Aircraft washer

Abstract

An aircraft pipe coupling including a first pipe end and a second pipe end, and a locking washer disposed between the first pipe end and second pipe end. The locking washer including a first tab in engagement with the first pipe end, and a second tab in engagement with the second pipe end.

Claims

1. An aircraft pipe coupling comprising: a first pipe end and a second pipe end, and a locking washer disposed between the first pipe end and second pipe end, the locking washer comprising: a first tab in engagement with a nut on the first pipe end, and a second tab in engagement with a nut on the second pipe end, a main body abutting a front surface of one of the nuts, wherein the main body and the front surface are parallel to a plane perpendicular to an axis of at least one of the first and second pipe ends, and the main body is separated by a gap from the other of the nuts; wherein the first tab and/or second tab of the locking washer is deformable to allow the engagement of the tab with the appropriate pipe end, and wherein at least one of the first tab and second tab is arranged to be more easily deformed in a particular direction.

2. The aircraft pipe coupling as claimed in claim 1, wherein the main body has an aperture through which the first pipe end and second pipe end are joined, and the first tab and/or second tab extend approximately perpendicular to the plane.

3. The aircraft pipe coupling as claimed in claim 1, comprising a drain port connected to the first pipe end and a drain pipe connected to the second pipe end.

4. The aircraft pipe coupling as claimed in claim 1, comprising a drain configured to remove water from a slat track housing.

5. The aircraft pipe coupling as claimed in claim 1, wherein the locking washer comprises one or more further tabs configured for engagement with the first pipe end or second pipe end.

6. The aircraft pipe coupling as in claim 1, wherein the first and second pipe ends are hollow, and the first pipe end is inserted into the second pipe end.

7. The aircraft pipe coupling as in claim 6, wherein the first and second pipe ends have a common axis.

8. An aircraft pipe coupling comprising: a first pipe having a first pipe end with a threaded outer surface; a second pipe having a second pipe end with a threaded outer surface, wherein the second pipe end is inserted into the first pipe end to establish an internal passage extending from the first pipe to the second pipe; a first nut mounted to the threaded outer surface of the first pipe end; a second nut mounted to the threaded outer surface of the second pipe end; a locking washer between the first nut and the second nut, wherein the locking washer comprises: a main body including an aperture, wherein the main body abuts against one of the first and second nuts, and is separated by a gap from the other of the first and second nuts, and wherein at least one of the first pipe end and the second pipe end extends through the aperture; a first tab extending from and outward of the main body, wherein the first tab is bent out of a plane of the main body and abuts the first nut, wherein the plane is perpendicular to an axis of at least one of the first pipe end and second pipe end; and a second tab extending from and outward of the main body, wherein the second tab is bent out of the plane of the main body and abuts the second nut, and wherein the second tab is bent in a direction with respect to the plane opposite to a direction in which the first tab is bent.

9. The aircraft pipe coupling of claim 8, wherein the main body includes opposite planar surfaces both parallel to the plane.

10. The aircraft pipe coupling of claim 8, wherein the plane of the main body is perpendicular to a common axis of both the first pipe end and the second pipe end.

11. The aircraft pipe coupling of claim 8, further comprising a drain port connected to one of the first pipe and the second pipe, and a drain pipe connected to the other of the second pipe and the first pipe.

12. The aircraft pipe coupling as claimed in claim 8, wherein the locking washer includes an additional tab configured to be bent and abut either the first or second nut.

Description

DESCRIPTION OF THE DRAWINGS

(1) Embodiments of the present invention will now be described by way of example only with reference to the accompanying schematic drawings of which:

(2) FIG. 1 shows a locking washer according to a first embodiment of the invention;

(3) FIG. 2 shows the locking washer of FIG. 1 in a pipe connection according to a second embodiment of the invention;

(4) FIGS. 3A, 3B, and 3C, show front and side views of a locking washer according to the third embodiment of the invention;

(5) FIGS. 4A, 4B, 4C, and 4D, show a locking washer and pipe connection according to a fourth embodiment of the invention,

(6) FIG. 5 shows a locking member according to a fifth embodiment of the invention, and

(7) FIG. 6 shows an aircraft according to a sixth embodiment of the invention.

