A comprehensive review of numerical and experimental techniques for enhancing axial flow compressor performance under various flow conditions

The fan, compressors and turbines are the main rotating components of a modern aircraft turbofan engine. The stable and safe performance of the propulsion system always depends on the inlet and engine compatibility. Which also includes the distortion that occurs due to flow separation or uneven flow distribution. Such distortions impact the compressor’s performance and operational range. Earlier, only theoretical and experimental methods were utilized to analyze the flow stability and disturbance such as inlet distortion of an axial flow compressor. Later numerical methods were developed and utilized as the most effective tool. In this review article, both numerical and experimental analyses on the performance of axial flow compressors and respective components are highlighted. Additionally, the review article also discusses numerical models, experiments, and latest techniques, and simulations related to inlet distortion, rotor blades, and axial flow compressor inlets. In conclusion, this review article provides insights into probable solutions that can enhance compressor performance under different flow disturbances and instability. This article is suitable in identifying the cause for instability that occurs inside the axial flow compressor. This review article helps researchers who are interested in axial flow compressor turbomachinery by providing insights into the latest numerical and experimental methods that can enhance overall performance.