A component for a gas turbine engine is provided. The component having: a platform; an airfoil secured to and extending radially from the platform, the airfoil having an exterior surface extending from a leading edge and a trailing edge; an internal cooling cavity located within the airfoil; and a first row of pedestals extending between opposite sides of the internal cavity and a second row of pedestals adjacent to the first row of pedestals and extending between opposite sides of the internal cavity, wherein the first row of pedestals are further from the trailing edge than the second row of pedestals and a lowermost pedestal of the first row of pedestals is further from the platform than a lowermost pedestal of the second row of pedestals.