An airfoil (100; 200; 300; 400; 500; 600) for use in a gas turbine engine, the airfoil (100; 200; 300; 400; 500; 600) comprising: an airfoil body having a leading edge (124; 604), a trailing edge (122; 602), an inner diameter end wall and an outer diameter end wall; a first cooling structure (120; 220; 420; 520; 620) disposed within the airfoil body, the first cooling structure (120; 220; 420; 520; 620) comprising a first rib extending between the inner diameter end wall and the outer diameter end wall and defining a first radial passage (172; 304; 402) configured to conduct a cooling airflow in a radial direction through the airfoil body; and a second cooling structure (150; 250; 450; 550) disposed within the airfoil body, the second cooling structure (150; 250; 450; 550) comprising: a first baffle defining a second radial passage (182; 582) within the first baffle, characterised in that the second cooling structure (150; 250; 450; 550) further comprises: first axial standoffs extending inward from an inner surface of the airfoil body toward the first baffle and contacting a first wall of the first baffle to define first axial passages between the first wall of the first baffle and a pressure side wall of the airfoil body; and second axial standoffs extending inward from an inner surface of the airfoil body toward the first baffle and contacting a second wall of the first baffle to define second axial passages between the second wall of the first baffle and the suction side wall of the airfoil body, wherein the first and second axial passages (184a, 184b) are configured to conduct the cooling airflow in an axial direction towards the trailing edge (122; 602) of the airfoil body. an airfoil body having a leading edge (124; 604), a trailing edge (122; 602), an inner diameter end wall and an outer diameter end wall; a first cooling structure (120; 220; 420; 520; 620) disposed within the airfoil body, the first cooling structure (120; 220; 420; 520; 620) comprising a first rib extending between the inner diameter end wall and the outer diameter end wall and defining a first radial passage (172; 304; 402) configured to conduct a cooling airflow in a radial direction through the airfoil body; and a second cooling structure (150; 250; 450; 550) disposed within the airfoil body, the second cooling structure (150; 250; 450; 550) comprising: a first baffle defining a second radial passage (182; 582) within the first baffle, characterised in that the second cooling structure (150; 250; 450; 550) further comprises: first axial standoffs extending inward from an inner surface of the airfoil body toward the first baffle and contacting a first wall of the first baffle to define first axial passages between the first wall of the first baffle and a pressure side wall of the airfoil body; and second axial standoffs extending inward from an inner surface of the airfoil body toward the first baffle and contacting a second wall of the first baffle to define second axial passages between the second wall of the first baffle and the suction side wall of the airfoil body, wherein the first and second axial passages (184a, 184b) are configured to conduct the cooling airflow in an axial direction towards the trailing edge (122; 602) of the airfoil body. first axial standoffs extending inward from an inner surface of the airfoil body toward the first baffle and contacting a first wall of the first baffle to define first axial passages between the first wall of the first baffle and a pressure side wall of the airfoil body; and second axial standoffs extending inward from an inner surface of the airfoil body toward the first baffle and contacting a second wall of the first baffle to define second axial passages between the second wall of the first baffle and the suction side wall of the airfoil body, wherein the first and second axial passages (184a, 184b) are configured to conduct the cooling airflow in an axial direction towards the trailing edge (122; 602) of the airfoil body.