A gas turbine engine airfoil comprising: a platform, and spaced apart walls (86,88) 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 (86,88) 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 (94,96) 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 (86,88) 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 (86,88) 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 (94,96) 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.