In-line centrifugal sealant debubbler

Patent metadata

Field	Value
Publication number	US-10080981-B2
Application number	US-201615058721-A
Country	US
Kind code	B2
Filing date	Mar 2, 2016
Priority date	Mar 2, 2016
Publication date	Sep 25, 2018
Grant date	Sep 25, 2018

Abstract

Systems for removing gas from a sealant and transferring gas-less sealant to an applicator are provided. The system may comprise: a rotatable chamber including: a first opening for receiving sealant; a hollow conduit arranged such that when gas accumulates in the center of the rotatable chamber when the rotatable chamber is rotating, the gas is ventable from the rotatable chamber; a second opening for receiving gas-less sealant from the rotatable chamber after the gas is vented from the hollow conduit; and a motor operatively configured to rotate the rotatable chamber; and a gas-less sealant applicator in fluid communication with the second opening of the rotatable chamber such that gas-less sealant released by the second opening is flowable into the applicator. The system may also include a robot arm including an end effector with a sealant dispensing nozzle. A method for applying sealant to an aircraft structure is also provided.

First claim

The invention claimed is:

1. A system for removing gas from a sealant and transferring gas-less sealant to a gas-less sealant applicator, the system comprising:
a rotatable chamber including:
a first opening for receiving sealant, wherein the first opening is at a first axial end of the rotatable chamber;
a hollow conduit arranged such that when gas accumulates in the center of the rotatable chamber when the rotatable chamber is rotating, the gas is ventable from the rotatable chamber,
wherein the hollow conduit has at least one first hollow conduit opening at the center of the rotatable chamber and at least one second hollow conduit opening outside of the rotatable chamber and perpendicular to the at least one first hollow conduit opening;

a second opening for receiving gas-less sealant from the rotatable chamber after the gas is vented from the hollow conduit,
wherein the second opening is at a second axial end of the rotatable chamber, and
wherein the first opening and the second opening are in line with each other;

a motor operatively configured to rotate the rotatable chamber; and
a gas-less sealant applicator in fluid communication with the second opening of the rotatable chamber such that gas-less sealant released by the second opening is flowable into the gas-less sealant applicator.

2. The system of claim 1 further comprising a sealant repository in fluid communication with the first opening of the rotatable chamber for providing the sealant to the first opening.

3. The system of claim 2 further comprising a pneumatic piston disposed such that the piston urges the sealant from the sealant repository to the first opening of the rotatable chamber.

4. The system of claim 2 further comprising a human-powered piston disposed such that the piston urges the sealant from the sealant repository to the first opening of the rotatable chamber.

5. The system of claim 1 further comprising a valve located between the second opening of the rotatable chamber and the gas-less sealant applicator.

6. The system of claim 1 wherein the motor rotates the rotatable chamber at least about 1800 RPM.

7. The system of claim 1 wherein the sealant is a thixotropic fluid.

8. The system of claim 1 wherein the sealant is a compressible fluid.

9. A method for applying sealant to an aircraft structure using the system of claim 1 , the method comprising:
receiving the sealant at the rotatable chamber;
rotating the rotatable chamber such that:
the sealant is separated into the gas-less sealant and the gas; and
the gas is vented outside the rotatable chamber; and

urging the gas-less sealant to the gas-less sealant applicator.

10. The method of claim 9 , further comprising controlling a valve to release the gas-less sealant at the gas-less sealant applicator.

11. The method of claim 9 wherein the rotatable chamber is rotated at about 1800 RPM.

12. The method of claim 9 further comprising moving the gas-less sealant applicator along a predetermined path with a robot arm.

13. A system for providing sealant to an aircraft structure during manufacturing, the system comprising:
a robot arm including an end effector with a sealant dispensing nozzle;
a sealant supply including a supply of raw sealant;
a rotatable chamber disposed on the robot arm, wherein the rotatable chamber includes
a first opening for receiving the sealant, wherein the first opening is at a first axial end of the rotatable chamber;
a hollow conduit arranged such that when gas accumulates in the center of the rotatable chamber when the rotatable chamber is rotating, the gas is ventable from the rotatable chamber,
wherein the hollow conduit has at least one first hollow conduit opening at the center of the rotatable chamber and at least one second hollow conduit opening outside of the rotatable chamber and perpendicular to the at least one first hollow conduit opening;

a second opening for receiving gas-less sealant from the rotatable chamber after the gas is vented from the hollow conduit,
wherein the second opening is at a second axial end of the rotatable chamber, and
wherein the first opening and the second opening are in line with each other;

a motor operatively configured to rotate the rotatable chamber; and
a sealant line connected to the end effector and to the rotatable chamber,
wherein the sealant dispensing nozzle in fluid communication with the sealant line such that gas-less sealant released by the second opening is flowable into the sealant dispensing nozzle.

14. The system of claim 13 further comprising a valve disposed on the sealant line to control the flow of the gasless sealant to the end effector.

15. The system of claim 13 wherein the sealant supply is provided to the rotatable chamber by pressurizing the sealant at the source such that the sealant flows to the rotatable chamber.

16. The system of claim 13 wherein the sealant is a compressible fluid.

17. The system of claim 13 wherein the sealant is a thixotropic fluid.

18. The system of claim 13 wherein the motor rotates the rotatable chamber at least about 1800 RPM.

19. The system of claim 15 wherein the sealant is pressurized at the source by a pneumatic piston.

Assignees

• Boeing Co

Inventors

• Podnar Gregg W

Classifications

• B64D37/02

  Tanks (tanks constructed integrally with aircraft wings B64C3/34) · CPC title

• B05C17/005

  for discharging material {from a reservoir or container located in or on the hand tool} through an outlet orifice by pressure {without using surface contacting members like pads or brushes} · CPC title

• B01D19/0052 Primary

  in rotating vessels, vessels containing movable parts or in which centrifugal movement is caused (B01D19/0026 takes precedence) · CPC title

• B05C5/0225

  characterised by flow controlling means, e.g. valves, located proximate the outlet (B05C5/0258, B05C5/0275 take precedence; supply valves upstream the coating head B05C11/1036) · CPC title

• B05C5/02

  {the liquid or other fluent material being discharged through an outlet orifice by pressure, e.g.} from an outlet device in contact or almost in contact, with the work · CPC title