A vane for a gas turbine engine, comprising: a first platform and a second platform joined together by an airfoil, the airfoil defining a flow passage that extends between the first platform and the second platform, at least one of the first platform and the second platform includes a first rail disposed proximate to a first platform end, a second rail disposed proximate to a second platform end, the first rail being opposite the second rail, a first surface and a second surface that is disposed opposite the first surface, the flow passage defining a passage outlet that extends through the second surface; and a cooling arrangement, comprising: a first wall disposed on the second surface, the first wall having a first wall first portion that axially extends from a portion of a pressure side of the airfoil that is spaced from a leading edge of the airfoil towards a trailing edge of the airfoil, a first wall second portion that extends from the first wall first portion and engages the trailing edge and extends towards the second platform end and engages the second rail, a second wall spaced apart from the first wall and disposed on the second surface, the second wall having a second wall first portion, a second wall second portion, and a second wall third portion, the second wall first portion engages the first rail and axially extends toward and engages the leading edge of the airfoil, the second wall second portion extends from the second wall first portion and engages a suction side of the airfoil and extends from the leading edge towards the trailing edge, and the second wall third portion axially extends from the second wall second portion and extends towards and is spaced apart from the second rail, a third wall connected to the second surface to define a flow cavity therebetween, the third wall defining a first outlet; the third wall, the first wall, and the second wall at least partially define a first flow passage that extends between the passage outlet and the first outlet, and wherein a heat transfer enhancement feature is disposed on the second surface. a first platform and a second platform joined together by an airfoil, the airfoil defining a flow passage that extends between the first platform and the second platform, at least one of the first platform and the second platform includes a first rail disposed proximate to a first platform end, a second rail disposed proximate to a second platform end, the first rail being opposite the second rail, a first surface and a second surface that is disposed opposite the first surface, the flow passage defining a passage outlet that extends through the second surface; and a cooling arrangement, comprising: a first wall disposed on the second surface, the first wall having a first wall first portion that axially extends from a portion of a pressure side of the airfoil that is spaced from a leading edge of the airfoil towards a trailing edge of the airfoil, a first wall second portion that extends from the first wall first portion and engages the trailing edge and extends towards the second platform end and engages the second rail, a second wall spaced apart from the first wall and disposed on the second surface, the second wall having a second wall first portion, a second wall second portion, and a second wall third portion, the second wall first portion engages the first rail and axially extends toward and engages the leading edge of the airfoil, the second wall second portion extends from the second wall first portion and engages a suction side of the airfoil and extends from the leading edge towards the trailing edge, and the second wall third portion axially extends from the second wall second portion and extends towards and is spaced apart from the second rail, a third wall connected to the second surface to define a flow cavity therebetween, the third wall defining a first outlet; the third wall, the first wall, and the second wall at least partially define a first flow passage that extends between the passage outlet and the first outlet, and wherein a heat transfer enhancement feature is disposed on the second surface. a first wall disposed on the second surface, the first wall having a first wall first portion that axially extends from a portion of a pressure side of the airfoil that is spaced from a leading edge of the airfoil towards a trailing edge of the airfoil, a first wall second portion that extends from the first wall first portion and engages the trailing edge and extends towards the second platform end and engages the second rail, a second wall spaced apart from the first wall and disposed on the second surface, the second wall having a second wall first portion, a second wall second portion, and a second wall third portion, the second wall first portion engages the first rail and axially extends toward and engages the leading edge of the airfoil, the second wall second portion extends from the second wall first portion and engages a suction side of the airfoil and extends from the leading edge towards the trailing edge, and the second wall third portion axially extends from the second wall second portion and extends towards and is spaced apart from the second rail, a third wall connected to the second surface to define a flow cavity therebetween, the third wall defining a first outlet; the third wall, the first wall, and the second wall at least partially define a first flow passage that extends between the passage outlet and the first outlet, and wherein a heat transfer enhancement feature is disposed on the second surface.