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US 10,371,052 B2Granted
Integrated thermal management with nacelle laminar flow control for geared architecture gas turbine engine
AssigneeUnited Technologies Corporation
InventorJinQuan Xu
Life of this patent
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Abstract
A thermal management system for a gas turbine engine includes a heat exchanger in fluid communication with a geared architecture and a heating compartment.
Claims17
A thermal management system for a gas turbine engine comprising:
- a geared architecture to drive a fan at a lower speed than a low spool;
- a heating compartment located within an inlet of a fan nacelle, the fan nacelle surrounds the fan;
- and
- a heat exchanger in fluid communication with said geared architecture and said heating compartment.
1 more element
A gas turbine engine comprising:
- a geared architecture to drive a fan at a lower speed than a low spool, wherein said fan and said low spool are defined along an engine axis;
- a heating compartment within an inlet of a nacelle, said fan located within said nacelle;
- and
- a heat exchanger in fluid communication with said heating compartment, the heat exchanger located within the nacelle generating a thermal gradient that encourages a sustained stabilization of a boundary-layer adjacent to the nacelle;
- a fluid plenum that at least partially surrounds the geared architecture, said heat exchanger in fluid communication with said geared architecture.
2 more elements
A method of thermal management for a gas turbine engine, comprising:
- vaporizing a heat exchange fluid to form a vaporized heat exchange fluid with heat from a geared architecture that drives a fan at a lower speed than a low spool, wherein said fan and said low spool are defined along an engine axis;
- and
- communicating the vaporized heat exchange fluid to a heating compartment located within an inlet of a nacelle.
Dependencies are inferred from the claim text.