Fluid flow guiding device and a gas turbine engine

Abstract

The invention concerns a flow guide device for a gas turbine engine, in particular an aircraft engine, with a fan and a bypass duct downstream of the fan, wherein the bypass duct is arranged radially between an engine nacelle and a core engine of the gas turbine engine, characterized by a guide vane assembly with load-bearing guide vanes and additional guide vanes in the bypass duct, wherein the load-bearing guide vanes are integrally connected to a structural component of the gas turbine engine, and the additional guide vanes are connected to the structural component via connecting means. The invention furthermore concerns a gas turbine device.

Dependencies are inferred from the claim text.