A gas turbine engine airfoil comprising: a platform , and spaced apart walls providing an exterior airfoil surface extending radially from the platform to an end opposite the platform , multiple cooling passages extending radially within the airfoil and spaced apart from one another in a chord-wise direction and including a two pass serpentine cooling passage arranged between the walls and having a first passageway extending from the platform toward the end and a second passageway fluidly connecting to the first passageway and extending from the end toward the platform to an end, and a platform cooling passageway fluidly connected to the second passage at an end and extending transversely into the platform , a cooling hole fluidly connecting the platform cooling passageway to an exterior surface ; wherein the first and second passageways provide an up-pass passageway and a down-pass passageway that form a two-pass U-shaped cooling passage; and the serpentine cooling passage terminates at the end of the U-shaped cooling passage; wherein the platform cooling passageway extends along a pressure side of the platform , along a suction side of the platform or along a pressure side and a suction side of the platform ; characterized in that : the multiple passages further include a leading edge passage arranged near a leading edge of the exterior airfoil surface and a trailing edge passage arranged near a trailing edge of the exterior airfoil surface; and each of the multiple passages includes discrete inlets that provide cooling flow to the passage. a platform , and spaced apart walls providing an exterior airfoil surface extending radially from the platform to an end opposite the platform , multiple cooling passages extending radially within the airfoil and spaced apart from one another in a chord-wise direction and including a two pass serpentine cooling passage arranged between the walls and having a first passageway extending from the platform toward the end and a second passageway fluidly connecting to the first passageway and extending from the end toward the platform to an end, and a platform cooling passageway fluidly connected to the second passage at an end and extending transversely into the platform , a cooling hole fluidly connecting the platform cooling passageway to an exterior surface ; wherein the first and second passageways provide an up-pass passageway and a down-pass passageway that form a two-pass U-shaped cooling passage; and the serpentine cooling passage terminates at the end of the U-shaped cooling passage; wherein the platform cooling passageway extends along a pressure side of the platform , along a suction side of the platform or along a pressure side and a suction side of the platform ; characterized in that : the multiple passages further include a leading edge passage arranged near a leading edge of the exterior airfoil surface and a trailing edge passage arranged near a trailing edge of the exterior airfoil surface; and each of the multiple passages includes discrete inlets that provide cooling flow to the passage. the multiple passages further include a leading edge passage arranged near a leading edge of the exterior airfoil surface and a trailing edge passage arranged near a trailing edge of the exterior airfoil surface; and each of the multiple passages includes discrete inlets that provide cooling flow to the passage. <EOS>