U.S. patent application number 16/358183 was filed with the patent office on 2020-09-24 for seal plate lubricant slinger.
The applicant listed for this patent is United Technologies Corporation. Invention is credited to Christopher T. Anglin, Camron Najafi.
Application Number | 20200300122 16/358183 |
Document ID | / |
Family ID | 1000005073996 |
Filed Date | 2020-09-24 |
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United States Patent
Application |
20200300122 |
Kind Code |
A1 |
Anglin; Christopher T. ; et
al. |
September 24, 2020 |
SEAL PLATE LUBRICANT SLINGER
Abstract
A seal plate is disclosed herein that is annular in shape and
configured to rotate about a centerline. The seal plate includes a
seal body having a first axial end forming a sealing surface and a
second axial end opposite the first axial end, a slinger ring
axially rearward of the seal body and having a plurality of
radially extending tabs separated by a plurality of slots, and a
groove between the seal body and the slinger ring. The tabs on the
slinger ring are configured to direct lubricant at least partially
radially inward into the groove and at least partially in a
direction of rotation of the seal plate to cool the seal body.
Inventors: |
Anglin; Christopher T.;
(Manchester, CT) ; Najafi; Camron; (West Hartford,
CT) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
United Technologies Corporation |
Farmington |
CT |
US |
|
|
Family ID: |
1000005073996 |
Appl. No.: |
16/358183 |
Filed: |
March 19, 2019 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F01D 11/02 20130101;
F01D 25/18 20130101; F01D 25/183 20130101 |
International
Class: |
F01D 25/18 20060101
F01D025/18; F01D 11/02 20060101 F01D011/02 |
Claims
1. A seal plate that is annular in shape and configured to rotate
about a centerline, the seal plate comprising: a seal body having a
first axial end forming a sealing surface and a second axial end
opposite the first axial end; a slinger ring axially rearward of
the seal body and having a plurality of radially extending tabs
separated by a plurality of slots; and a groove between the seal
body and the slinger ring, wherein the tabs are configured to
direct lubricant at least partially radially inward into the groove
and at least partially in a direction of rotation of the seal plate
to cool the seal body.
2. The seal plate of claim 1, wherein the plurality of tabs are
each rectangular in shape.
3. The seal plate of claim 1, wherein the plurality of tabs each
have a front edge facing the direction of rotation of the seal
plate that is angled in a radial direction towards the direction of
rotation.
4. The seal plate of claim 1, wherein the plurality of tabs each
have a front edge facing the direction of rotation that is beveled
towards the seal body.
5. The seal plate of claim 1, wherein the plurality of tabs each
have a front edge facing the direction of rotation that is
perpendicular to the direction of rotation.
6. The seal plate of claim 1, wherein a radial depth of the groove
is greater than a radial height of each of the plurality of
tabs.
7. The seal plate of claim 1, wherein the seal body has an angled
surface on a radially outward side adjacent the groove.
8. The seal plate of claim 1, wherein the plurality of tabs
includes at least ten tabs.
9. The seal plate of claim 1, wherein a depth of the groove is
greater than one-half a height of the seal body.
10. A seal assembly centered about a centerline comprising: an
annular, nonrotating sealing element having a first sealing surface
on one axial end; a seal plate that is annular in shape and
configured to rotate about the centerline, the seal plate
comprising: a seal body having a second sealing surface on a first
axial end configured to form a seal with the first sealing surface
of the sealing element and a second axial end opposite the first
axial end; a slinger ring adjacent the second axial end of the seal
body and having a plurality of radially extending tabs
circumferentially separated by a plurality of slots; and a groove
between the seal body and the slinger ring; and a lubricant nozzle
radially outward from the seal plate, the lubricant nozzle
configured to direct lubricant at the seal plate, wherein the tabs
of the seal plate are configured to direct lubricant at least
partially radially inward into the groove and at least partially in
a direction of rotation of the seal plate to cool the seal
body.
11. The seal assembly of claim 10, wherein the lubricant nozzle is
angled to direct lubricant partially in a radially inward direction
and partially in an axial direction.
12. The seal assembly of claim 10, wherein the lubricant nozzle is
angled to direct lubricant partially in the direction of rotation
of the seal plate.
13. The seal assembly of claim 10, further comprising: a shaft
radially inward from and coupled to the seal plate such that the
seal plate and the shaft rotate in unison.
