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US 12,004,334 B2Granted
Thermal management system and method of use
AssigneeHamilton Sundstrand Corporation
InventorsDebabrata Pal, Craig R. LeGros, Tom A. Utecht
Life of this patent
Estimating the term…
Abstract
An thermal management system including, a body having a coolant passage in thermal communication with an electronic device, a first heat exchanger fluidically connected to the coolant passage configured to receive the coolant from the coolant passage, a second heat exchanger fluidically connected to the first heat exchanger, and a generator fluidically connected to the second heat exchanger.
Claims20
An aircraft engine thermal management system comprising:
- a body having a coolant passage in thermal communication with an electronic device and fluidically connected to a first coolant circuit;
- a first heat exchanger fluidically connected to the first coolant circuit and fluidically connected to fuel and air fluid streams, the first heat exchanger being adapted and configured to receive coolant from the first coolant circuit and to transfer heat energy from the first coolant circuit to either the fuel fluid stream during aircraft engine start up or the air fluid stream after aircraft engine start up;
- a generator fluidically connected to a second coolant circuit;
- and
- a second heat exchanger fluidically connected to the second coolant circuit and to the air fluid stream, the second heat exchanger being adapted and configured to receive coolant from the second coolant circuit and to transfer heat energy from the second coolant circuit to the air fluid stream.
2 more elements
A method of managing heat of an electronic device on an aircraft engine comprising:
- pumping a coolant through a passage of a body coupled to an electronic device;
- transferring heat from the electronic Ma device to the coolant within the passage of the body prior to aircraft engine start up;
- transferring heat from the coolant to fuel within a heat exchanger;
- producing bypass air;
- and
- transferring heat from the coolant to air within the heat exchanger after aircraft engine start up.
3 more elements
An aircraft engine thermal management system comprising:
- a body having a coolant passage in thermal communication with an electronic device and fluidically connected to a coolant circuit;
- and
- a heat exchanger fluidically connected to the coolant circuit and fluidically connected to fuel and air fluid streams, the heat exchanger being adapted and configured to receive coolant from the coolant circuit and to transfer heat energy from the coolant circuit to either the fuel fluid stream during aircraft engine start up or the air fluid stream after aircraft engine start up.
Dependencies are inferred from the claim text.