Aerodynamic study of a gooseneck

The study of the flow behavior within an inter-compressor channel has become an increasingly interesting material in new generation engine configurations. The big difference in the diameters of the low and high-pressure components requires an annular connection channel that increases its geometric aggressiveness more and more. In addition to the centrifugal effects deriving from the shape of the channel itself, the presence of blades inside the duct exerts a high influence. These faired devices are necessary for the passage of various wiring and equipment and for the redirection of the flow to provide the cleanest and uniform input to the downstream modules. The coupled effect of the shape of the channel and the presence of these devices has a great impact on diffusion and on boundary layer destabilization. The present work, carried out within the company Safran Aircraft engines, aims to represent a global analysis on the issue of the inter-compressor channel. A prior bibliographic study is followed by a geometric analysis and one and two-dimensional estimation of pressure drops. A numerical CFD study is conducted at the end of the paper for comparative and validation purposes.