14. The seal assembly of claim 10, wherein the plurality of tabs of
the seal plate are each rectangular in shape.
15. The seal assembly of claim 10, wherein the plurality of tabs of
the seal plate each have a front edge facing the direction of
rotation that is angled in a radial direction towards the direction
of rotation.
16. The seal assembly of claim 10, wherein the plurality of tabs of
the seal plate each have a front edge facing the direction of
rotation that is beveled towards the seal body.
17. The seal assembly of claim 10, wherein the plurality of tabs of
the seal plate each have a front edge facing the direction of
rotation that is perpendicular to the direction of rotation.
18. The seal assembly of claim 10, wherein the seal body has an
angled notch on a radially outward side adjacent the groove.
19. The seal assembly of claim 10, wherein the sealing element is
constructed substantially from carbon.
20. A gas turbine engine comprising the seal assembly of claim 10.
Description
BACKGROUND
[0001] The present disclosure relates to hydrodynamic seal
assemblies and, more particularly, to cooling features in a
hydrodynamic seal plate.
[0002] Hydrodynamic seals are used in various applications,
including for sealing a bearing cavity (in which cooling lubricant
is present) from other components of a gas turbine engine. A
hydrodynamic seal includes a nonrotating seal element, a rotating
seal plate, and a bearing/sealing surface that forms between the
nonrotating seal element and rotating seal plate to provide a seal.
The bearing/sealing surface (which can contain a thin film of air,
in some applications) prevents fluids, such as oil or another
cooling lubricant, from flowing through a gap between the
nonrotating seal element and the rotating seal plate while also
reducing wear on the sealing surfaces of the seal element and the
seal plate. Friction between the nonrotating seal element and the
rotating seal plate can cause heat to be generated within the seal
plate. Oftentimes, cooling lubricant is introduced into channels
that extend through the seal plate to mitigate the heat. However,
the environment surrounding the hydrodynamic seal can be limited in
space, preventing proper positioning of lubricant nozzles and other
components necessary to convey the lubricant to the channels within
the seal plate.
SUMMARY
[0003] A seal plate is disclosed herein that is annular in shape
and configured to rotate about a centerline. The seal plate
includes a seal body having a first axial end forming a sealing
surface and a second axial end opposite the first axial end, a
slinger ring axially rearward of the seal body and having a
plurality of radially extending tabs separated by a plurality of
slots, and a groove between the seal body and the slinger ring. The
tabs on the slinger ring are configured to direct lubricant at
least partially radially inward into the groove and at least
partially in a direction of rotation of the seal plate to cool the
seal body.
[0004] A seal assembly centered about a centerline includes a
sealing element, a seal plate, and a lubricant nozzle. The sealing
element is annular and nonrotating and has a first sealing surface
on one axial end. The seal plate is annular and configured to
rotate about the centerline. The seal plate includes a seal body
having a second sealing surface on a first axial end that is
configured to form a seal with the first sealing surface of the
sealing element and a second axial end opposite the first axial
end, a slinger ring that is adjacent the second axial end of the
seal body and has a plurality of radially extending tabs
circumferentially separated by a plurality of slots, and a groove
between the seal body and the slinger ring. The lubricant nozzle is
radially outward from the seal plate and configured to direct
lubricant at the seal plate. The tabs of the seal plate are
configured to direct lubricant at least partially radially inward
into the groove and at least partially in a direction of rotation
of the seal plate to cool the seal body.
BRIEF DESCRIPTION OF THE DRAWINGS
[0005] FIG. 1 is a partial cross-sectional view of a gas turbine
engine.
[0006] FIG. 2A is a cross-sectional view of a seal assembly
including a seal plate.
[0007] FIG. 2B is a perspective view of the seal plate in FIG.
2A.
[0008] FIG. 3 is a perspective view of a second embodiment of a
seal plate.
[0009] FIG. 4 is a perspective view of a third embodiment of a seal
plate.
DETAILED DESCRIPTION
[0010] A seal plate of a seal assembly is disclosed herein that
includes a slinger ring that directs lubricant (introduced by a
lubricant nozzle at a location radially outward from the seal
plate) radially inward into a groove and circumferentially in a
direction of rotation. The slinger ring in conjunction with the
lubricant provides improved cooling to the seal plate. The slinger
ring includes a plurality of tabs (separated by slots) having
various configurations for directing the lubricant more in a
radially inward direction and/or more in a circumferential
direction. Because of space limitations surrounding the seal plate,
the lubricant nozzle is located radially outward from the seal
plate, and thus the lubricant is directed from a location radially
outward from the seal plate at least partially radially inward and
at least partially axially rearward towards the seal plate. The
slinger ring functions to direct/alter the flow of lubricant to
provide efficient cooling of the seal plate.
