An airfoil (400; 500b; 600; 700; 800; 900; 1000; 1100; 1200; 1300) of a gas turbine engine comprising: an airfoil body having a leading edge and a trailing edge (414; 614; 714; 814; 914; 1114; 1214; 1314) and extending in a radial direction; a cooling cavity (418; 618; 718) defined within the airfoil body at the trailing edge, wherein the cooling cavity extends in the radial direction within the airfoil body; and a plurality of angled pedestals (426; 526b; 626; 726; 826; 926; 1026) arranged along the trailing edge defining a plurality of angled trailing edge slots (431; 831) therebetween, wherein adjacent angled pedestals of the plurality of angled pedestals define a meter section (434; 834) of a respective angled trailing edge slot and a diffuser section (438; 838) of the respective angled trailing edge slot, wherein the meter section is defined by parallel sides of the adjacent angled pedestals, characterized in that : the parallel sides of the adjacent angled pedestals are oriented at a bleed direction (D b ) that is less than 90° with respect to a feed direction (D f ) through the cooling cavity, wherein the feed direction (D f ) is in the radial direction and in that the airfoil further comprises a dividing rib (1158; 1258; 1358) separating the cooling cavity into a first cooling cavity (1118a; 1218a; 1318a) and a second cooling cavity (1118b; 1218b; 1318b), wherein the dividing rib extends in an axial direction from a radially extending rib (1120; 1220; 1320) of the airfoil through the cooling cavity toward the trailing edge, wherein a first set (1126a; 1226a; 1326a) of angled pedestals of the plurality of pedestals is located within the first cooling cavity and a second set of angled pedestals (1126b;1226b;1326b) is located within the second cooling cavity, a rib flow control feature being located at a trailing edge end of the dividing rib to maintain the meter section of the last trailing edge slot in the first and second cooling cavity (1118a; 1218a; 1318a; 1118b; 1218b; 1318b). an airfoil body having a leading edge and a trailing edge (414; 614; 714; 814; 914; 1114; 1214; 1314) and extending in a radial direction; a cooling cavity (418; 618; 718) defined within the airfoil body at the trailing edge, wherein the cooling cavity extends in the radial direction within the airfoil body; and a plurality of angled pedestals (426; 526b; 626; 726; 826; 926; 1026) arranged along the trailing edge defining a plurality of angled trailing edge slots (431; 831) therebetween, wherein adjacent angled pedestals of the plurality of angled pedestals define a meter section (434; 834) of a respective angled trailing edge slot and a diffuser section (438; 838) of the respective angled trailing edge slot, wherein the meter section is defined by parallel sides of the adjacent angled pedestals, characterized in that : the parallel sides of the adjacent angled pedestals are oriented at a bleed direction (D b ) that is less than 90° with respect to a feed direction (D f ) through the cooling cavity, wherein the feed direction (D f ) is in the radial direction and in that the airfoil further comprises a dividing rib (1158; 1258; 1358) separating the cooling cavity into a first cooling cavity (1118a; 1218a; 1318a) and a second cooling cavity (1118b; 1218b; 1318b), wherein the dividing rib extends in an axial direction from a radially extending rib (1120; 1220; 1320) of the airfoil through the cooling cavity toward the trailing edge, wherein a first set (1126a; 1226a; 1326a) of angled pedestals of the plurality of pedestals is located within the first cooling cavity and a second set of angled pedestals (1126b;1226b;1326b) is located within the second cooling cavity, a rib flow control feature being located at a trailing edge end of the dividing rib to maintain the meter section of the last trailing edge slot in the first and second cooling cavity (1118a; 1218a; 1318a; 1118b; 1218b; 1318b). <EOS>