Aerodynamic Design of the Cooling Flow Duct System for an Intercooled Aero Engine

摘要

This paper examines an intercooled concept for a large, high by-pass ratio, high overall pressure ratio aero-engine. Specifically the paper describes the aerodynamic design of the diffusing duct system required to deliver cooling air from the bypass duct to the intercooler. Preliminary numerical design studies were used to identify a general duct layout which had the potential to meet the aerodynamic and geometrical constraints. Subsequently, a fully annular isothermal test facility, incorporating a 1? stage axial compressor, was used to evaluate a large range of potential configurations. Ultimately the feasibility of designing aerodynamic ducts within the relevant constraints was demonstrated and a future design strategy established.