Multi-path secondary power system for an aircraft

• US 6,142,418 A
• Filed: 05/12/1998
• Issued: 11/07/2000
• Est. Priority Date: 05/12/1998
• Status: Expired due to Term

• Current Assignee: Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Hamilton Sundstrand Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Short, Keith E., Weber, Kent
• Primary Examiner(s): Swiatek, Robert P.
• Application Number:
  US09/076,222
• Time in Patent Office: 910 Days
• Field of Search: 244/58, 244/54, 244/17.19, 244/17.21, 244/17.13
• US Class Current: 244/58
• CPC Class Codes: B64D 41/00 Power installations for auxiliary purposes
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

An improved single engine military aircraft is provided through the use of an improved secondary power system which incorporates an additional accessory drive, and utilizes improved multi-path system architecture together with optimal distribution of accessories to thereby enhance partial operational flexibility of the secondary power system in both normal and partial failure modes of operation. The additional accessory drive also provides an aircraft in which the engine can be removed with minimal disruption of the EMAD or AMAD and accessories mounted thereon to thereby enhance both initial manufacturability and repairability of the aircraft and secondary power system.

Claims

1. An aircraft having a propulsion engine driving a secondary power system comprising:

a) an engine gearbox operably connected to the propulsion engine; and

b) a first and a second accessory drive operably connected to said engine gearbox to be rotationally driven thereby, with said at least one of said first and second accessory drives having drive means for driving aircraft accessories.

2. The aircraft of claim 1 wherein said engine gearbox includes engine gearbox lubrication means for said propulsion engine and engine gearbox.

3. The aircraft of claim 2 wherein said first accessory drive includes first accessory drive lubrication means separate from said engine gearbox lubrication means for providing lubrication to said first accessory drive.

4. The aircraft of claim 2 wherein said second accessory drive includes second accessory drive lubrication means separate from said engine gearbox lubrication means for providing lubrication to said second accessory drive.

5. The aircraft of claim 1 wherein said first accessory drive includes first accessory drive lubrication means.

6. The aircraft of claim 1 wherein said second accessory drive includes second accessory drive lubrication means.

7. The aircraft of claim 1, wherein:

a) said engine gearbox includes engine gearbox lubrication means for said propulsion engine and engine gearbox;

b) said first accessory drive includes first accessory drive lubrication means separate from said engine gearbox lubrication means for providing lubrication to said first accessory drive; and

c) said second accessory drive includes lubrication means separate from said engine gearbox lubrication means for providing lubrication to said second accessory drive.

8. The aircraft of claim 1, wherein at least one of said first and second accessory drives are operably connected to said engine gearbox only via a rotating shaft.

9. The aircraft of claim 1, wherein the propulsion engine and engine gearbox are removable from the aircraft without removal of at least one of said first and second accessory drives.

10. The aircraft of claim 1, wherein the propulsion engine and engine gearbox are removable from the aircraft without removal of either said first and second accessory drives.

11. The aircraft of claim 1, wherein said secondary power system includes a first source of secondary power operably connected to rotatably drive said first accessory drive.

12. The aircraft of claim 11 wherein said secondary power system includes a second source of secondary power operably connected to rotatably drive said second accessory drive.

13. The aircraft of claim 1 wherein at least one of said first or second accessory drives includes means driven by said engine gearbox for driving an accessory operably attached to said at least one of said first or second accessory drives.

14. The aircraft of claim 13 wherein said means for driving includes a clutch operably connected to selectively connect or disconnect said means for driving from said engine gearbox.

15. The aircraft of claim 14 wherein said first accessory drive further includes a secondary power source operably connected to said means for driving for driving said means for driving.

16. The aircraft of claim 15 wherein said means for driving further includes a clutch operably connected for selective engagement and disengagement of said secondary power source from said means for driving.

17. The aircraft of claim 1 wherein at least one of said first and second accessory drives further includes a source of auxiliary power and a torque converter for operably connecting said source of auxiliary power to said engine gearbox for starting said propulsion engine.

18. The aircraft of claim 1 wherein at least one of said first and second accessory drives further includes a source of auxiliary power and a torque converter for operably connecting said source of auxiliary power to said engine gearbox for starting said source of auxiliary power.

19. The aircraft of claim 1 further including a hydraulic circuit having a first and a second pump connected in parallel, with said first pump being operably connected to said first accessory drive to be driven thereby, and said second pump being operably connected to said second accessory drive to be driven thereby.

20. The aircraft of claim 1 wherein at least one of said accessory drives is an EMAD, mounted to the engine gearbox.

21. The aircraft of claim 1 further including an airframe;

and wherein at least one of said accessory drives is mounted on said airframe.

22. An aircraft having a propulsion engine driving a secondary power system comprising:

a) an engine gearbox operably connected to the propulsion engine; and

b) a first and a second accessory drive operably connected to said engine gearbox to be rotationally driven thereby, with said at least one of said first and second accessory drives having drive means for driving aircraft accessories;

said first accessory drive including first accessory drive lubrication means separate from said engine gearbox lubrication means for providing lubrication to said first accessory drive, and said second accessory drive including lubrication means separate from said engine gearbox lubrication means for providing lubrication to said second accessory drive.