US Patent 9976485 Gas turbine engine buffer cooling system

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a heat exchanger configured to exchange heat with a bleed airflow to provide a conditioned airflow. A bearing compartment is in fluid communication with the heat exchanger, and a first passageway communicates the conditioned airflow to the bearing compartment. The conditioned airflow is communicated radially between a bearing housing of the bearing compartment and a diffuser case and a nozzle assembly in fluid communication with the bearing compartment. A second passageway communicates the conditioned airflow from the bearing compartment and then through a plurality of openings of the nozzle assembly.