U.S. patent application number 16/202652 was filed with the patent office on 2020-05-28 for heat exchanger gasket.
The applicant listed for this patent is Hamilton Sundstrand Corporation. Invention is credited to Donald E. Army, Anthony DeLugan.
Application Number | 20200166297 16/202652 |
Document ID | / |
Family ID | 68531477 |
Filed Date | 2020-05-28 |
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United States Patent
Application |
20200166297 |
Kind Code |
A1 |
DeLugan; Anthony ; et
al. |
May 28, 2020 |
HEAT EXCHANGER GASKET
Abstract
A method of affixing a gasket to a flange of a heat exchanger
core includes aligning the gasket with the flange of the heat
exchanger core. The gasket includes a tab extending outward from
the gasket. The flange of the heat exchanger core is contacted with
the gasket. The gasket is secured to the flange by bending the tab
of the gasket around an outer edge of the flange and such that
relative motion between the gasket and the flange is prevented by
the tab.
Inventors: |
DeLugan; Anthony; (Agawam,
MA) ; Army; Donald E.; (Enfield, CT) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Hamilton Sundstrand Corporation |
Charlotte |
NC |
US |
|
|
Family ID: |
68531477 |
Appl. No.: |
16/202652 |
Filed: |
November 28, 2018 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F28F 2275/14 20130101;
F28F 9/001 20130101; F28D 1/0233 20130101; F28D 2021/0021 20130101;
F28F 2230/00 20130101; B64D 13/06 20130101; F28F 9/002 20130101;
F16L 23/003 20130101; F16L 23/14 20130101; F28F 9/04 20130101; F28F
2275/122 20130101; F24F 13/30 20130101; F16J 15/061 20130101 |
International
Class: |
F28F 9/04 20060101
F28F009/04 |
Claims
1. A method of affixing a gasket to a flange of a heat exchanger
core, the method comprising: aligning the gasket with the flange of
the heat exchanger core, wherein the gasket comprises: a body; and
a tab extending outward from the body; contacting the flange of the
heat exchanger core with the gasket; and securing the gasket to the
flange by bending the tab of the gasket around an outer edge of the
flange and such that relative motion between the gasket and the
flange is prevented by the tab.
2. The method of claim 1, wherein aligning the gasket with the
flange of the heat exchanger core comprises: positioning the gasket
a distance from the flange of the heat exchanger core; adjusting an
orientation of the gasket such that a major face of the gasket is
parallel to a major face of the flange; and aligning features of
the gasket with corresponding features of the flange.
3. The method of claim 2, wherein aligning features of the gasket
with corresponding features of the flange comprises aligning
through holes in the gasket with corresponding through holes
disposed in the flange of the heat exchanger core.
4. The method of claim 1, bending the tab of the gasket around an
outer edge of the flange comprises: pushing a distal end of the tab
in a first direction that is towards the heat exchanger core and
perpendicular to the major face of the flange; and pushing the
distal end of the tab towards a middle of the gasket and parallel
to the major face of the flange.
5. The method of claim 1, further comprising retaining the tab as
part of the gasket during operation of the heat exchanger core.
6. The method of claim 1, further comprising: wherein the gasket
comprises: the body comprising: an external edge disposed along an
exterior of the body; an internal edge defining a orifice passing
through the body; and a sealing feature disposed in the body and
extending around the orifice of the body; and the tab connected to
and extending from the external edge of the body, wherein the tab
includes a first end proximal to the external edge of the gasket
and a second end that is located distally from the first end;
wherein the flange comprise: a first major face facing towards the
gasket; a second major face on an opposite side of the flange as
the first face; and an outer endwall positioned and extending
between the first and second major faces of the flange; and wherein
bending the tab of the gasket around an outer edge of the flange
comprises bending the tab such that the first end of the tab comes
into contact with the outer endwall of the flange and such that the
second end of the tab comes into contact with the second major face
of the flange.
