Computational Inlet Swirl Distortion Investigation of a High-Speed Compressor

Aero gas turbine engines are commonly supplied with straight-flowing air into the compressor, but recent high-efficiency aircraft configurations, such as Boundary Layer Ingestion (BLI), distort the flow of air into the engine. BLI turns the flowing air, causing flow angularity or swirl distortion. Swirl distortion affects the stability of the compressor, potentially hindering operability. The Society of Automotive Engineers S-16 Committee on Turbine Engine Inlet Flow Distortion is developing a methodology to assess compressor stability due to swirl distortion. The S-16 swirl methodology is initially explored in a computational study to prepare for an experimental investigation using a swirl generator, ultimately demonstrating the S-16 swirl methodology experimentally for a modern high-speed compressor.