The present disclose provides a method of manufacturing a turbine component (32) for a gas turbine engine, comprising: forming, by a casting process, a primary component (23); forming, by an additive manufacturing process, a secondary component (27), wherein the secondary component (27) comprises a main air passageway (30) extending therethrough; assembling the primary component (23) and the secondary component (27) together to form the turbine component (32), wherein the main air passageway (30) of the secondary component (27) forms part of an internal air flow path through the turbine component (32).