7. The method of claim 1, wherein the gasket comprises a metallic
face seal capable of withstanding temperatures of 800 degrees
Fahrenheit (427 degree Celsius) or greater.
8. The method of claim 1, wherein the tab extends outward from the
gasket along a plane that is parallel to a major face of the
gasket.
9. The method of claim 1, wherein bending the tab comprises bending
the tab at a location of a relief cut disposed in the tab.
10. A gasket for engagement with a flange of a header of a heat
exchanger assembly, the gasket comprising: a body comprising: an
external edge disposed along an exterior of the body; an internal
edge defining a orifice passing through the body; and a sealing
feature disposed in the body and extending around the orifice of
the body; and a series of malleable tabs extending from the
external edge of the body.
11. The gasket of claim 10, wherein the tabs are capable of bending
at least approximately 90 degrees.
12. The gasket of claim 10, wherein the gasket comprises a metallic
face seal capable of withstanding temperatures of 800 degrees
Fahrenheit (427 degree Celsius) or greater.
13. The gasket of claim 10, wherein each tab of the series of
malleable tabs extends outward from the gasket along a plane that
is parallel to a major face of the gasket.
14. The gasket of claim 10, wherein each tab of the series of
malleable tabs extends from the gasket approximately perpendicular
to a major face of the gasket.
15. The gasket of claim 10, wherein a tab of the series of
malleable tabs includes a relief cut disposed in a portion of the
tab.
Description
BACKGROUND
[0001] The present disclosure generally relates to heat exchangers.
In particular, the present disclosure relates to metal gaskets used
in heat exchangers.
[0002] Heat exchanger assemblies, such as those used to help
provide conditioned air as part of an environmental control system
("ECS") in an aircraft, may require the use of metal gaskets at an
interface with mating ducting to prevent fluid leakage. It can be
undesirable to ship a metal gasket separately from a corresponding
heat exchanger unit. Furthermore, it may not be possible to
adhesively bond the gasket to the heat exchanger unit under high
temperature conditions, due to the limits of adhesive bonding
temperatures.
SUMMARY
[0003] A method of affixing a gasket to a flange of a heat
exchanger core includes aligning the gasket with the flange of the
heat exchanger core. The gasket includes a tab extending outward
from the gasket. The flange of the heat exchanger core is contacted
with the gasket. The gasket is secured to the flange by bending the
tab of the gasket around an outer edge of the flange and such that
relative motion between the gasket and the flange is prevented by
the tab.
[0004] A gasket for engagement with a flange of a header of a heat
exchanger assembly includes a body and a series malleable tabs. The
body includes an external edge disposed along an exterior of the
body, an internal edge defining an orifice passing through the
body, and a sealing feature disposed in the body and extending
around the internal edge of the body. The series of malleable tabs
extends from the external edge of the body.
[0005] The present summary is provided only by way of example, and
not limitation. Other aspects of the present disclosure will be
appreciated in view of the entirety of the present disclosure,
including the entire text, claims, and accompanying figures.
BRIEF DESCRIPTION OF THE DRAWINGS
[0006] FIG. 1A is an exploded perspective view of a gasket and a
heat exchanger core with a flange.
[0007] FIG. 1B is a perspective view of the gasket of FIG. 1A in
contact with the flange of the heat exchanger core.
[0008] FIG. 2 is an enlarged view of a portion of the gasket
identified by 2-2 from FIG. 1B.
[0009] FIG. 3 is a perspective cross section view of the
gasket.
[0010] FIG. 4A is a perspective view of the gasket attached to the
flange of the heat exchanger core.
[0011] FIG. 4B is an enlarged perspective view of portion 4-4 of
the gasket as shown in FIG. 4A, illustrating the gasket attached to
the flange of the heat exchanger core via tabs of the gasket.
[0012] FIG. 4C is an enlarged perspective view of portion 4-4 of
the gasket as shown in FIG. 4A, illustrating the tabs in a second,
intermediate position relative to the flange of the heat exchanger
core.