[0011] FIG. 1 is a partial cross-sectional view of gas turbine
engine 20. Gas turbine engine 20 is disclosed herein as a two-spool
turbofan that generally incorporates fan section 22, compressor
section 24, combustor section 26, and turbine section 28.
Alternative engines might include an augmentor section (not shown)
among other systems or features. Fan section 22 drives air along
bypass flow path B in a bypass duct defined within nacelle 15,
while compressor section 24 drives air along core flow path C for
compression and communication into combustor section 26 and then
expansion through turbine section 28. Although depicted as a
two-spool turbofan gas turbine engine in the disclosed non-limiting
embodiment, it should be understood that the concepts described
herein are not limited to use with two-spool turbofans as the
teachings may be applied to other types of turbine engines
including three-spool architectures.
[0012] Exemplary gas turbine engine 20 generally includes low speed
spool 30 and high speed spool 32 mounted for rotation about engine
central longitudinal axis (i.e., centerline) A relative to engine
static structure 36 via several bearing systems 38. It should be
understood that various bearing systems 38 at various locations may
alternatively or additionally be provided, and the location of
bearing systems 38 may be varied as appropriate to the
application.
[0013] Low speed spool 30 generally includes inner shaft 40 that
interconnects fan 42, first (or low) pressure compressor 44, and
first (or low) pressure turbine 46. Inner shaft 40 is connected to
fan 42 through a speed change mechanism, which in exemplary gas
turbine engine 20 is illustrated as geared architecture 48 to drive
fan 42 at a lower speed than low speed spool 30. High speed spool
32 includes outer shaft 50 that interconnects second (or high)
pressure compressor 52 and second (or high) pressure turbine 54.
Combustor 56 is arranged in exemplary gas turbine 20 between high
pressure compressor 52 and high pressure turbine 54. Mid-turbine
frame 57 of engine static structure 36 is arranged generally
between high pressure turbine 54 and low pressure turbine 46.
Mid-turbine frame 57 further supports bearing systems 38 in turbine
section 28. Inner shaft 40 and outer shaft 50 are concentric and
rotate via bearing systems 38 about centerline A.
[0014] The core airflow is compressed by low pressure compressor 44
then high pressure compressor 52, mixed and burned with fuel in
combustor 56, and then expanded over high pressure turbine 54 and
low pressure turbine 46. Mid-turbine frame 57 includes airfoils 59
which are in core airflow path C. Turbines 46 and 54 rotationally
drive respective low speed spool 30 and high speed spool 32 in
response to the expansion. It will be appreciated that each of the
positions of fan section 22, compressor section 24, combustor
section 26, turbine section 28, and fan drive gear system 48 may be
varied. For example, gear system 48 may be located aft of combustor
section 26 or even aft of turbine section 28, and fan section 22
may be positioned forward or aft of the location of gear system 48.
Bearing compartment 60 is shown supports bearings 62 for the fan
drive or low pressure turbine 46. It should be understood that the
teachings of this disclosure would extend to a three turbine rotor
engine wherein a dedicated turbine rotor drives the fan, such as
through gear reduction 48.
[0015] Gas turbine engine 20 in one example is a high-bypass geared
aircraft engine. In a further example, the bypass ratio for gas
turbine engine 20 is greater than about six, with an example
embodiment being greater than about ten. The geared architecture 48
can be an epicyclic gear train, such as a planetary gear system or
other gear system, with a gear reduction ratio of greater than
about 2.3, and low pressure turbine 46 can have a pressure ratio
that is greater than about five. In one disclosed embodiment, the
bypass ratio of gas turbine engine 20 is greater than about ten
(i.e., 10:1), the fan diameter is significantly larger than that of
low pressure compressor 44, and low pressure turbine 46 has a
pressure ratio that is greater than about five (i.e., 5:1). The
pressure ratio of low pressure turbine 46 is pressure measured
prior to the inlet of low pressure turbine 46 relative to the
pressure measured at the outlet of low pressure turbine 46 prior to
an exhaust nozzle. Geared architecture 48 may be an epicycle gear
train, such as a planetary gear system or other gear system, with a
gear reduction ratio of greater than about 2.3:1. It should be
understood, however, that the above parameters are only exemplary
of one embodiment of a geared architecture engine and that the
present invention is applicable to other gas turbine engines
including direct drive turbofans.
