Independent power generation in aircraft

• US 8,657,227 B1
• Filed: 09/11/2009
• Issued: 02/25/2014
• Est. Priority Date: 09/11/2009
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Paterson, John T., Retz, Kevin, Bayliss, Andrew J.
• Primary Examiner(s): Ellis, Christopher P
• Assistant Examiner(s): Badawi, Medhat
• Application Number:
  US12/558,177
• Time in Patent Office: 1,628 Days
• Field of Search: 244/58, 244/134.D, 244/175, 244/236, 244/227, 244/228, 290/7, 310/10, 417/313
• US Class Current: 244/58
• CPC Class Codes: B64D 13/00 Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space , or structural parts of the aircraft treatment rooms with artificial climate for medical purposes A61G10/02; respiratory apparatus in general A62B; for vehicles in general B60H
• CPC Class Codes: B64D 13/06 the air being conditioned pressurising B64D13/02
• CPC Class Codes: B64D 2013/0603 Environmental Control Systems
• CPC Class Codes: B64D 2013/0644 including electric motors or generators
• CPC Class Codes: B64D 2041/002 Mounting arrangements for auxiliary power units (APU's)
• CPC Class Codes: B64D 2041/005 Fuel cells
• CPC Class Codes: B64D 2221/00 Electric power distribution systems onboard aircraft
• CPC Class Codes: B64D 37/04 Arrangement thereof in or on aircraft
• CPC Class Codes: B64D 37/20 Emptying systems
• CPC Class Codes: B64D 41/00 Power installations for auxiliary purposes
• CPC Class Codes: B64D 41/007 Ram air turbines
• CPC Class Codes: H02J 2300/30 The power source being a fuel cell
• 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: Y02T 50/40 Weight reduction
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency
• CPC Class Codes: Y02T 90/40 Application of hydrogen technology to transportation, e.g. using fuel cells

Abstract

Systems and methods of independent power generation are disclosed. A particular system includes an aircraft having at least one engine and a plurality of independent power units. Each power unit of the plurality of independent power units generates electricity independently of the at least one engine. The plurality of independent power units include at least a first independent power unit that generates first electricity having a first set of electrical characteristics and a second independent power unit that generates second electricity having a second set of electrical characteristics concurrently with the first power unit generating the first electricity. The first set of electrical characteristics is different than the second set of electrical characteristics.

Claims

1. An aircraft, comprising:

at least one engine;

a plurality of independent power units; and

a fuselage,

wherein each power unit of the plurality of independent power units generates electricity independently of the at least one engine during flight, the plurality of independent power units including at least a first independent power unit that generates first electricity having a first set of electrical characteristics and a second independent power unit that generates second electricity having a second set of electrical characteristics concurrently with the first power unit generating the first electricity,

wherein the first set of electrical characteristics is different than the second set of electrical characteristics,

wherein the second independent power unit provides power to an environmental control system (ECS) configured to provide conditioned air to the fuselage, and

wherein, during flight, the ECS is electrically and pneumatically isolated from the at least one engine.

2. The aircraft of claim 1, wherein the first electricity includes direct current and the second electricity includes alternating current.

3. The aircraft of claim 1, wherein the first set of electrical characteristics includes a first frequency range and the second set of electrical characteristics includes a second frequency range, wherein the first frequency range and the second frequency range are different.

4. The aircraft of claim 3, wherein the first frequency range and the second frequency range are each independent of an operating speed of the at least one engine.

5. The aircraft of claim 1, wherein the first set of electrical characteristics includes a first voltage range and the second set of electrical characteristics includes a second voltage range, wherein the first voltage range and the second voltage range are different.

6. The aircraft of claim 1, wherein the first independent power unit includes a first generator.

7. The aircraft of claim 6, wherein the second independent power unit includes a second generator.

8. The aircraft of claim 1, wherein the second independent power unit includes a fuel cell.

9. The aircraft of claim 1, wherein the second independent power unit includes a gas turbine.

10. The aircraft of claim 1, further comprising:

a main fuel storage and supply system to provide fuel to the at least one engine;

a first fuel storage and supply unit to provide fuel to the first independent power unit; and

a second fuel storage and supply unit to provide fuel to the second independent power unit,

wherein the first fuel storage and supply unit and the second fuel storage and supply unit are independent of the main fuel storage and supply system.

11. The aircraft of claim 10, further comprising a line replaceable unit (LRU) comprising the first fuel storage and supply unit and the first independent power unit.

12. The aircraft of claim 1, further comprising a third independent power unit that generates third electricity having a third set of electrical characteristics concurrently with the first power unit generating the first electricity and concurrently with the second power unit generating the second electricity, wherein the third set of electrical characteristics is different than the first set of electrical characteristics and is different than second set of electrical characteristics.

13. The aircraft of claim 12, further comprising a power conversion system, the power conversion system operable to modify the third electricity to have the first set of electrical characteristics or the second set of electrical characteristics.

14. The aircraft of claim 1, further comprising:

at least one first powered system having a first set of power requirements, wherein the first set of electrical characteristics substantially matches the first set of power requirements; and

at least one second powered system having a second set of power requirements, wherein the second set of electrical characteristics substantially matches the second set of power requirements.

15. The aircraft of claim 14, wherein the first independent power unit and the at least one first powered system are coupled to the fuselage at a first location, wherein the second independent power unit and the at least one second powered system are coupled to the fuselage at a second location, wherein the second location is remote from the first location, wherein a plurality of wings is coupled to the fuselage, and wherein the at least one engine is coupled to at least one of the fuselage and one or more of the plurality of wings.

16. The aircraft of claim 1, wherein, during flight, no power generated by the at least one engine is routed for use at the fuselage of the aircraft.

17. An aircraft, comprising:

a body, comprising;

a first independent power unit that provides power to a first set of powered devices; and

a second independent power unit that provides power to a second set of powered devices concurrently with the first independent power unit providing power to the first set of powered devices, wherein the first set of powered devices is different than the second set of powered devices, and wherein the second set of power devices includes an environmental control system (ECS) configured to provide conditioned air to a fuselage of the aircraft; and

at least one engine coupled to the body, wherein, during flight, neither the first independent power unit nor the second independent power unit receives operational power from the at least one engine, and wherein, during flight, the ECS is electrically and pneumatically isolated from the at least one engine.

18. The aircraft of claim 17, wherein the at least one engine is housed in at least one engine nacelle, wherein power derived from the at least one engine is not routed to operate systems of the aircraft located outside the engine nacelle, and wherein the power derived from the at least one engine includes electric power, mechanical power, pneumatic power, or a combination thereof.

19. The aircraft of claim 17, wherein the first independent power unit is located nearer to the first set of powered devices than to the second set of powered devices and wherein the second independent power unit is located nearer to the second set of powered devices than to the first set of powered devices.

20. The aircraft of claim 17, wherein the first independent power unit provides backup power to the second set of powered devices.