AIRCRAFT ENGINE, GAS TURBINE INTAKE THEREFORE, AND METHOD OF GUIDING EXHAUST GASSES

A gas turbine intake (16) has a swirl housing (42) having a tangential inlet (58) fluidly connecting an exhaust conduit, an annular outlet (52) defined around a central axis (36) and fluidly connecting a turbine gas path (34), a swirl path (44) extending circumferentially around the central axis (36) from the tangential inlet (58), and a plurality of vanes (56) located in the swirl housing (42), the vanes (56) circumferentially interspaced from one another relative the central axis (36), each vane (56) having a twisted and flat body having a length extending from a leading end (60) to a trailing end (62), the leading end (60) being oriented mainly circumferentially and axially at the swirl path (44), the trailing end (62) being oriented mainly axially and radially at the annular outlet (52), the twisted and flat body twisting between the leading end (60) and the trailing end (62) around the central axis (36), around a radial axis (70) perpendicular to the central axis (36), and around a tangential axis (68) perpendicular to both the central axis (36) and the radial axis (70).