A gas turbine engine includes a core engine that has a compressor section, a combustor section and a turbine section. A thermal management system is configured to receive a cooling stream. The thermal management system includes a metering device that is located near an outer diameter of the core engine. The metering device is configured to divide the cooling stream into multiple segregated passages. The metering device can be configured to divide the cooling stream between a first passage and a second passage that is concentric with the first passage.