United Technologies Corporation

Justin J Phillips

Gabriel L Suciu

William K Ackermann

James D Hill

Anthony R Bifulco

Julian Partyka

Chris J Niggemeier

Gabriel L Sucui

A cooling system for providing a buffer cooled cooling air to a turbine section of a gas turbine engine is disclosed. The cooling system may comprise a first conduit configured to transmit a cooling air toward the turbine section, a heat exchanger configured to cool a bleed airflow diverted from the first conduit to provide a buffer air, and a bypass conduit configured to direct at least a portion of the buffer air through at least one passageway that bypasses a bearing compartment of the gas turbine engine. The cooling system may further comprise a manifold configured to allow the cooling air exiting the first conduit and the buffer air exiting the bypass conduit to mix and provide the buffer cooled cooling air, and a nozzle assembly configured to deliver the buffer cooled cooling air to the turbine section.

Cooling system with a bearing compartment bypass

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West Suffield, CT, United States of America

Justin J Phillips