Hybrid power system for an aircraft

Patent metadata

Field	Value
Publication number	US-10227137-B2
Application number	US-201615077178-A
Country	US
Kind code	B2
Filing date	Mar 22, 2016
Priority date	Mar 22, 2016
Publication date	Mar 12, 2019
Grant date	Mar 12, 2019

Abstract

Systems and methods for distributing in an aircraft are provided. More particularly, in one embodiment, a system can include one or more gas turbine engines configured to provide propulsion and electrical power to an aircraft. The system can further include one or more electrical engines configured to provide propulsion for the aircraft. The system can include one or more first electrical power systems configured to provide power to the one or more electrical engines for one or more electrical power propulsion loads for the aircraft. The system can further include one or more second electrical power systems configured to provide power for one or more non-propulsion electrical power loads of the aircraft.

First claim

What is claimed is:

1. A system for distributing electrical power in an aircraft, the system comprising:
one or more gas turbine engines configured to provide propulsion and electrical power to an aircraft;
one or more electrical engines configured to provide propulsion for the aircraft;
one or more first electrical power systems configured to provide power to the one or more electrical engines for one or more electrical power propulsion loads on the aircraft, wherein one or more generators are coupled to a low spool shaft of the one or more gas turbine engines to generate power for the one or more first electrical power systems; and
one or more second electrical power systems configured to provide power for one or more non-propulsion electrical power loads of the aircraft.

2. The system of claim 1 , wherein the one or more first electrical power systems are configured to operate at a first voltage and the one or more second electrical power system(s) are configured to operate at a second voltage, and wherein the first voltage is at least two times greater than the second voltage.

3. The system of claim 1 , wherein the first voltage is at least 1000 Volts DC or 1000 Volts ACRMS.

4. The system of claim 1 , wherein the one or more gas turbine engines are configured to generate power for the one or more second electrical power systems.

5. The system of claim 4 , wherein one or more generators are coupled to a high spool shaft of the one or more gas turbine engines to generate power for the one or more second electrical power systems.

6. The system of claim 1 , further comprising:
one or more contactors configured to adjust between an open position and a closed position, wherein the one or more contactors are configured to couple one or more of the first electrical power systems to one or more of the second electrical power systems when in the closed position.

7. The system of claim 6 , further comprising:
one or more control devices configured to
monitor an operational status of the one or more second electrical power systems,
detect a failure associated with the one or more second electrical power systems based at least in part on the operational status, and
send one or more command signals to the one or more contactors to couple one or more of the first electrical power systems to one or more of the second electrical power systems based at least in part on the detected failure such that one or more of the first electrical power systems can provide power to one or more of the second electrical power systems for the one or more non-propulsion loads of the aircraft.

8. The system of claim 7 , further comprising:
one or more power converters configured to convert a first power associated with the first electrical power systems to a second power associated with the second electrical power systems.

9. The system of claim 1 , wherein the one or more gas turbine engines comprise a plurality of gas turbine engines, wherein the one or more first electrical power systems comprise a plurality of high voltage electrical power systems, wherein the one or more electrical engines comprise a single electrical engine, wherein each gas turbine engine is configured to generate power for at least one high voltage electrical power system, and wherein the plurality of high voltage electrical power systems is configured to provide power to the single electrical engine.

10. The system of claim 9 , wherein the single electrical engine is configured to provide boundary layer ingestion for the aircraft.

11. The system of claim 1 , wherein the one or more gas turbine engines comprise a plurality of gas turbine engines, wherein the one or more first electrical power systems comprise a plurality of high voltage electrical power systems, wherein the one or more electrical engines comprise a plurality of electrical engines, wherein each gas turbine engine is configured to generate power for at least one high voltage electrical power system, and wherein each of the high voltage electrical power systems is configured to provide power to at least one of the electrical engines.

12. The system of claim 1 , wherein the one or more gas turbine engines comprise a plurality of gas turbine engines, wherein the one or more first electrical power systems comprise a plurality of high voltage electrical power systems, wherein the one or more electrical engines comprise a plurality of electrical engines, and wherein at least one electrical engine is configured to provide rotational power to at least one gas turbine engine to provide propulsion for the aircraft.

13. The system of claim 1 , wherein at least one of the electrical engines or the gas turbine engines are configured to operate as one or more ram air turbines to generate electrical power for the aircraft.

14. A method for distributing electrical power in an aircraft, the method comprising:
monitoring, by one or more control devices, an operational status of a lower voltage electrical power system included on an aircraft,
wherein the lower voltage electrical power system is configured to provide power to one or more onboard systems of the aircraft for one or more non-propulsion electrical power loads;
detecting, by the one or more control devices, a failure associated with the lower voltage electrical power system based at least in part on the operational status; and
coupling, by the one or more control devices, a high voltage electrical power system to the lower voltage electrical power system based at least in part on the detected failure such that the high voltage electrical power system can provide power to the lower voltage electrical power system for the one or more non-propulsion electrical power loads of the aircraft.

15. The method of claim 14 , wherein the high voltage electrical power system is configured to operate at a first voltage of at least 1000 Volts DC or 1000 Volts ACRMS, and wherein the lower voltage electrical power system is configured to operate at a second voltage that is lower than the first voltage.

16. The method of claim 14 , wherein the failure of the lower voltage electrical power system at least partially inhibits at least one of an ability of the lower voltage electrical power system to receive power from one or more gas turbine engines of the aircraft or an ability of the lower voltage electrical power system to provide power for the one or more non-propulsion electrical power loads of the aircraft.

17. The method of claim 14 , wherein coupling, by the one or more control devices, the high voltage electrical power system to the lower voltage electrical power system comprises:
sending, by the one or more control devices, one or more command signals to one or more tie bus contactors to couple the high voltage electrical power system to the lower voltage electrical power system.

18. An aircraft, comprising:
one or more gas turbine engines configured to provide propulsion and electric power to the aircraft;
one or more electrical engines;
one or more onboard systems configured to receive power for one or more non-propulsion electrical power loads;
one or more high voltage electrical power systems configured to receive a first power generated by one or more of the gas turbine engines and to provide a second power to the one or more electrical engines;
one or more lower voltage electrical power systems configured to receive a third power generated by one or more of the gas turbine engines and to provide a fourth power to the one or more onboard systems;
one or more contactors configured to couple one o

Assignees

• Ge Aviation Systems Llc

Inventors

• Huang Hao

Classifications

• B64D27/10 Primary

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• B64D2027/026

  Operations & Transport · mapped topic

• B64D27/24 Primary

  using steam or spring force (jet aircraft B64D27/16) · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title