Reducing condensation in dimmable window systems

• US 9,365,281 B2
• Filed: 11/19/2014
• Issued: 06/14/2016
• Est. Priority Date: 11/19/2013
• Status: Active Grant

• Current Assignee: Gentex Corporation
• Original Assignee: Gentex Corporation
• Inventors: Driscoll, David I., Busscher, Bradley L.
• Primary Examiner(s): HASAN, MOHAMMED A
• Application Number:
  US14/547,564
• Publication Number:
  US 20150138622A1
• Time in Patent Office: 573 Days
• Field of Search: 359270-280, 359/296, 359/265
• US Class Current: 1/1
• CPC Class Codes: B64C 1/1492 Structure and mounting of the transparent elements in the window or windscreen
• CPC Class Codes: B64D 45/0063 by avoiding the use of electronic equipment during flight, e.g. of mobile phones or laptops

Abstract

An aircraft window mounting assembly having a pressure pane in abutting contact with an inner surface of an exterior pressure pane frame. A bezel is proximate a periphery of the pressure pane and defines an inner opening. The bezel includes an inner wall, an outer wall, an exterior wall, and an interior wall. A dust cover is proximate the interior wall of the foam bezel. An electro-optic element is disposed in the opening and is configured for reception by the inner wall. The pressure pane, the foam bezel, and the electro-optic element define an exterior cavity. The bezel, the electro-optic element, and the dust cover define an interior cavity. A first relief passage is in fluid communication with the exterior cavity and the interior cavity. A second relief passage is in fluid communication with the interior cavity and one of an aircraft interior cabin and an aircraft wall.

Claims

1. An aircraft window mounting assembly comprising:

a pressure pane in abutting contact with an inner surface of an exterior pressure pane frame;

a bezel proximate a periphery of the pressure pane and defining an inner opening, the foam bezel including an inner wall, an outer wall, an exterior wall, and an interior wall;

a dust cover proximate the interior wall of the bezel;

an electro-optic element disposed in the opening and configured for reception by the inner wall, wherein the pressure pane, the bezel, and the electro-optic element define an exterior cavity, and wherein the bezel, the electro-optic element, and the dust cover define an interior cavity;

a first relief passage in fluid communication with the exterior cavity and the interior cavity; and

a second relief passage in fluid communication with the interior cavity and one of an aircraft interior cabin and an aircraft wall.

2. The aircraft window mounting assembly of claim 1, further comprising:

an outer reveal and an inner reveal, wherein the dust cover is disposed between the outer reveal and the inner reveal.

3. The aircraft window mounting assembly of claim 1, wherein the first relief passage includes a U-shaped cross-section that extends around the electro-optic element.

4. The aircraft window mounting assembly of claim 1, wherein the electro-optic element is an electrochromic element.

5. The aircraft window mounting assembly of claim 1, wherein the second relief passage is includes a linear configuration that extends generally vertically through a lower portion of the bezel.

6. The aircraft window mounting assembly of claim 1, wherein the bezel is juxtaposed proximate both the exterior pressure pane frame and the pressure pane.

7. The aircraft window mounting assembly of claim 1, wherein the bezel alone defines the first relief passage.

8. The aircraft window mounting assembly of claim 1, wherein the bezel alone defines the second relief passage.

9. An aircraft window mounting assembly comprising:

a compliant bezel defining an inner opening, the compliant bezel including an inner wall having a channel;

a dust cover proximate the compliant bezel;

an electro-optic element disposed in the opening and configured for reception in the channel of the inner wall, wherein the pressure pane, the compliant bezel, and the electro-optic element define an exterior cavity, and wherein the compliant bezel, the electro-optic element, and the dust cover define an interior cavity;

a first relief passage in fluid communication with the exterior cavity and the interior cavity; and

a second relief passage in fluid communication with the interior cavity and an expansion bellows mechanism.

10. The aircraft window mounting assembly of claim 9, further comprising:

An outer reveal and an inner reveal, wherein the dust cover is disposed between the outer reveal and the inner reveal.

11. The aircraft window mounting assembly of claim 9, wherein the first relief passage includes a U-shaped cross-section that extends around the electro-optic element.

12. The aircraft window mounting assembly of claim 9, wherein the electro-optic element is an electrochromic element.

13. The aircraft window mounting assembly of claim 9, wherein the second relief passage includes a linear configuration that extends generally vertically through a lower portion of the bezel.

14. An aircraft window mounting assembly comprising:

a foam bezel proximate a periphery of the pressure pane and defining an inner opening, the foam bezel including an inner wall, an outer wall, an exterior wall, and an interior wall, wherein the inner wall includes a channel;

an electro-optic element disposed in the opening and configured for reception in the channel of the inner wall, wherein the foam bezel at least partially defines an exterior cavity and wherein the foam bezel also at least partially defines an interior cavity;

a first relief passage extending through the foam bezel and in fluid communication with the exterior cavity and the interior cavity; and

a second relief passage extending through the foam bezel and in fluid communication with the interior cavity and one of an aircraft interior cabin and an aircraft wall.

15. The aircraft window mounting assembly of claim 14, further comprising:

a dust cover proximate the foam bezel.

16. The aircraft window mounting assembly of claim 14, further comprising:

an outer reveal and an inner reveal, wherein the dust cover is disposed between the outer reveal and the inner reveal.

17. The aircraft window mounting assembly of claim 14, wherein the first relief passage includes a U-shaped cross-section that extends around the electro-optic element.

18. The aircraft window mounting assembly of claim 14, wherein the electro-optic element is an electrochromic element.

19. The aircraft window mounting assembly of claim 14, wherein the second relief passage includes a linear configuration that extends generally vertically through a lower portion of the foam bezel.

20. The aircraft window mounting assembly of claim 14, wherein the foam bezel is disposed proximate both a pressure pane and an exterior pressure pane frame.