[0013] FIG. 4D is an enlarged perspective view of portion 4-4 of
the gasket as shown in FIG. 4A, illustrating a third, final
position of the tabs relative to the flange of the heat exchanger
core.
[0014] FIG. 5A is a perspective view of a tab connected to an outer
edge of a gasket.
[0015] FIG. 5B is a perspective view of a tab connected to a gasket
near an outer edge of the gasket.
[0016] FIG. 5C is a perspective view of a tab connected
perpendicularly to an outer edge of a gasket.
[0017] FIG. 6 is a top view of a gasket with an elliptical
shape.
[0018] While the above-identified figures set forth one or more
embodiments of the present disclosure, other embodiments are also
contemplated, as noted in the discussion. In all cases, this
disclosure presents the invention by way of representation and not
limitation. It should be understood that numerous other
modifications and embodiments can be devised by those skilled in
the art, which fall within the scope and spirit of the principles
of the invention. The figures may not be drawn to scale, and
applications and embodiments of the present invention may include
features and components not specifically shown in the drawings.
DETAILED DESCRIPTION
[0019] For a discussion of an exemplary heat exchanger assembly,
see U.S. patent application Ser. No. 15/879,234 entitled
"ENVIRONMENTAL CONTROL SYSTEM TRI-HEAT EXCHANGER" filed on Jan. 1,
2018, which is herein incorporated by reference in its
entirety.
[0020] FIG. 1A is an exploded perspective view of gasket 10 and
heat exchanger core 12 with gasket 10 shown as separated from heat
exchanger core 12. Gasket 10 is shown to include body 14, tabs 16,
holes 18, sealing element 20, and orifice 22. Heat exchanger core
12 is shown to include first flange 24A (with holes 26A), second
flange 24B (with holes 26B), first circuit inlet 28, first circuit
outlet 30, second circuit inlet 32, and second circuit outlet 34.
FIG. 1B is a perspective view of gasket 10 in contact with first
flange 24A and shows tabs 16 engaged with first flange 24A. FIGS.
1A and 1B will be discussed in tandem.
[0021] Gasket 10 is a sealing element. In this non-limiting
embodiment, gasket 10 is a crushable, metallic face seal. Here, a
shape of gasket 10 is shown as rectangular. In other non-limiting
embodiments, gasket 10 can include other geometric shapes such as
circular, elliptical, parallelogram Heat exchanger core 12 is a
core of a heat exchanger. In this non-limiting embodiment, heat
exchanger core 12 can be part of a heat exchanger assembly of an
ECS of an aircraft. Heat exchanger core 12 can, for example,
include hot and cold circuits passing through heat exchanger core
12 (e.g., in a cross-flow relationship). Body 14 is a flat piece of
solid material. In this non-limiting embodiment, body 14 includes a
metallic material and can be a die-stamped piece of sheet metal.
Tabs 16 are flat, elongated strips of solid material. Eight tabs 16
are shown. In other embodiments, however, there can be more or less
than eight tabs 16. Holes 18, 26A, and 26B are openings. Sealing
element 20 is a portion of body 14 that projects outward from a
major face of body 14. Orifice 22 is an opening in body 14.
[0022] First flange 24A and second flange 24B are flat rims of
solid material extending from heat exchanger core 12. In this
non-limiting embodiment, first flange 24A and second flange 24B are
picture frame flanges with a rectangular shape. In other
non-limiting embodiments, first flange 24A and/or second flange 24B
can include non-rectangular shapes such as circular, C-shaped,
triangular, elliptical, etc. First major face 25 is a flat surface
of first flange 24A. First circuit inlet 28, first circuit outlet
30, second circuit inlet 32, and second circuit outlet 34 are
fluidic openings.
[0023] In FIG. 1A, gasket 10 is shown in a pre-installation phase
and as being positioned a distance from first flange 24A. In this
stage, an orientation of gasket 10 is adjusted such that a major
face of gasket 10 is parallel to a major face of first flange 24A.
