tips, secondary flow, and non-uniformity of compressor inlet flow (inlet distortion) in aircraft engine axial compressors.
Tested Axial Compressor
We are currently conducting research on the following topics:
１）Study on improving the performance of compressors through differences in static blade shapes
２）Study on the effect of forward sweep blades on distortion resistance performance
３）Comparison of compressor internal flow structures based on differences in blade shapes using numerical analysis
Internal Flow Filed of Sweep Rotor(Design and Near Stall Point)