An internal cooling system having an insert forming a near-wall cooling passage in a chord central cooling cavity of a gas turbine blade

摘要

Wing (10) for a gas turbine engine is disclosed in which the wing (10) comprises an internal cooling system (14) with one or more internal cavities (16) and the internal cavity ) Has an insert (18) contained within this internal cavity (16), which forms a near-wall cooling channel (20) with an improved flow pattern There. The cooling fluid flow in the near wall cooling passage (20) may be controlled by a plurality of cooling fluid flow control bodies (22) extending from the outer wall (24) forming an elongated hollow blade (26) as a whole. The cooling fluid flow control 22 may be grouped together to form a row 28 extending in the spanwise direction and the internal cooling system 14 may be arranged from the insert 18 towards the outer wall 24 May comprise one or more bypass flow reducing bodies (30) that extend, this bypass flow reducing body (30) passes through a passage (20) formed by the cooling fluid flow control body (22) It directs the cooling fluid, which improves the effectiveness of the internal cooling system (14).