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US 11,378,009 B2Granted
Multi-mode heat rejection system for a gas turbine engine
AssigneeRaytheon Technologies Corporation
InventorGary D. Roberge
Life of this patent
Estimating the term…
Abstract
A turbine engine includes a duct defining an annular passage, at least two heat exchangers arranged within the annular passage and spaced circumferentially apart, a passage between the at least two heat exchangers, and a forward flow control device operable for controlling airflow through the passages.
Claims19
A turbine engine comprising:
- a duct defining an annular space;
- at least two heat exchangers arranged within the annular space and spaced circumferentially apart;
- a passage between the at least two heat exchangers;
- a forward flow control device operable for controlling airflow through the passage;
- and
- an aft flow control device disposed on either side of an outlet of the passage between the at least two heat exchangers for defining an outlet of the passage and of the at least two heat exchangers.
3 more elements
A thermal management system for a gas turbine engine comprising:
- a plurality of heat exchangers circumferentially spaced apart within an annular duct;
- a plurality of passages disposed within circumferential spaces between the plurality of heat exchangers;
- and
- a plurality of forward flow control devices for distributing airflow between the plurality of passages and the plurality of heat exchangers wherein each of the plurality of forward flow control devices comprise a fixed fairing and two vanes movable outward from the fixed fairing to a plurality of intermediate positions between an open position allowing airflow through the plurality of passages and a closed position blocking airflow through the plurality of passages to direct and proportionally control airflow through the plurality of heat exchangers and through the plurality of passages.
1 more element
A turbine engine comprising:
- a duct defining an annular space;
- at least two heat exchangers arranged within the annular space and spaced circumferentially apart;
- a passage between the at least two heat exchangers;
- a forward flow control device operable for controlling airflow through the passage wherein the forward flow control device is movable from an open position allowing airflow through the passage and a closed position blocking airflow through the passage to force all airflow through the at least two heat exchangers and wherein the flow control device comprises a fixed fairing and two vanes movable outward from the fixed fairing between the open position and the closed position.
1 more element
A thermal management system for a gas turbine engine comprising:
- a plurality of heat exchangers circumferentially spaced apart within an annular duct;
- a plurality of passages disposed within circumferential spaces between the plurality of heat exchangers;
- a plurality of forward flow control devices for distributing airflow between the plurality of passages and the plurality of heat exchangers;
- and
- a plurality of aft flow control devices disposed at an outlet of each of the plurality of passages, wherein each of the plurality of aft flow control devices are movable to a first position defining a diverging nozzle through a corresponding one of the plurality of passages and a second position defining a diverging nozzle of airflow exiting a corresponding one of the plurality of heat exchangers.
2 more elements
Dependencies are inferred from the claim text.