[0016] FIG. 2A is a cross-sectional view of seal assembly 64
including seal plate 68, and FIG. 2B is a perspective view of the
seal plate in FIG. 2A (with a portion enlarged). Seal assembly 64
can be adjacent to, incorporated in, or encompassing any of bearing
systems 38, bearing compartment 60, and/or support bearings 62
shown in FIG. 1. Seal assembly 64 includes seal element 66 with
first seal surface 67, seal plate 68, and lubricant nozzle 70. Also
shown in FIG. 2A are bearing 72 and shaft 74 (which can be one of
inner shaft 40 and outer shaft 50, with momentary reference to FIG.
1). Seal plate 68 includes first axial end 76, second axial end 78,
and seal body 80 with second seal surface 81 at first axial end 76
and angled surface 90 on a radially outward side. Seal plate 68
also includes slinger ring 82 with tabs 84 separated by slots 86 of
FIG. 2B, groove 88 between seal body 80 and slinger ring 82, neck
92, and front edge 94 of FIG. 2B.
[0017] Seal assembly 64 has the same functionality as other seal
assemblies (hydrodynamic seals) known in the art. Seal assembly 64
is substantially annular about centerline A, and can be centered
about shaft 74, which in turn can be inner shaft 40 or outer shaft
50 of gas turbine engine 20, with momentary reference to FIG.
1.
[0018] Seal element 66 of seal assembly 64 is
stationary/nonrotating, annular, and centered about centerline A.
Seal element 66 functions to ensure first seal surface 67 is
adjacent to second seal surface 81 of seal plate 68 (with,
potentially, a fluid (e.g., air) therebetween to form a seal when
seal assembly 64 is functioning properly). The configuration and
functionality of seal element 66 is known to one of ordinary skill
in the art, and the disclosed seal element 66 is only one exemplary
embodiment. Seal element 66 can include other components not
expressly labeled in FIG. 2A, such as a housing, resilient member
(e.g., spring), and carrier. The entirety of or a portion of seal
element 66 can be made from carbon to provide structural strength
and the necessary sealing capabilities.
[0019] First sealing surface 67 provides a seal between seal
element 66 and seal plate 68. First sealing surface 67 is annular
in shape and can have a square or rectangular cross section (or
another shape) when viewed circumferentially as shown in FIG. 2A.
First sealing surface 67 can be made from a variety of materials,
including carbon, metal, or a composite material, but should be
constructed from a material that allows fluid (such as air) to form
a fluid bearing/seal between first sealing surface 67 and second
sealing surface 81 of seal plate 68 to establish a tight seal.
First sealing surface 67 can be coated with a material and/or have
a desired surface topography that allows for a sufficient sealing
surface and promotes air or another fluid to establish a tight
seal.
[0020] Seal plate 68 is in an axially rearward direction from seal
element 66 (though other embodiments can have seal plate 68 axially
forward of seal element 66) such that first axial end 76 of seal
plate 68 is at least partially adjacent to seal element 66 (i.e.,
second seal surface 81 is adjacent to first sealing surface 67).
Seal plate 68 is annular in shape and rotatable about centerline A.
Seal plate 68 can be connected at a radially inner side to shaft
74, and seal plate 68 can include additional features on a radially
inward side to attach seal plate 68 to shaft 74 or another
component. Further, seal plate 68 can be connected to a rotating
member through other configurations, such as on first axial end 76,
second axial end 78, and/or an axially forward extending arm. While
shown as having seal body 80, slinger ring 82, and groove 88
therebetween, seal plate 68 can have other configurations that
function to work in conjunction with seal element 66 to form a seal
(e.g., a hydrodynamic seal). Seal plate 68 can be constructed from
multiple pieces that are fastened together, or seal plate 68 can be
one continuous and monolithic component that is formed or molded
during one process. In the disclosed embodiments, shaft 74 is
radially inward from and coupled to seal plate 68 of seal assembly
64 such that seal plate 68 and shaft 74 rotate in unison.
