A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a wall that extends about a cooling cavity. The cooling cavity is a dual-fed cavity that is fed from at least two different locations. A rib separates the cooling cavity into a first portion and a second portion that is fluidly isolated from the first portion. The component is an airfoil. The first portion is fed with a first cooling fluid from a first coolant source, and the second portion is fed with a second, different cooling fluid from a second coolant source. The first and second coolant sources are separate and distinct from the component.