US Patent 11187086 Gas turbine engine component cooling with resupply of cooling passage

A gas turbine engine component with a core includes a first core portion configured to provide a first cooling passage. A second core portion is spaced from the first core portion and configured to provide a second cooling passage. The second core portion includes a longitudinal leg and a resupply leg transverse to and intersecting the longitudinal leg. The resupply leg has a terminal end and is configured to provide a resupply channel. A connector interconnects the terminal end to the first core portion. The connector is configured to provide a resupply hole.