[0021] Seal body 80 is annular in shape and forms a hydrodynamic
seal with seal element 66 at second seal surface 81. While seal
body 80 is shown in FIGS. 2A and 2B as having a substantially
rectangular cross-sectional shape, seal body 80 can have any
cross-sectional shape configured to seal with seal element 66. Seal
body 80 can have angled surface 90 on a radially outward side of
seal body 80 adjacent groove 88 to aid lubricant in being directed
from lubricant nozzle 70 into groove 88. Seal body 80 can include
other features not expressly disclosed to aid in providing sealing
with seal element 66 while also allowing for lubricant to cool seal
plate 68. For example, seal body 80 can include channels or other
features that extend from the radially outward side of seal body 80
to groove 88 to allow lubricant to flow from lubricant nozzle 70
into groove 88.
[0022] Similar to first seal surface 67, second seal surface 81
provides a seal between seal element 66 and seal plate 68. Second
seal surface 81 can be a dedicated component on seal body 80 (like
the rectangular cross-sectional shape of first seal surface 67) or
can just be a flat surface on first axial end 76 of seal plate 68.
Second seal surface 81 can be made from a variety of materials,
including carbon, metal, or a composite material, but should be
constructed from a material that allows fluid (such as air) to form
a fluid bearing/seal between second sealing surface 81 and first
sealing surface 67 of seal element 66 to establish a tight seal.
Second sealing surface 81 can be coated with a material and/or have
a desired surface topography that allows for a sufficient sealing
surface and promotes air or another fluid establish a tight
seal.
[0023] Slinger ring 82 is at second axial end 78 of seal plate 68
and is axially rearward of seal body 80 (though other embodiments
can have slinger ring 82 axially forward of seal body 80). Slinger
ring 82 has radially extending tabs 84 separated by slots 86.
Slinger ring 82 is annular in shape and is attached to seal body 80
by neck 92, which is radially inward from groove 88 (which in turn
is axially between seal body 80 and slinger ring 82). Neck 92 can
be as thin or thick as necessary for structural strength and/or to
form a depth of groove 88 that provides sufficient cooling to seal
plate 68. For example, the depth of groove 88 can be greater than
one-half the height of seal body 80 (and, therefore, the thickness
of neck 92 can be less than one-half the height of seal body 80).
Slinger ring 82 can extend entirely radially outward, or other
embodiments can include a slinger ring that is angled partially
axially forward (i.e., to the left in FIG. 2A) and/or rearward
(i.e., to the right in FIG. 2A) to partially enclose groove 88 or
widen groove 88 depending on the cooling needs of seal plate 68.
Slinger ring 82 can include other features not expressly disclosed
to provide sufficient cooling to seal plate 68, such as fins or
other features extending into groove 88 and/or channels extending
through tabs 84. As discussed below and in regards to the
embodiments in FIGS. 3 and 4, tabs 84 and corresponding slots 86
can be configured to provide additional cooling and direct
lubricant in various directions.
[0024] As shown in FIG. 2B, tabs 84 are radially outward extending
projections that are circumferentially separated by slots 86.
Slinger ring 82 can have any number of tabs 84 separated by
corresponding slots 86, which as a slinger ring that includes at
least ten tabs 84. In FIG. 2B, slinger ring 82 includes fifteen
tabs 84 (and fifteen slots 86). Tabs 84 can have the same axial
thickness as a portion of slinger ring 82 radially inward from tabs
84, or tabs 84 can have a different axial thickness from the rest
of slinger ring 82 and/or adjacent tabs 84. Tabs 84 can have a
variety of shapes and/or configurations, including those disclosed
in the exemplary embodiments set out in FIGS. 2B, 3, and 4. In FIG.
