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US 11,958,623 B2Granted
Thermal management system for gas turbine engine
AssigneeRtx Corporation
InventorGary D. Roberge
Life of this patent
Estimating the term…
Abstract
A thermal management system for a gas turbine engine includes an additively manufactured nacelle component, at least a portion of the additively manufactured nacelle component forming an additively manufactured heat exchanger that extends into a fan bypass flow.
Claims21
A thermal management system for a gas turbine engine comprising:
- a core cowl, at least a portion of the core cowl forming an integral heat exchanger, the heat exchanger comprises an external surface of the core cowl with a multiple of fins each being elongate and extending along the external surface of the core cowl and having a fin height extending from the external surface of the core cowl to interact with a fan bypass airflow, wherein the multiple of fins extend along the external surface along a length that is greater than the fin height, wherein at least one of the multiple of fins contains at least one passage.
A core cowl door for a gas turbine engine comprising:
- a heat exchanger that comprises an external surface of the core cowl door, the heat exchanger comprises a multiple of fins that extend outward into a fan bypass airflow;
- a multiple of passages that comprise a tailored cross-sectional geometry, at least one of the multiple of fins contains at least one passage of the multiple of passages;
- and
- a tank within the core cowl door, the tank in fluid communication with at least one of the multiple of passages.
1 more element
A core cowl assembly for a gas turbine engine comprising:
- an articulatable first core cowl door;
- an articulatable second core cowl door;
- a first heat exchanger that comprises an external surface of the first core cowl door, the first heat exchanger comprises a first multiple of fins that extend outward from the first core cowl door into a fan bypass airflow, at least one of the first multiple of fins contains a passage that comprises a tailored cross-sectional geometry;
- a second heat exchanger that comprises an external surface of the second core cowl door, the second heat exchanger comprises a second multiple of fins that extend outward from the second core cowl door into the fan bypass airflow, at least one of the second multiple of fins contains a passage that comprises a tailored cross-sectional geometry;
- and
- a distribution manifold operable to receive heated oil from a gas turbine engine and distribute the oil to the first and second heat exchangers to extract heat therefrom.
3 more elements
Dependencies are inferred from the claim text.