Method and apparatus for operating a power system architecture

Patent metadata

Field	Value
Publication number	US-10530153-B2
Application number	US-201715602904-A
Country	US
Kind code	B2
Filing date	May 23, 2017
Priority date	May 23, 2017
Publication date	Jan 7, 2020
Grant date	Jan 7, 2020

Abstract

A method and apparatus for operating a power architecture for an aircraft, includes a primary variable frequency generator system having a first power output, a secondary variable frequency generator system having a second power output, a power distribution node, an essential power bus selectively connected with a set of essential aircraft electrical loads, and a controller module.

First claim

What is claimed is:

1. A power architecture for an aircraft, comprising:
a variable frequency primary generator system having a first power output;
a variable frequency secondary generator system having a second power output;
an essential power bus selectively connected with the first power output and connected with a set of essential aircraft electrical loads;
a power distribution node disposed electrically between the second power output and the essential power bus and configured to selectably connect the second power output to an essential bus power output; and
a controller module configured to, upon failure of the first power output, disconnect the first power output from the essential power bus and connect the essential bus power output with the essential power bus;
wherein the essential bus power output is sufficient to energize the set of essential aircraft electrical loads.

2. The power architecture of claim 1 wherein at least one of the first power output, the second power output, or the essential bus power output is an alternating current (AC) power output.

3. The power architecture of claim 2 wherein the first power output, the second power output, and the essential bus power output are alternating current (AC) power outputs.

4. The power architecture of claim 1 wherein the power distribution node includes a set of contactors operable in response to the controller module.

5. The power architecture of claim 1 wherein the essential power bus has a set of predetermined power demand characteristics.

6. The power architecture of claim 1 wherein the set of essential aircraft electrical loads are essential to the operation of the aircraft, compared with a set of non-essential aircraft electrical loads.

7. The power architecture of claim 1 wherein the primary generator system is mechanically connected with an aircraft engine.

8. The power architecture of claim 1 , further comprising a first aircraft engine system connected with the primary generator system and the secondary generator system, and a second aircraft engine system connected with a second variable frequency primary generator system and a second variable frequency secondary generator system.

9. The power architecture of claim 8 wherein the second secondary generator system includes a third power output connected with the distribution node, and wherein the power distribution node is further configured to selectably connect the third power output to the essential bus power output.

10. The power architecture of claim 9 wherein the power distribution node includes a second essential power output configured to selectably connect with a second essential power bus, and wherein the controller module is configured to, upon failure of the primary generator system and the second secondary generator system, connect the second power output to the essential bus power output to energize the essential power bus and connect the third power output to the second essential power output to energize the second essential power bus simultaneously.

11. The power architecture of claim 9 wherein, upon failure of the first power output, the essential bus power output can supply a sufficient amount of power to the essential aircraft electrical loads for at least 180 minutes.

12. A method of operating a power system architecture, comprising:
receiving, by a control module, a demand signal indicative of an emergency demand for electrical power;
in response to receiving the demand signal, controlling, by the control module, a supplying of electrical power to an essential power bus from a backup generator system including a first variable frequency generator system providing a power output to a backup distribution box configured to selectively enable the power output to energize an essential bus compatible power output selectively connected with the essential power bus; and
further supplying the essential bus compatible power from the essential power bus to a set of essential electrical loads of an aircraft;
wherein the supplying electrical power is proportional to the emergency demand.

13. The method of claim 12 wherein the first variable frequency generator system provides an alternating current (AC) power output.

14. The method of claim 12 wherein the demand signal indicative of an emergency demand for power is triggered by the failure of a variable frequency primary generator system supplying power to the essential power bus.

15. The method of claim 14 wherein the triggering by the failure of the primary generator system includes a variable frequency generator system mechanically powered by an aircraft engine.

16. The method of claim 15 wherein the variable frequency generator system and the backup generator system are mechanically powered by the aircraft engine.

17. The method of claim 16 wherein the supplying of electrical power to the essential power bus from the backup generator system powers the essential electrical loads of the aircraft for at least 180 minutes.

18. The method of claim 16 wherein in response to receiving the demand signal, controlling, by the control module, a supplying of electrical power from a second variable frequency generator system mechanically powered by a second aircraft engine to the backup distribution box.

19. The method of claim 12 wherein the essential power bus is at least one of a first essential power bus associated with a first engine system or a second essential power bus associated with a second engine system.

20. The method of claim 12 wherein the generator system is an auxiliary power unit generator providing the power output.

Assignees

• Ge Aviation Systems Llc

Inventors

• Huang Hao

Classifications

• H02J4/00

  Circuit arrangements for mains or distribution networks not specified as AC or DC; Circuit arrangements for mains or distribution networks combining AC and DC sections or sub-networks (arrangements using intermediate DC-AC-DC conversion H02J1/002; arrangements using high-voltage DC [HVDC] links H02J3/36) · CPC title

• H02J3/0073 Primary

  by providing alternative feeding paths when the main path fails · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• H02J3/381 Primary

  Dispersed generators · CPC title

• H02J9/08 Primary

  requiring starting of a prime-mover · CPC title