DESIGN OF INTEGRATED TURNING VANES FOR A COMPRESSOR TRANSITION DUCT

摘要

Compressor transition ducts are used to connect the booster or intermediate-pressure compressor (IPC) with the high-pressure compressor (HPC) in 2- and 3-spool turbofan engine configurations respectively. At high by-pass ratios the radial offset between the compressors can be substantial. In order not to make the duct longer than necessary there is a need for an "aggressive" duct aero-design, implying a large aspect ratio (Ar/L) duct. By introducing an integrated turning vane concept, additional length reduction of the upstream compressor is possible. This paper presents a study where the last compressor stator row is removed and turning vanes are placed in the compressor duct. A comparison, in terms of performance and weight, is made to a conventional configuration, where the stators remain and symmetrical non-turning struts are placed in the compressor duct.