Grommet assembly and method of installing a grommet assembly

Patent metadata

Field	Value
Publication number	US-11498692-B2
Application number	US-201916600012-A
Country	US
Kind code	B2
Filing date	Oct 11, 2019
Priority date	Oct 11, 2019
Publication date	Nov 15, 2022
Grant date	Nov 15, 2022

Abstract

Grommet assembly and method for installing a grommet assembly in a penetration hole of a panel. In one embodiment, a grommet assembly is comprised of multiple parts, including end members having a diameter greater than the penetration hole, and a middle member having a diameter sized to fit within the penetration hole. Each of the members includes one or more conduit holes for a conduit that is routed through the penetration hole, and an installation slit disposed between an outer peripheral surface and a conduit hole.

First claim

The invention claimed is:

1. A grommet assembly comprising:
a first end member having a diameter greater than a penetration hole of a panel, wherein the first end member includes:
at least one first conduit hole; and
a first installation slit disposed between an outer peripheral surface of the first end member and the at least one first conduit hole;

a middle member having a diameter sized to fit within the penetration hole of the panel, wherein the middle member includes:
at least one second conduit hole; and
a second installation slit disposed between an outer peripheral surface of the middle member and the at least one second conduit hole; and

a second end member having a diameter greater than the penetration hole of the panel, wherein the second end member includes:
at least one third conduit hole; and
a third installation slit disposed between an outer peripheral surface of the second end member and the at least one third conduit hole;

wherein the first end member, the middle member, and the second end member are separate parts made from an elastic material.

2. The grommet assembly of claim 1 wherein:
the middle member is bonded to the first end member with an adhesive prior to insertion of the middle member in the penetration hole from a first side of the panel.

3. The grommet assembly of claim 2 wherein:
the second end member is bonded to the middle member with an adhesive from a second side of the panel after insertion of the middle member in the penetration hole of the panel.

4. The grommet assembly of claim 1 wherein:
the first end member, the middle member, and the second end member are made from rubber.

5. The grommet assembly of claim 1 wherein:
the first end member, the middle member, and the second end member further include one or more fastener holes.

6. The grommet assembly of claim 5 further comprising:
one or more fasteners configured to pass through the fastener holes to secure the first end member, the middle member, and the second end member together.

7. The grommet assembly of claim 6 wherein the fasteners comprise:
a spacer configured to fit within the fastener holes;
a bolt having a head, and having a shank configured to fit within the spacer; and
a nut configured to screw onto threads of the bolt.

8. The grommet assembly of claim 1 wherein:
the panel is a structure of an aircraft; and
the at least one first conduit hole, the at least one second conduit hole, and the at least one third conduit hole are sized to accommodate a hydraulic tube of the aircraft.

9. The grommet assembly of claim 8 wherein:
the panel comprises a composite panel.

10. The grommet assembly of claim 1 wherein:
when installed, the first installation slit of the first end member and the second installation slit of the middle member are aligned, and the third installation slit of the second end member is oriented at an opposite direction than the first installation slit and the second installation slit.

11. An aircraft comprising:
a composite panel that includes a penetration hole through which a conduit is routed; and
a grommet assembly installed in the penetration hole to secure the conduit;
the grommet assembly comprised of separate parts, the separate parts comprising:
a first end member having a diameter greater than the penetration hole;
a middle member having a diameter sized to fit within the penetration hole; and
a second end member having a diameter greater than the penetration hole;
wherein the conduit passes through conduit holes of the first end member, the middle member, and the second end member;
wherein the first end member and the middle member include installation slits configured to flex open enabling the first end member and the middle member to be installed cross-wise onto the conduit from a first side of the composite panel with the conduit holes of the first end member and the middle member surrounding the conduit;
wherein the second end member includes an installation slit configured to flex open enabling the second end member to be installed cross-wise onto the conduit from a second side of the composite panel with the conduit holes of the second end member surrounding the conduit.

12. The aircraft of claim 11 wherein:
the middle member is bonded to the first end member with an adhesive prior to insertion of the middle member in the penetration hole from the first side of the composite panel.

13. The aircraft of claim 12 wherein:
the second end member is bonded to the middle member with an adhesive from the second side of the composite panel after insertion of the middle member in the penetration hole of the composite panel.

14. The aircraft of claim 11 wherein:
an annular collar of the first end member is bonded to the first side of the composite panel with an adhesive;
an annular collar of the second end member is bonded to the second side of the composite panel with the adhesive; and
an outer peripheral surface of the middle member is bonded to an edge of the penetration hole with the adhesive.

15. The aircraft of claim 11 wherein:
the installation slit of the second end member is oriented at an opposite direction than the installation slits of the first end member and the middle member.

16. The aircraft of claim 11 wherein:
the grommet assembly further includes:
one or more fasteners installed through fastener holes in the first end member, the middle member, and the second end member to secure the first end member, the middle member, and the second end member together.

17. The aircraft of claim 16 wherein the fasteners comprise:
a spacer configured to fit within the fastener holes;
a bolt having a head, and having a shank configured to fit within the spacer; and
a nut configured to screw onto threads of the bolt.

18. A method of installing a grommet assembly in a penetration hole of a panel, wherein a conduit is routed through the penetration hole, the method comprising:
acquiring a first end member having a diameter greater than the penetration hole, and including a first conduit hole and a first installation slit disposed between an outer peripheral surface of the first end member and the first conduit hole;
acquiring a middle member having a diameter sized to fit within the penetration hole, and including a second conduit hole and a second installation slit disposed between an outer peripheral surface of the middle member and the second conduit hole;
acquiring a second end member having a diameter greater than the penetration hole, and including a third conduit hole and a third installation slit disposed between an outer peripheral surface of the second end member and the third conduit hole;
bonding the first end member to the middle member with the first conduit hole aligned with the second conduit hole, and with the first installation slit aligned with the second installation slit;
installing the first end member and the middle member on the conduit from a first side of the panel via the first installation slit and the second installation slit;
inserting the middle member into the penetration hole from the first side of the panel;
installing the second end member on the conduit from a second side of the panel via the third installation slit; and
bonding the second end member to the middle member.

19. The method of claim 18 further comprising:
bonding the first end member to the first side of the panel;
bonding the middle member to an edge of the penetration hole; and
bonding the second end member

Assignees

• Boeing Co

Inventors

• Tian Yuri

Classifications

• H02G3/22 Primary

  Installations of cables or lines through walls, floors or ceilings, e.g. into buildings · CPC title

• F16L5/10

  by using sealing rings or sleeves only · CPC title

• H02G1/00

  Methods or apparatus specially adapted for installing, maintaining, repairing or dismantling electric cables or lines · CPC title

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title

• B64D2221/00

  Electric power distribution systems onboard aircraft · CPC title