2B, tabs 84 are rectangular in shape with front edge 94 (the edge
facing direction of rotation R) that extends entirely in the radial
direction. Additionally, front edge 94 in FIG. 2B is straight such
that front edge 94 is perpendicular to direction of rotation R
(i.e., front edge 94 is not beveled or otherwise angled in the
axial direction). Front edge 94 extending entirely in the radial
direction and perpendicular to direction of rotation R directs
lubricant into groove 88 to cool seal plate 68. Further, tabs 84
can have the same or different circumferential lengths and widths
than adjacent tabs 84 and can have any circumferential length
necessary to direct lubricant into grooves 88 and provide cooling
to seal plate 68 (i.e., tabs 84 can have any circumferential
length, spacing, and variations as is necessary to direct lubricant
into grooves 88). Tabs 84 direct lubricant at least partially
radially inward into groove 88 to cool seal plate 68 and at least
partially circumferentially in direction of rotation R of seal
plate 68 to cool seal body 80. Tabs 84 can be configured to provide
laminar or turbulent flow of the lubricant within groove 88 to
provide sufficient cooling. Tabs 84 can have a straight radially
outer edge or a curved radially outer edge to match that of seal
body 80. Further, tabs 84 can have other configurations of the
radially outer edge, such as a radially outer edge that has waves,
stair-steps, or another configuration.
[0025] Slots 86 circumferentially separate tabs 84 and can be as
circumferentially wide or narrow as necessary. Slots 86 can have a
depth that is consistent in the circumferential direction and/or
among adjacent slots 86, or slots 86 can have a varying depth in
the circumferential direction of each slot 86 and/or among adjacent
slots 86. Additionally, slots 86 can extend radially inward all the
way to neck 92, or slots 86 can extend only a portion of the
distance to neck 92. For example, as shown in FIG. 2A, a height of
slots 86 (and therefore tabs 84) are approximately equal to
one-half the total depth of groove 88 with the total depth of
groove 88 being a distance from a radially outward side of seal
body 80/slinger ring 82 to a bottom of groove 88.
[0026] Groove 88 is located between seal body 80 and slinger ring
82. Groove 88 is annular in shape and can extend only partially
circumferentially around seal plate 68 or entirely
circumferentially around seal plate 68. Groove 88 provides a void
into which lubricant can be directed and flow within to cool seal
plate 68. Groove 88 can have a consistent circumferential
cross-section shape (as shown, groove 88 has a rectangular
cross-sectional shape with a rounded bottom), or the
circumferential cross-sectional shape can be varying. For example,
groove 88 can be narrower at one circumferential location than at
another and/or narrower at one radial location than at another
radial location. Further, groove 88 can undulate in the axial
direction or otherwise vary in axial distance from second axial end
78 depending on the structural strength and cooling needs of seal
plate 68. Groove 88 can have any depth necessary to provide
sufficient cooling to seal plate 68, and the depth of groove 88 can
vary in the circumferential direction. For example, grooves can be
configured such that a depth of groove 88 (i.e., the distance from
a radially outer end of seal body 80 to a bottom of groove 88) is
greater than one-half a height of seal body 80/slinger ring 82.
[0027] Lubricant nozzle 70 of FIG. 2A is configured to direct
lubricant towards seal plate 68. Lubricant nozzle 70 is, due to
space limitations surrounding sealing assembly 64, radially outward
from seal plate 68 and can be angled axially rearward such that
lubricant is directed at least partially in a radially inward
direction and partially in an axial direction. Further, lubricant
nozzle 70 can also be angled in a circumferential direction such
that lubricant is directed at least partially into or away from
direction of rotation R of seal plate 68. In prior art
configurations, lubricant nozzle 70 is located axially rearward of
seal plate 68 and directs lubricant either radially inward so that
lubricant can flow through shaft 74 and then through seal plate 68
through channels within seal plate 68, or can direct lubricant
axially forward so that lubricant contacts second axial end 78 of
seal plate 68. However, in sealing element 64 of the present
disclosure, bearing 72 prevents lubricant nozzle 70 from being
located axially rearward of seal plate 68, and other components
prevent lubricant from being directed through shaft 74. Thus,
lubricant nozzle 70 is forced to be located radially outward from
seal plate 68.
[0028] As disclosed above, lubricant nozzle 70 functions in
conjunction with slinger ring 82 (tabs 84 and slots 86) to direct
lubricant into groove 88 to provide cooling to seal plate 68 and to
direct lubricant in direction of rotation R. Tabs 84 can have
varying configurations to direct lubricant radially inward, axially
rearward, and/or circumferentially in direction of rotation R.
[0029] FIG. 3 is a perspective view of a second embodiment of a
seal plate (with a portion enlarged). Seal plate 168 is similar to
seal plate 68 of FIGS. 2A and 2B except that seal plate 168
includes tabs 184 (and corresponding slots 186) that have a
different shape. As shown in FIG. 3, seal plate 168 includes first
axial end 176, second axial end 178, seal body 180 (having a second
seal surface (not shown, but similar to second sealing surface 81
of FIG. 2A) and angled surface 190), slinger ring 182 (having tabs
184, slots 186, and a neck (not shown, but similar to neck 92 of
FIG. 2A)), and groove 188. Tabs 184 include front edge 194.
