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US 2019/0100319 A1Published application
Combined fluid ice protection and electronic cooling system
AssigneeThe Boeing Company
InventorSteve G. Mackin
Life of this patent
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Abstract
A method and apparatus combining an aircraft wing and engine ice protection system with an aircraft electronic cooling system
Claims20
An ice protection system 200 for an aerodynamic surface 206 of an aircraft 202, the ice protection system 200 comprising:
- a reservoir 208;
- an electronics cooling system 210 connected to the reservoir 208 and comprising a first conduit 212, wherein:
- the electronics cooling system 210 distributes coolant 218 from the reservoir 208 through the first conduit 212 in thermal contact 220 with electronics 222, and
- heat 224 is transferred from the electronics 222 to the coolant 218;
- a pump 214 operatively coupled 216 to the reservoir 208;
- and
- a second conduit 232 in communication with the pump 214 and including an outlet 232a disposed at the aerodynamic surface 206 located on an outside of the aircraft 202, wherein the pump 214 pumps the coolant 218 onto the aerodynamic surface 206 and the coolant 218 reduces or prevents ice formation 204 on the aerodynamic surface 206.
4 more elements
A method of manufacturing, refitting, or servicing an aircraft 202, comprising:
- mounting an electronics cooling apparatus 210 distributing coolant 218 for cooling electronics 222 on an aircraft 202;
- and
- mounting an ice protection apparatus 242 on the aircraft 202 and connecting the ice-protection apparatus to the electronics cooling apparatus 210, wherein the ice protection apparatus 242 receives the coolant 218 from the electronics cooling apparatus 210 and distributes the coolant 218 onto an aerodynamic surface 206 outside of the aircraft 202, the coolant reducing and removing ice formation 204 on an aerodynamic surface 206 of the aircraft 202.
A method of operating an aircraft 202, comprising:
- providing an aircraft 202 comprising an ice protection system 200, the ice protection system 200 comprising:
- a reservoir 208;
- an electronics cooling system 210 connected to the reservoir 208 and comprising a first conduit 212, wherein:
- the electronics cooling system 210 distributes coolant 218 from the reservoir 208 through the first conduit 212 in thermal contact 220 with electronics 222, and
- heat 224 is transferred from the electronics 222 to the coolant 218;
- a pump 214 operatively coupled 216 to the reservoir 208;
- and
- a second conduit 232 in communication with the pump 214 and including an outlet 232a disposed at an aerodynamic surface 206 located on an outside of the aircraft 202, wherein the pump 214 pumps the coolant 218 onto the aerodynamic surface 206 and the coolant 218 reduces or prevents ice formation 204 on the aerodynamic surface 206;
- providing instructions allowing higher thrust for the aircraft 202 in icing conditions, as compared to an otherwise identical aircraft 202 without the ice protection system 200;
- and
- providing instructions allowing operation of the ice protection system 200 while the aircraft 202 is parked.
8 more elements
Dependencies are inferred from the claim text.