A review on aero-engine inlet-compressor integration and inlet flow distortion in axial compressors.

Abstract

The air intake-compression systems of modern aircraft usually use the aero-engine intake and fan/compressor as the main components. Inlet-engine compatibility has always been the key to the stable and safe operation of the propulsion system, including the influence of inlet distortion on the compressor performance and stall margin. Since 1950, theoretical models and experiments on the flow stability and inlet distortion of axial compressors have been released. After the 1990s, numerical methods became important tools. In the 21st century, the new trends of aircraft propulsion system/inlet integration, blended wing body, and stealth capability led to a new direction for the inlet-engine flow matching problem. This review aims to combine the development of both the inlet and the axial compressor components, and provides an overview of the research history, latest progress, and prospects of compressor inlet distortion in inlet-engine compatibility problems. Analytical or numerical models, experiments, and simulations related to inlet distortion problems are summarized.