DETAILED DESCRIPTION

(8) FIG. 1 shows a locking washer 10 according to a first embodiment of the invention. The locking washer 10 comprises a main body 12, a first tab 14, and a second tab 16. The first tab 14 shown in FIG. 1 has already been deformed for allowing engagement with a pipe end fitting. The main body 12 defines an aperture 18 through which a part of a pipe end fitting may be passed to allow joining with another pipe end fitting. When installed in a pipe coupling, the second tab may be deformed, such that it extends in the opposite direction to the first tab, with both the first tab and second tab being perpendicular to the plane being defined by the main body. The tab may be deformed by an engineer using a hammer. The base of the tabs 14, 16, where they join to the main body 12, may be arranged to be more easily deformed in one direction as compared to another direction. This may be as a result of the base of the tab being weakened in one direction, for example by stamping or removal of material from the base of the tab.

(9) FIG. 2 shows the locking washer according to the first embodiment of the invention in an aircraft pipe coupling according to a second embodiment of the invention. A track can drain in an aircraft wing provides a first pipe end 20 to which a flexible hose 22 is connected, the flexible hose providing the second pipe end 26. The flexible hose 22 leads to drain port 24 in the lower cover of the wing. The locking arrangements at both the track can drain and the drain port 24 are the same, and so will only be described for the connection of the hose 22 with the first pipe end 20 of the track can drain. The first pipe end 20 and the second pipe end 26 are threaded to facilitate the screwing together of the first pipe end 20 and the second pipe end 26. The locking washer 10 is threaded between the first pipe end 20 and the second pipe end 26 prior to the two pipe ends being screwed together. Each pipe end includes a hexagonal head to allow the tightening together of the two pipe ends by using a spanner. Once the first pipe end 20 and the second pipe end 26 have been screwed together, with the locking washer trapped between the first pipe 20 and second pipe end 26, the first tab 14 of the locking washer 10 is located in contact with a head of the first pipe end 20. The second tab 16 may then be bent into contact with the head of the second pipe end 26. The locking washer 10 effectively couples together the head of the first pipe end 20 and the head of the second pipe end 26 which prevents any rotational movement of the two heads relative to each other. Thereby, the pipe joint is locked by the screwing together of the two ends, and the use of the locking washer between the heads of the two ends prevents aircraft vibrations etc. from loosening the connection between the two pipe ends by preventing relative rotational movement of the two pipe ends.

(10) FIGS. 3A, 3B, and 3C show front and side views of a locking washer according to a third embodiment of the invention, similar to the locking washer shown in FIG. 1. However, in contrast to FIG. 1, the locking washer of FIGS. 3A, 3B, and 3C, has a main body defining a circular aperture, whereas in FIG. 1 the main body defines a twelve-sided aperture. FIG. 3C shows the first tab and second tab being pre-bent prior to installation. Such pre-bending may make it easier to install the washers in typically cramped aircraft environments.

(11) FIGS. 4A, 4B, 4C, and 4D, show a locking washer 40 according to a third embodiment of the invention. As can be seen, the locking washer comprises a third and fourth tab which may be deformed into contact with respective pipe ends. Such an arrangement may provide a more secure locking of a pipe joint than a locking washer having only two tabs. In the method shown in FIGS. 4A, 4B, 4C, and 4D, the locking washer is first slid into position on a first pipe end 42 of a drain adaptor 44. A first set of tabs 46 are then bent into engagement with a hexagonal head of the first pipe end 42. A second pipe end 47, at the end of a drain hose 48 is connected with the first pipe end 42. A second set of tabs 49 are then bent into engagement with a hexagonal head of the second pipe end 47.

(12) FIG. 5 shows a locking washer 50 according to a fourth embodiment of the invention. The locking washer 50 may include a number of additional small tabs 52 for engagement with a packing ring 54. The use of a packing ring 54 may make it more straightforward to deform the tabs of the locking washer without a resulting deformation of the main body of the locking washer. As can be seen in FIG. 5, the locking washer 50 comprises a number of tabs for engaging with a bolt head, wherein the tabs are deformable and to increase the ease of deformation include a curved crimped section 56.

(13) FIG. 6 shows an aircraft 60, the aircraft comprising a fuel system 62 including a pipe coupling according to any embodiment of the invention described above.

(14) Whilst the present invention has been described and illustrated with reference to particular embodiments, it will be appreciated by those of ordinary skill in the art that the invention lends itself to many different variations not specifically illustrated herein.

(15) Where in the foregoing description, integers or elements are mentioned which have known, obvious or foreseeable equivalents, then such equivalents are herein incorporated as if individually set forth. Reference should be made to the claims for determining the true scope of the present invention, which should be construed so as to encompass any such equivalents. It will also be appreciated by the reader that integers or features of the invention that are described as preferable, advantageous, convenient or the like are optional and do not limit the scope of the independent claims. Moreover, it is to be understood that such optional integers or features, whilst of possible benefit in some embodiments of the invention, may not be desirable, and may therefore be absent, in other embodiments.