Patent attributes
Components for gas turbine engines are provided. The components include a hybrid skin core cooling cavity defined by a cold wall and a hot wall, wherein the hot wall is exposed to an exterior environment of the component and a resupply hole is formed in the cold wall and fluidly connects a cold core cavity and the cooling cavity. The resupply hole extends between an inlet on a side of the cold wall exposed to the cold core cavity and an outlet on a side of the cold wall exposed to the cooling cavity. The cavity resupply hole is angled relative to the cold wall at an injection angle such that air passing through the cavity resupply hole is injected into the cooling cavity at the injection angle and at least partially parallel to a direction of flow within the hybrid skin core cooling cavity.
