Electrical power system for an aircraft

Patent metadata

Field	Value
Publication number	US-9963095-B2
Application number	US-201414266940-A
Country	US
Kind code	B2
Filing date	May 1, 2014
Priority date	Nov 6, 2013
Publication date	May 8, 2018
Grant date	May 8, 2018

Abstract

An electrical power system for an aircraft having electrical loads and at least one jet engine with a high pressure spool and a low pressure spool, the electrical power system includes a first electrical machine driven by a first pressure spool and outputting a first voltage, a second electrical machine driven by a second pressure spool and outputting a second voltage, and an electrical distribution bus receiving the first and second voltages and supplying the voltages to the loads.

First claim

What is claimed is:

1. An electrical power system for an aircraft having electrical loads, comprising:
a first electrical machine driven by a high pressure spool of a jet engine and outputting a first high direct current (DC) voltage;
a second electrical machine driven by a low pressure spool of the jet engine and outputting a second high DC voltage;
a first distribution bus, receiving the first high DC voltage, supplying at least some of the electrical loads with the first high DC voltage;
a second distribution bus, receiving the second high DC voltage, supplying at least some of the electrical loads with the second high DC voltage, wherein the first and second distribution buses are selectively coupled in parallel; and
a load leveling unit selectively coupled to the second distribution bus, wherein the load leveling unit comprises a battery.

2. The electrical power system of claim 1 wherein the first high DC voltage and the second high DC voltage are the same voltage.

3. The electrical power system of claim 2 wherein the same voltage is +/−270 Vdc.

4. The electrical power system of claim 1 wherein the load leveling unit is selectively coupled to the first distribution bus.

5. The electrical power system of claim 1 further comprising an auxiliary power unit selectively coupled to at least one of the first and second distribution buses.

6. The electrical power system of claim 1 wherein an auxiliary power unit is selectively coupled to both the first and second distribution buses.

7. The electrical power system of claim 1 further comprising an emergency power unit selectively coupled to at least one of the first and second distribution buses.

8. The electrical power system of claim 7 , the emergency primary unit comprises at least one of a fuel cell or a battery.

9. The electrical power system of claim 7 , wherein an auxiliary power unit and the load leveling unit are a single unit.

10. The electrical power system of claim 1 wherein the first and second electrical machines and the first and second distribution buses define an engine power system, which is provided for the jet engine.

11. The electrical power system of claim 1 further comprising a motor starter controller selectively, electrically connectable to the electrical distribution bus and at least one of environmental control system or cabin air compressor.

12. The electrical power system of claim 1 wherein the second electrical machine comprises a generator outputting the second high DC voltage and the first electrical machine comprises a starter/generator outputting the first high DC voltage.

13. The electrical power system of claim 12 wherein at least one of the starter/generator and the generator comprises multi-phase windings electrically coupled to a rectifier.

14. The electrical power system of claim 12 further comprising a speed range reduction unit coupling the low pressure spool to the generator.

15. The electrical power system of claim 1 further comprising:
an auxiliary power unit selectively coupled between the first and second distribution buses;
an emergency power unit selectively coupled to the second distribution bus; and
a motor starter controller selectively, electrically connectable between the first distribution bus and at least one of an environmental control system or a cabin air compressor.

16. The electrical power system of claim 1 , wherein during transients, at least one of the first or second distribution buses at least one of selectively connect or disconnect at east one of additional high DC voltage sources, or parallel primary distribution buses to provide balanced, no break power transfer to the electrical loads.

17. The e ectrical power system of claim 1 , wherein at least one of the first or second distribution buses includes a solid-state-based primary electrical power distribution center.

18. The electrical power system of claim 17 , wherein the solid-state-based primary electrical power distributions center comprises a silicon carbide solid-state-based primary electrical power distribution center.

19. The electrical power system of claim 1 , wherein at least one of the first or second distribution buses selectively connect or disconnect at least one of additional high DC voltage sources in response to expected or actual electrical needs.

Assignees

• Ge Aviat Systems Ltd

Inventors

• Huang Hao
• Shipley Adrian

Classifications

• H02J1/10

  Parallel operation of DC sources · CPC title

• B60R16/03 Primary

  for supply of electrical power to vehicle subsystems {or for (circuit arrangements for charging batteries H02J7/00)} · CPC title

• F01D15/10 Primary

  Adaptations for driving, or combinations with, electric generators · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title