Flight gas turbine engine i.e. turbomachine, has flow guide element designed as radiator element, and core thruster surrounded by by-pass channel, where partial flow is conducted from channel through engine casing for cooling core thruster

摘要

The engine has a core thruster (10) surrounded by a by-pass channel (29), which is radially limited from inside a core engine casing (21). A partial flow (30) is radially and inwardly conducted from the by-pass channel through the core engine casing for cooling the core thruster. The partial flow is derived by a ring portion, and a flow guide element is arranged in the ring portion. The flow guide element is designed as a radiator element e.g. matrix radiators and surface coolers, and extends annularly along circumferential direction and axial direction.