Here in FIG. 1A, features of gasket 10 are aligned with
corresponding features of first flange 24A. For example, gasket 10
is shown as aligned with first flange 24A such that each of the
four corners of gasket 10 are in alignment with the four corners of
first flange 24A. Additionally, holes 18 in gasket 10 are aligned
with corresponding holes 26A disposed in first flange 24A of heat
exchanger core 12.
[0024] Heat exchanger core 12 is fluidly connected to other
components of the aircraft ECS via first circuit inlet 28, first
circuit outlet 30, second circuit inlet 32, and second circuit
outlet 34. Tabs 16 are connected to and extend from body 14. In
FIG. 1A, tabs 14 are shown as extending outward from gasket 10
along a plane that is parallel to a major face of gasket 10. In
another non-limiting embodiment, tabs 14 are shown as extending
from gasket 10 approximately perpendicular to a major face of
gasket 10 (see. e.g., FIG. 5C). Tabs 16 can be integrally formed
with body 14. In some embodiments, for example, tabs 16 and body 14
can be produced together via a common sheet metal stamping process.
In another example, tabs 16 can be bonded to body 14 such as
through welding.
[0025] In FIG. 1B, gasket 10 is shown as brought into contact with
first flange 24A. As shown in FIG. 1B, tabs 16 are bent around
first flange 24A of heat exchanger core 12 so as to affix gasket 10
to first flange 24A. During operation of heat exchanger core 12,
tabs 16 are retained as connected to and part of gasket 10.
(Further discussion regarding the connection between tabs 16 and
first flange 24A is provided below with respect to FIGS. 4A-4D.)
Holes 18 are disposed in and extend through portions of body 14.
Sealing element 20 is connected to and extends outward from body 14
in a direction that is perpendicular to the major faces of body 14.
Orifice 22 is extends through an inner portion of body 14 of gasket
10.
[0026] First flange 24A and second flange 24B are connected to and
extend outward from opposite sides of heat exchanger core 12. Holes
26A are disposed in and extend through first flange 24A. Holes 26B
are disposed in and extend through second flange 26B. First circuit
inlet 28 passes through first flange 24A and is fluidly connected
to heat exchanger core 12. First circuit outlet 30 passes through
second flange 24B and is fluidly connected to heat exchanger core
12. Second circuit inlet 32 is fluidly connected to a top portion
of heat exchanger core 12 (top of heat exchanger core 12 as shown
in FIGS. 1A and 1B). Second circuit outlet 34 is fluidly connected
to a bottom portion of heat exchanger core 12 (bottom of heat
exchanger core 12 as shown in FIGS. 1A and 1B).
[0027] Gasket 10 provides a fluidic seal between first flange 24A
and another component of the ECS that attaches/connects to heat
exchanger core 12 via first flange 24A. Gasket 10 is also capable
of withstanding temperatures of 800.degree. Fahrenheit (427 degrees
Celsius) or greater such as 1,000.degree. Fahrenheit (538 degrees
Celsius). Heat exchanger core 12 provides transfer of thermal
energy between two separate fluids (e.g., aircraft engine bleed
air, ambient/fresh air, etc.) Tabs 16 secure gasket 10 to first
flange 24A by bending around an outer edge of first flange 24A
thereby preventing relative motion between gasket 10 and first
flange 24A. Holes 18 in gasket 10 provide an opening through which
a mechanical fastener extends in order to affix gasket 10 to first
flange 24A of gasket 12.
[0028] Sealing element 20 is a projection from body 14 or a
projecting portion of body 14 that provides a sealing interface
between body 14 of gasket 10 and another component that comes of
the ECS that connects to first flange 24A on an opposite side of
gasket 10 as first flange 24A. Orifice 22 provides an opening
through which a flow of fluid (e.g., air) enters into heat
exchanger core 12. First flange 24A and second flange 24B provide
interfaces to which other ECS components mount to. Holes 26A and
26B receive fasteners (e.g., bolts) that affix ECS components to
first and second flanges 24A and 24B. First circuit inlet 28 and
second circuit inlet 32 transfer fluid into heat exchanger core 12.
