Abstract: The present disclose provides a method of manufacturing a turbine component for a gas turbine engine, comprising: forming, by a casting process, a primary component; forming, by an additive manufacturing process, a secondary component, wherein the secondary component comprises a main air passageway extending therethrough; assembling the primary component and the secondary component together to form the turbine component, wherein the main air passageway of the secondary component forms part of an internal air flow path through the turbine component.

Abstract: Disclosed is an aerofoil for a gas turbine engine comprising: a first conduit formed in the aerofoil; a second conduit formed in the aerofoil; and a dividing wall separating the first and second conduits, the dividing wall comprising a transfer port configured to permit fluid flow between the first and second conduits; wherein the dividing wall further comprises a reinforcing boss at least partially encircling the transfer port. Also disclosed is a gas turbine engine comprising the aerofoil and an aircraft comprising the gas turbine engine.