Operational Characteristics of a Twin-Spool Turbofan Engine at Inlet Distortions with Reduced Surge Margin

The objective of this study is to investigate on an experimental basis the influence of different inlet distortions on the operational characteristics of a twin-spool turbofan engine representing a propulsion system application of a military aircraft. The inlet duct of a supersonic aircraft is a very sensitive component and plays a dominant role with respect to engine and aircraft performance. Its very complex shape,containing a S-duct,creates total pressure and swirl distortions and leads to an inhomogeneous air stream in the compressor inlet plane.