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US 10,364,750 B2Granted
Thermal management system
AssigneeGeneral Electric Company
InventorJeffrey Douglas Rambo
Life of this patent
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AssigneeGeneral Electric Company
InventorJeffrey Douglas Rambo
Estimating the term…
A gas turbine engine includes an outer nacelle; a fan at least partially surrounded by the outer nacelle; and a turbomachine drivingly coupled to the fan and at least partially surrounded by the outer nacelle. The outer nacelle defines a bypass airflow passage with the turbomachine. The turbomachine includes a compressor section defining in part a core air flowpath. The turbomachine also includes a heat sink heat exchanger; and a thermal management duct assembly defining a thermal management duct flowpath extending between an inlet and an outlet and positioned between the core air flowpath and the bypass airflow passage along the radial direction, the outlet selectively in airflow communication with a core compartment of the turbomachine, and the heat sink heat exchanger positioned in thermal communication with the thermal management duct flowpath for transferring heat to an airflow through the thermal management duct flowpath during operation.
A gas turbine engine defining a radial direction and comprising:
A method for operating a gas turbine engine having a fan, a turbomachine, and an outer nacelle defining a bypass airflow passage with the turbomachine, the turbomachine defining a core compartment and comprising a heat sink heat exchanger and a thermal management duct assembly, the thermal management duct assembly defining a thermal management duct flowpath, the heat sink heat exchanger in thermal communication with the thermal management duct flowpath, the method comprising:
Dependencies are inferred from the claim text.