ELECTRIC ARCHITECTURE WITH POWER STORAGE CELLS

• US 20160096632A1
• Filed: 10/01/2014
• Published: 04/07/2016
• Est. Priority Date: 10/01/2014
• Status: Active Grant

• Current Assignee: Hamilton Sundstrand Corporation (Rtx Corporation)
• Original Assignee: Goodrich Corporation (Rtx Corporation)
• Inventors: Veilleux, Leo J. Jr., Ribarov, Lubomir A.
• Granted Patent: US 9,982,606 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64D 2221/00 Electric power distribution systems onboard aircraft
• CPC Class Codes: B64D 41/00 Power installations for auxiliary purposes
• CPC Class Codes: F01D 15/10 Adaptations for driving, or combinations with, electric generators
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F05D 2220/76 an electrical generator
• CPC Class Codes: F05D 2260/42 Storage of energy
• CPC Class Codes: F05D 2260/96 Preventing, counteracting or reducing vibration or noise
• CPC Class Codes: H02J 2310/44 for aircrafts
• CPC Class Codes: H02J 4/00 Circuit arrangements for mains or distribution networks not specified as ac or dc
• CPC Class Codes: H02J 7/345 using capacitors as storage or buffering devices

Abstract

An architecture for providing power to an aircraft comprises a power supply. The power supply provides power to a plurality of components. An array has a plurality of storage cells. The plurality of storage cells includes capacitors which are charged by the power supply, and which selectively provide power to the components. The array is mounted on a fan case. An engine is also disclosed.

Claims

1. An architecture for providing power to an aircraft comprising:

a power supply, said power supply for providing power to a plurality of components;

an array including a plurality of storage cells, said plurality of storage cells including capacitors which are charged by said power supply, and which selectively provide power to said components; and

said array is mounted on a fan case of a gas turbine engine.

2. The architecture as set forth above in claim 1, wherein said power supply is provided by a generator and a bus for powering systems on the aircraft.

3. The architecture as set forth above in claim 1, wherein at least one of said storage cells provides power across a switch between said power supply and said at least one component, and said storage cell reducing arcs upon closure of said switch.

4. The architecture as set forth above in claim 1, wherein said storage cells are provided with a rectifier.

5. The architecture as set forth above in claim 1, wherein said storage cells provide power to a component at a peak power transient.

6. The architecture as set forth above in claim 1, wherein said plurality of storage cells are circumferentially spaced about said fan case.

7. The architecture as set forth above in claim 1, wherein said plurality of storage cells are axially spaced along a drive axis of said fan.

8. The architecture as set forth above in claim 1, wherein said plurality of storage cells include at least a plurality of radially spaced storage cells.

9. An engine comprising:

a fan including a fan case;

a power supply, said power supply for providing power to a plurality of components; and

a storage cell array mounted on said fan case and including a plurality of storage cells, said plurality of storage cells including capacitors which are charged by said power supply, and which selectively provide power to said components.

10. The engine as set forth above in claim 9, wherein said power supply is provided by at least one of a generator and a bus for powering systems on an associated aircraft.

11. The engine as set forth above in claim 9, wherein at least one of said storage cells provides power across a switch between said power supply and said at least one component, and said storage cell reducing arcs upon closure of said switch.

12. The engine as set forth above in claim 9, wherein, wherein said storage cells are provided with a rectifier.

13. The engine as set forth above in claim 9, wherein said plurality of storage cells are circumferentially spaced about said fan case.

14. The engine as set forth above in claim 9, wherein said plurality of storage cells are axially spaced along a drive axis of said fan.

15. The engine as set forth above in claim 9, wherein said plurality of storage cells include at least a plurality of radially spaced storage cells.