Non-propulsive utility power (NPUP) generation system for providing secondary power in an aircraft

Patent metadata

Field	Value
Publication number	US-10737802-B2
Application number	US-201715729203-A
Country	US
Kind code	B2
Filing date	Oct 10, 2017
Priority date	Dec 4, 2013
Publication date	Aug 11, 2020
Grant date	Aug 11, 2020

Abstract

An aircraft may include at least one secondary power system requiring secondary power, at least two main engines, and at least three non-propulsive utility power (NPUP) generation systems. The NPUP generation systems may each be configured to provide full-time secondary power during operation of the aircraft. The NPUP generation systems may be configured to provide at least a portion of the secondary power required by the secondary power system.

First claim

What is claimed is:

1. An aircraft, comprising:
a plurality of environmental control systems (ECSs) each requiring compressed air;
a plurality of pneumatic compressors, wherein the pneumatic compressors are configured to provide substantially all the compressed air required by the ECSs;
at least one secondary power system requiring secondary power;
a plurality of main engine generators each coupled to one of at least two main engines, wherein the main engine generators are redundant electrical power sources;
a plurality of non-propulsive utility power (NPUP) generation systems, each with a NPUP generation source, and each configured to provide full-time secondary power during operation of the aircraft, wherein the NPUP generation systems are configured to provide at least a portion of the secondary power required by the at least one secondary power system, the pneumatic compressors are each coupled to a corresponding one of the NPUP generation sources; and
a plurality of generators that are rated to provide substantially all electric power required by electric consumption systems of the aircraft, wherein the plurality of generators are each coupled to a corresponding NPUP generation source.

2. The aircraft of claim 1 , wherein the plurality of NPUP generation systems include at least three NPUP generation systems.

3. The aircraft of claim 2 , wherein the three NPUP generation systems provide substantially all of the secondary power required by the at least one secondary power system.

4. The aircraft of claim 1 , further comprising at least three NPUP generators each coupled to a corresponding one of at least three NPUP generation sources.

5. The aircraft of claim 4 , comprising of at least three pneumatic compressors, each coupled to a corresponding one of the three NPUP generation sources.

6. The aircraft of claim 4 , wherein the at least three NPUP generators provide substantially all electrical power required by the aircraft.

7. The aircraft of claim 4 , wherein two of the at least three NPUP generators are rated to provide substantially all electrical power required by the aircraft, and a remaining NPUP generator is configured to support flight based on an inoperative NPUP generation source.

8. The aircraft of claim 1 , further comprising a plurality of NPUP hydraulic pumps that are each coupled to one of the plurality of NPUP generation sources.

9. The aircraft of claim 8 , further comprising a plurality of supplementary hydraulic pumps that are each driven by one of the at least two main engines.

10. The aircraft of claim 8 , further comprising a plurality of NPUP hydraulic pumps that are each coupled to one of the plurality of primary NPUP generation sources to provide substantially all hydraulic power with one or more backup hydraulic pumps coupled to a redundant NPUP generation source, with a corresponding coupled redundant generator.

11. The aircraft of claim 1 , wherein the NPUP generation systems include at least two NPUP generation systems and wherein at least two NPUP generators are each coupled to a corresponding one of at least two NPUP generation sources.

12. The aircraft of claim 11 , wherein the at least two NPUP generators provide substantially all electrical power required by the aircraft.

13. The aircraft of claim 11 , further comprising a plurality of main engine hydraulic pumps that are each coupled to one of the at least two main engines, wherein the main engine hydraulic pumps are rated to provide substantially all hydraulic power required by the aircraft.

14. The aircraft of claim 13 , further comprising a plurality of electric hydraulic pumps that supplement the main engine hydraulic pumps based on the main engine hydraulic pumps becoming inoperative or during high demand operating conditions.

15. An aircraft, comprising:
a plurality of environmental control systems (ECSs) that each use compressed air;
a plurality of pneumatic compressors, wherein the pneumatic compressors are configured to provide at least a portion of the compressed air required by the plurality of ECSs;
at least one secondary power system requiring secondary power;
a plurality of main engine generators each coupled to one of at least two main engines, wherein the main engine generators are redundant electrical power sources;
a plurality of NPUP generation systems each configured to provide full-time secondary power during operation of the aircraft, wherein the plurality of NPUP generation systems are configured to provide at least a portion of the secondary power required by the at least one secondary power system, and the plurality of pneumatic compressors are each coupled to a corresponding one of the plurality of NPUP generation sources; and
a plurality of generators that are rated to provide substantially all electric power required by electric consumption systems of the aircraft, wherein the plurality of generators are each coupled to a corresponding NPUP generation source.

16. The aircraft of claim 15 , wherein bleed air is extracted from the at least two main engines, and wherein a portion of the bleed air is supplied to the ECSs.

17. The aircraft of claim 16 , wherein the bleed air is used to provide wing ice protection.

18. The aircraft of claim 15 , wherein the pneumatic compressors are configured to provide substantially all the compressed air required by the plurality of ECSs.

19. The aircraft of claim 15 , wherein the plurality of NPUP generation systems include at least three NPUP generation systems.

20. The aircraft of claim 19 , wherein the at least three NPUP generation systems provide substantially all of the secondary power required by the at least one secondary power system.

21. The aircraft of claim 15 , wherein the pneumatic compressor supplies air required to pneumatically start the at least two main engines.

Assignees

• Boeing Co

Inventors

• Krug David S
• Karimi Kamiar J
• Currier Thomas F
• Bayliss Andrew J
• Roe George M
• Liffring Mark E
• Lesyna Mark W
• Severns Christopher M
• Johnson Andrew

Classifications

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title

• B64D15/04

  Hot gas application · CPC title

• B64D41/00 Primary

  Power installations for auxiliary purposes · CPC title

• B60R16/03

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

• H02J9/06

  with automatic change-over {, e.g. UPS systems} · CPC title