A turbine blade having an airfoil comprising: an outer wall delimiting an airfoil interior, the outer wall extending span-wise along a radial direction of a turbine engine and being formed of a pressure sidewall and a suction sidewall joined at a leading edge and at a trailing edge, a trailing edge coolant cavity located in the airfoil interior between the pressure sidewall and the suction sidewall, the trailing edge coolant cavity being positioned adjacent to the trailing edge and in fluid communication with a plurality of coolant exit slots positioned along the trailing edge, wherein a plurality of cooling features are located in the trailing edge coolant cavity and are disposed in a flow path of the coolant flowing toward the coolant exit slots, the cooling features being located between the radially outer span-wise end of the trailing edge coolant cavity and the radially inner span-wise end of the trailing edge coolant cavity, wherein each cooling feature has a length in the radial direction which is greater than a width in the chord-wise direction, wherein the cooling features comprise an array of pins, each pin extending from the pressure sidewall to the suction sidewall, the array comprising multiple chord-wise spaced apart radial rows of said pins with the pins in each row being interspaced radially to define coolant passages therebetween, wherein at least one framing passage (70, 80) is formed at a span-wise end of the trailing edge coolant cavity, wherein the at least one framing passage (70, 80) comprises a first framing passage and a second framing passage formed at span-wise opposite ends of the trailing edge coolant cavity, and framing features (72A-B, 82A-B) located in both the first and second framing passages (70, 80), the framing features configured as ribs (72A-B, 82A-B) arranged chord-wise spaced apparat on the pressure sidewall and/or the suction sidewall and protruding from the pressure sidewall and/or the suction sidewall, the ribs (72A-B, 82A-B) extending partially between the pressure sidewall and the suction sidewall, wherein each rib (72A-B, 82A-B) is aligned with a respective row of said pins in the radial direction. an outer wall delimiting an airfoil interior, the outer wall extending span-wise along a radial direction of a turbine engine and being formed of a pressure sidewall and a suction sidewall joined at a leading edge and at a trailing edge, a trailing edge coolant cavity located in the airfoil interior between the pressure sidewall and the suction sidewall, the trailing edge coolant cavity being positioned adjacent to the trailing edge and in fluid communication with a plurality of coolant exit slots positioned along the trailing edge, wherein a plurality of cooling features are located in the trailing edge coolant cavity and are disposed in a flow path of the coolant flowing toward the coolant exit slots, the cooling features being located between the radially outer span-wise end of the trailing edge coolant cavity and the radially inner span-wise end of the trailing edge coolant cavity, wherein each cooling feature has a length in the radial direction which is greater than a width in the chord-wise direction, wherein the cooling features comprise an array of pins, each pin extending from the pressure sidewall to the suction sidewall, the array comprising multiple chord-wise spaced apart radial rows of said pins with the pins in each row being interspaced radially to define coolant passages therebetween, wherein at least one framing passage (70, 80) is formed at a span-wise end of the trailing edge coolant cavity, wherein the at least one framing passage (70, 80) comprises a first framing passage and a second framing passage formed at span-wise opposite ends of the trailing edge coolant cavity, and framing features (72A-B, 82A-B) located in both the first and second framing passages (70, 80), the framing features configured as ribs (72A-B, 82A-B) arranged chord-wise spaced apparat on the pressure sidewall and/or the suction sidewall and protruding from the pressure sidewall and/or the suction sidewall, the ribs (72A-B, 82A-B) extending partially between the pressure sidewall and the suction sidewall, wherein each rib (72A-B, 82A-B) is aligned with a respective row of said pins in the radial direction.