First circuit outlet 30 and second circuit outlet 34 transfer fluid
out of heat exchanger core 12.
[0029] Tabs 16 of gasket 10 enable gasket 10 to be held in place
relative to first flange 24A of heat exchanger core 12 until gasket
10 can be secured via fasteners as described above. This improves
the assembly process of the ECS by saving an installer the work of
holding gasket 10 in place while trying to sandwich gasket 10
between first flange 24A and the other component being attached to
first flange 24A. This can be particularly beneficial when
conditions require first flange 24A to be facing in a downwards
direction relative to gravity during installation/assembly. Using
tabs 16 to attach gasket 10 to first flange 24A also enables making
gasket 10 integral to heat exchanger core 12 in order to avoid
shipping gasket 10 by itself (e.g., separately from heat exchanger
core 12), and reducing any logistical/handling issues associated
with shipping gasket 10 separately from heat exchanger core 12.
Tabs 16 also provide the benefit of reducing maintenance time at
the airliner level and the number of parts the maintainer needs to
handle. Additionally, due to the mechanical nature of the
connection between tabs 16 and first flange 24A, gasket 10 is
capable of being fastened to heat exchanger core 12 when
temperatures are too high to use a bonding adhesive (e.g., such as
temperature above 800 degrees Fahrenheit).
[0030] FIG. 2 is an enlarged view of a portion of gasket 10
identified by 2-2 from FIG. 1B and shows body 14, holes 18, sealing
element 20, orifice 22, and internal edge 36 of body 14. FIG. 3 is
a perspective cross section view of gasket 10 taken along 3-3 in
FIG. 2 and shows body 14, sealing element 20, and internal edge 36
of body 14. FIGS. 2 and 3 are discussed in tandem.
[0031] FIGS. 2 and 3 are provided to show the relative position of
sealing element 20 in body 14, as well as to show a shape of
sealing element 20. Here, sealing element 20 is shown as a
C-shaped, raised ridge that protrudes outward from body 14 of
gasket 10 in a direction that is perpendicular to a plane of body
14. In other non-limiting embodiments, sealing element 20 can
include a shape other than a C-shape, such as a triangle, square,
ellipse, or other shape. Sealing element 20 functions as a
crushable seal that engages with a flat face of another component
brought into contact with gasket 10. Sealing element 20 prevents
leakage of fluid flow going through first flange 24A. In this
non-limiting example, sealing element 20 is compressed under
pressure in order to trap any fluid from leaking once fasteners
(e.g., bolts) attached first flange 24A to another component of the
ECS.
[0032] FIG. 4A is a perspective view of gasket 10 attached to first
flange 24A of heat exchanger core 12. FIG. 4B is an enlarged
perspective view of the portion 4-4 shown in FIG. 4A and shows
gasket 10 (with body 14, tabs 16, first ends 38 (of tabs 16),
second end 40 (of tabs 16), and external edge 42 of body 14), and
heat exchanger core 12 (with first flange 24A, holes 26A, second
major face 44, and outer endwall 46), and forces F.sub.1. FIGS. 4A
and 4B show tabs 16 shown in a first, initial position. FIGS. 4A
and 4B will be discussed in tandem.
[0033] First ends 38 are ends of tabs 16 that are proximal (e.g.,
nearest) to external edge 42 of gasket 10. Second ends 40 are ends
of tabs 16 that are distal (e.g., farthest) from external edge 42
of gasket 10. External edge 42 is an endwall of body 14. Second
major face 44 is a large, flat surface of first flange 24A. Outer
endwall 46 is an external edge of first flange 24A.
[0034] As can be seen in FIGS. 4A and 4B, tabs 16 occupy an
initial, un-bent position extending in the same plane as body 14.
As shown in FIG. 4B, forces F.sub.1 are then applied to second ends
40 in order to push second ends 40 in a first direction that is
towards heat exchanger core 12 and that is perpendicular to second
major face 44 of first flange 24A. The resulting positions of tabs
16 after forces F.sub.1 have been applied to tabs 16 are shown in
FIG. 4C.
