System of harness and engine case for aircraft engine

Patent metadata

Field	Value
Publication number	US-11211184-B2
Application number	US-201916255444-A
Country	US
Kind code	B2
Filing date	Jan 23, 2019
Priority date	Jan 23, 2019
Publication date	Dec 28, 2021
Grant date	Dec 28, 2021

Abstract

An aircraft engine comprises an engine case, the engine case flange(s). A harness of wires extends in proximity to the engine case. The harness of wires includes two or more metal shield sleeves externally covering a bundle of wires in a longitudinal direction, the metal shield sleeves being at least partially electrically insulated from one another. A conductive contact between the at least one flange and at least one of the metal shield sleeve.

First claim

The invention claimed is:

1. An aircraft engine comprising:
an engine case having at least one flange;
a harness of wires extending in proximity to the engine case, the harness of wires including a metal shield sleeve externally covering a bundle of wires in a longitudinal direction, at least one break in the metal shield sleeve to provide at least two sleeve segments of the metal shield sleeve longitudinally spaced along the harness of wires; and
a conductive contact between the at least one flange and at least one of the sleeve segments.

2. The aircraft engine according to claim 1 , wherein the metal shield sleeve is an outer braid with metallic content.

3. The aircraft engine according to claim 1 , wherein the at least one break has a size of at least 0.2″ between ends of adjacent ones of the separate segments.

4. The aircraft engine according to claim 1 , wherein the at least one break has a size of at most 0.5″ between ends of adjacent ones of the separate segments.

5. The aircraft engine according to claim 1 , wherein the flange includes a mated flange pair joining annular case sections.

6. The aircraft engine according to claim 5 , further comprising a connector at a junction between the conductive wire and the at least one flange.

7. The aircraft engine according to claim 6 , wherein the connector is a terminal lug.

8. The aircraft engine according to claim 5 , wherein the conductive wire has an end connected to or adjacent to an end of one of the separate segments of the metal shield sleeve.

9. The aircraft engine according to claim 1 , further comprising an insulating sheath covering the metal shield sleeve and the at least one break, an opening being defined in the insulating sheath for said conductive contact.

10. The aircraft engine according to claim 1 , wherein the engine case has a plurality of engine case portions interconnected by flanges, the harness of wires extending along the engine case for one said break to be in proximity to each one of said flanges.

11. An aircraft engine comprising:
an engine case, the engine case having at least one flange;
a harness of wires extending in proximity to the engine case, the harness of wires including at least two metal shield sleeves externally covering a bundle of wires in a longitudinal direction, the at least two metal shield sleeves being at least partially electrically insulated from one another; and
a conductive contact between the at least one flange and at least one of the metal shield sleeve.

12. The aircraft engine according to claim 11 , wherein the metal shield sleeves are outer braids with metallic content.

13. The aircraft engine according to claim 11 , wherein the electrical insulation is provided by a separation between adjacent ends of the metal shield sleeves has a size of at least 0.2″ between ends of adjacent ones of the separate segments.

14. The aircraft engine according to claim 11 , wherein the separation has a size of at most 0.5″ between said adjacent ends.

15. The aircraft engine according to claim 11 , wherein the flange is a mated flange pair connecting annular engine case portions.

16. The aircraft engine according to claim 11 , further comprising a connector at a junction between a conductive wire and the at least one flange.

17. The aircraft engine according to claim 16 , wherein the connector is a terminal lug.

18. The aircraft engine according to claim 15 , wherein the conductive wire has an end connected to or adjacent to an end of one of the metal shield sleeves.

19. The aircraft engine according to claim 11 , further comprising an insulating sheath covering the metal shield sleeves and a separation therebetween, an opening being defined in the insulating sheath for said conductive contact.

20. The aircraft engine according to claim 11 , wherein the engine case has a plurality of engine case portions interconnected by flanges, the harness of wires extending along the engine case for separations between adjacent ends of metal shield sleeves to be in proximity to each one of said flanges.

Assignees

• Pratt & Whitney Canada

Inventors

• Youssef Michael
• Basse Olivier
• Duke Brant

Classifications

• H01B7/0045

  Cable-harnesses · CPC title

• H01B7/18 Primary

  Protection against damage caused} by wear, mechanical force or pressure; {Sheaths; Armouring · CPC title

• F02K3/06

  with front fan · CPC title

• F01D25/243

  Flange connections; Bolting arrangements (F01D25/265 takes precedence) · CPC title

• F02C7/00 Primary

  Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants (controlling F02C9/00) · CPC title