# US 12,004,334 B2 · Thermal management system and method of use > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,004,334 B2 - Document ID: US12004334B2 - Status: Granted - Kind: B2 - Application number: 17/313,746 - Filed: 2021-05-06 - Published: 2021-11-11 - Granted: 2024-06-04 - Earliest claimed: 2020-05-06 - Assignees: Hamilton Sundstrand Corporation - Applicants: Hamilton Sundstrand Corporation - Inventors: Debabrata Pal; Craig R. LeGros; Tom A. Utecht - Web page: https://patentgrep.com/patent/US12004334B2 ## CPC - F02C 7/185: {Cooling means for reducing the temperature of the cooling air or gas} - H05K 7/20945: {Thermal management, e.g. inverter temperature control} - F01D 25/12: Cooling - F02C 7/12: Cooling of plants (of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P) - H02M 7/003: {Constructional details, e.g. physical layout, assembly, wiring or busbar connections} - H05K 7/20254: {Cold plates transferring heat from heat source to coolant} - H05K 7/20909: {Forced ventilation, e.g. on heat dissipaters coupled to components} - H05K 7/20927: {Liquid coolant without phase change} - F05D 2260/213: by the provision of a heat exchanger within the cooling circuit - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - H05K: PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - H02M: APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF (transformers H01F; dynamo-electric converters H02K47/00; controlling transformers, reactors or choke coils, control or regulation of electric motors, generators or dynamo-electric converters H02P) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## 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. ## Claims ### Claim 1 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. ### Claim 2 (depends on 1) The system of claim 1, wherein the electronic device includes a bi-directional rectifier. ### Claim 3 (depends on 1) The system of claim 1, wherein the first heat exchanger is an air-coolant heat exchanger and a fuel-coolant heat exchanger. ### Claim 4 (depends on 1) The system of claim 1, wherein the second heat exchanger is an air-coolant heat exchanger. ### Claim 5 (depends on 1) The system of claim 1, wherein a first pump is located downstream of the coolant passage configured to drive oil out of the coolant passage. ### Claim 6 (depends on 5) The system of claim 5, wherein a second pump is located downstream of the generator configured to drive oil from the generator. ### Claim 7 (depends on 1) The system of claim 1, wherein the coolant is an oil coolant. ### Claim 8 (depends on 1) The system of claim 1, wherein the first heat exchanger is located within a nacelle of an aircraft engine. ### Claim 9 (depends on 1) The system of claim 1, wherein the first heat exchanger is coupled to a nacelle of an aircraft engine. ### Claim 10 (depends on 1) The system of claim 1, wherein cooling of the coolant in the first heat exchanger by the fuel fluid stream is controlled by a valve on a fuel line fluidically connected to the first heat exchanger. ### Claim 11 (depends on 1) The system of claim 1, wherein cooling of the coolant in the first heat exchanger by the air fluid stream is controlled by a valve in a flow path of ram air fluidically connected to the first heat exchanger. ### Claim 12 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. ### Claim 13 (depends on 12) The method of claim 12, wherein the bypass air is fan bypass air. ### Claim 14 (depends on 13) The method of claim 13, wherein there is no bypass flow during aircraft engine startup. ### Claim 15 (depends on 12) The method of claim 12, wherein the step of transferring heat from the coolant to the fuel includes the step of opening a valve on a fuel line fluidically connected to the heat exchanger. ### Claim 16 (depends on 12) The method of claim 12, wherein the step of transferring heat from the coolant to air includes the step of opening a valve in a flow path of ram air fluidically connected to the heat exchanger. ### Claim 17 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. ### Claim 18 (depends on 17) The system of claim 17, wherein cooling of the coolant in the heat exchanger by the fuel fluid stream is controlled by a valve on a fuel line fluidically connected to the heat exchanger. ### Claim 19 (depends on 17) The system of claim 17, wherein cooling of the coolant in the heat exchanger by the air fluid stream is controlled by a valve in a flow path of ram air fluidically connected to the heat exchanger. ### Claim 20 (depends on 19) The system of claim 19, wherein the valve is an operable nacelle scoop.