[0035] FIG. 4C shows tabs 16 in a second, intermediate position. In
FIG. 4C, tabs 16 have been bent approximately 90 degrees such that
second ends 40 of tabs are positioned perpendicular relative to
second major face 44 of first flange 24A. As shown in FIG. 4C,
forces F.sub.2 are then applied to second ends 40 in order to push
second ends 40 towards a middle of gasket 10 and such that second
ends 40 become parallel to second major face 44 of first flange
24A. These positions of tabs 16 are shown in FIG. 4D.
[0036] FIG. 4D shows a third, final position of tabs 16 relative to
first flange 24A. In FIG. 4D, tabs 16 occupy a third and final
position such that first ends 38 of tabs 16 come into contact with
outer endwall 46 of first flange 24A and such that second ends 40
of tabs 16 come into contact with second major face 44 of first
flange 24A. These positions of tabs 16 enable gasket 16 to be
affixed to first flange 24A such that relative motion between
gasket 10 and first flange 24A is prevented.
[0037] FIG. 5A is a perspective view of tab 16A connected to
external edge 42 of gasket 10 at welded interface 48A. Here, tab
16A is shown as connected to external edge 42 of gasket 10 with a
weld joint. In this non-limiting embodiment, both gasket 10 and tab
16A include a metallic material enabling the connection of the two
to be formed via welding. As opposed to tradition adhesive bonding,
welded interface 48A allows gasket 10 with tab 16A to be used in a
high temperature environments common in aircraft where temperatures
can be too high for adhesive bonding techniques. Attaching tab 16A
to gasket 10 as shown in FIG. 5A also enables tab 16A to be of a
different material than gasket 10 allowing a user to select a
desirable malleability of tabs 16A based on material properties of
the metal chosen for tabs 16A.
[0038] FIG. 5B is a perspective view of tab 16B connected to gasket
10 near external edge 42 of gasket 10. Here, tab 16B is welded to
gasket 10 at welded interface 48B located on a major surface of
gasket 10. This configuration and location of welded interface 48B
allows for an alternate location of tab 16B which may be desirable
based on the thickness of tab 16B and the malleability of tab
16B.
[0039] FIG. 5C is a perspective view of tab 16C connected
perpendicularly to external edge 42 of gasket 10 at welded
interface 48C and shows tab 16C as including relief cut 50. Relief
cut 50 is a channel that extends or cuts into a portion of tab 16C.
In this non-limiting embodiment, a single relief cut 50 is shown.
In other non-limiting embodiments, more than one relief cut 50 can
be used in tab 16C (and/or tabs 16, 16A, and 16B). Relief cut 50
can be cut into or stamped in tab 16C.
[0040] Relief cut 50 provides a pre-determined location where tab
16C is to be bent as force is applied to tab 16C to bend tab 16C
around first flange 24A (see e.g., FIGS. 4A-4D). Relief cut 50
reduces the potential of shearing or breaking tab 16C as tab 16C is
bent during the steps of attaching gasket 10 to first flange 24A of
heat exchanger core 12. By creating a designated bend of tab 16C
with relief cut 50, there is less material that is subject to
bending at relief cut 50 than at other portions of tab 16C, thereby
reducing the amount of shear forces encountered by tab 16C at
relief cut 50.
[0041] FIG. 6 is a top view of gasket 110 with an elliptical shape
and shows body 114, tabs 116, holes 118, sealing element 120, and
orifice 122. Here, gasket 110 is shown to include a circular or
elliptical shape (e.g., with its eccentricity equal to zero).
Elliptically shaped gasket 110 can be used with corresponding
elliptically shaped attachment flanges on a heat exchanger
assembly.
Discussion of Possible Embodiments
[0042] The following are non-exclusive descriptions of possible
embodiments of the present invention.
[0043] A method of affixing a gasket to a flange of a heat
exchanger core includes aligning the gasket with the flange of the
heat exchanger core. The gasket includes a tab extending outward
from the gasket. The flange of the heat exchanger core is contacted
with the gasket. The gasket is secured to the flange by bending the
tab of the gasket around an outer edge of the flange and such that
relative motion between the gasket and the flange is prevented by
the tab.
[0044] The method of the preceding paragraph can optionally
include, additionally and/or alternatively, any one or more of the
following steps, features, configurations and/or additional
components.
[0045] Aligning the gasket with the flange of the heat exchanger
core can comprise: positioning the gasket a distance from the
flange of the heat exchanger core; adjusting an orientation of the
gasket such that a major face of the gasket can be parallel to a
major face of the flange; and/or aligning features of the gasket
with corresponding features of the flange.
[0046] Through holes in the gasket can be aligned with
corresponding through holes disposed in the flange of the heat
exchanger core.
[0047] Bending the tab of the gasket around an outer edge of the
flange can comprise: pushing a distal end of the tab in a first
direction that can be towards the heat exchanger core and/or
perpendicular to the major face of the flange; and/or pushing the
distal end of the tab towards a middle of the gasket and/or
parallel to the major face of the flange.
[0048] The tab can be retained as part of the gasket during
operation of the heat exchanger core.
[0049] The gasket can comprises the body with an external edge that
can be disposed along an exterior of the body, an internal edge
that can define an orifice passing through the body, and/or a
sealing feature that can be disposed in the body and/or extend
around the orifice of the body; and/or the tab can be connected to
and/or extend from the external edge of the body, wherein the tab
can include a first end proximal to the external edge of the gasket
and/or a second end that can be located distally from the first
end; wherein the flange can comprise a first major face facing
towards the gasket, a second major face on an opposite side of the
flange as the first face, and/or an outer endwall positioned and/or
extending between the first and second major faces of the flange;
and wherein bending the tab of the gasket around an outer edge of
the flange can comprise bending the tab such that the first end of
the tab comes into contact with the outer endwall of the flange
and/or such that the second end of the tab comes into contact with
the second major face of the flange.
[0050] The gasket can comprise a metallic face seal capable of
withstanding temperatures of 800 degrees Fahrenheit (427 degree
Celsius) or greater.
[0051] The tab can extend outward from the gasket along a plane
that can be parallel to a major face of the gasket.
[0052] Bending the tab can comprises bending the tab at a location
of a relief cut disposed in the tab.
[0053] A gasket for engagement with a flange of a header of a heat
exchanger assembly includes a body and a series malleable tabs. The
body includes an external edge disposed along an exterior of the
body, an internal edge defining an orifice passing through the
body, and a sealing feature disposed in the body and extending
around the internal edge of the body. The series of malleable tabs
extends from the external edge of the body.
[0054] The gasket of the preceding paragraph can optionally
include, additionally and/or alternatively, any one or more of the
following features, configurations and/or additional
components.
[0055] The tabs can be capable of bending at least approximately 90
degrees.
[0056] The gasket can comprise a metallic face seal capable of
withstanding temperatures of 800 degrees Fahrenheit (427 degree
Celsius) or greater.
[0057] Each tab of the series of malleable tabs can extend outward
from the gasket along a plane that can be parallel to a major face
of the gasket.
[0058] Each tab of the series of malleable tabs can extend from the
gasket approximately perpendicular to a major face of the
gasket.
[0059] A tab of the series of malleable tabs can include a relief
cut disposed in a portion of the tab.
[0060] While the invention has been described with reference to an
exemplary embodiment(s), it will be understood by those skilled in
the art that various changes may be made and equivalents may be
substituted for elements thereof without departing from the scope
of the invention. In addition, many modifications may be made to
adapt a particular situation or material to the teachings of the
invention without departing from the essential scope thereof.
Therefore, it is intended that the invention not be limited to the
particular embodiment(s) disclosed, but that the invention will
include all embodiments falling within the scope of the appended
claims.
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