[0030] Tabs 184 of seal plate 168 have front edge 194 facing
direction of rotation R of seal plate 168 that is angled in the
radial direction towards direction of rotation R (i.e., front edge
194 of tabs 184 is angled circumferentially towards direction of
rotation R as front edge 194 extends radially outward). As such,
tabs 184 have a substantially trapezoidal shape when viewed in the
axial direction. However, a rear edge of tabs 184 can extend
entirely in the radial direction (i.e., extend straight outward) or
can also be angled. As shown in FIG. 3, front edge 194 is
perpendicular to direction of rotation R (i.e., front edge 94 is
not beveled or otherwise angled in the axial direction). With tabs
184 having front edge 194 that is angled in the radial direction
while not being angled/beveled in the axial direction, lubricant
contacting tabs 184 and front edge 194 is directed more radially
inward into groove 188 than tabs 84 of seal plate 68.
[0031] FIG. 4 is a perspective view of a third embodiment of a seal
plate (with a portion enlarged). Seal plate 268 is similar to seal
plate 68 of FIGS. 2A and 2B except that seal plate 268 includes
tabs 284 (and corresponding slots 286) that have a different shape.
As shown in FIG. 4, seal plate 268 includes first axial end 276,
second axial end 278, seal body 280 (having a second seal surface
(not shown, but similar to second sealing surface 81) and angled
surface 290), slinger ring 282 (having tabs 284, slots 286, and a
neck (not shown, but similar to neck 92 of FIG. 2A)), and groove
288. Tabs 284 include front edge 294
[0032] Tabs 284 of seal plate 268 have front edge 294 facing
direction of rotation R of seal plate 268 that is both angled in
the radial direction towards direction of rotation R (i.e., front
edge 294 of tabs 284 is angled circumferentially towards direction
of rotation R as front edge 294 extends radially outward) as well
as being beveled toward seal body 280 (i.e., front edge 294 of tabs
284 is angled in the axial direction towards seal body 280). Front
edge 294 being beveled toward seal body 280 is in contrast to tabs
84 and 184 of FIGS. 2B and 3 respectively, which have an angle that
is perpendicular to direction of rotation R. With tabs 284 having
front edge 294 that is angled in the radial direction and also
angled/beveled in the axial direction, lubricant contacting tabs
284 and front edge 294 is directed more radially inward into groove
288 and more in direction of rotation R than tabs 84 of seal plate
68 and tabs 184 of seal plate 168 of FIGS. 2B and 3
respectively.
[0033] Tabs 84 in FIG. 2A and 2B, tabs 184 in FIG. 3, and tabs 284
in FIG. 4 provide differing amounts of cooling by directing
differing amounts of lubricant radially inward and
circumferentially in direction of rotation R. However, tabs 84,
184, and 284 require differing amount of manufacturing time and
expense. Thus, the configuration of the tabs can be selected
depending on the cooling needs for seal plate 68/168/268 and the
amount of manufacturing time/expense allowed.
[0034] Seal plate 68/168/268 of seal assembly 64 is disclosed
herein that includes slinger ring 82/182/282 that directs lubricant
(introduced by lubricant nozzle 70 at a location radially outward
from seal plate 68/168/268) radially inward into groove 88/188/288
and circumferentially in direction of rotation R. Slinger ring
82/182/282 in conjunction with the lubricant provides improved
cooling to seal plate 68/168/268. Slinger ring 82/182/282 includes
a plurality of tabs 84/184/284 (separated by slots 86/186/286)
having various configurations for directing the lubricant more in a
radially inward direction and/or more in a circumferential
direction. Because of space limitations surrounding seal plate
68/168/268, lubricant nozzle 70 is located radially outward from
seal plate 68/168/268, and thus the lubricant is directed from a
location radially outward from seal plate 68/168/268 at least
partially radially inward and at least partially axially rearward
towards slinger ring 82/182/282. Slinger ring 82/182/282 functions
to direct/alter the flow of lubricant to provide efficient cooling
of seal plate 68/168/268.
[0035] Discussion of Possible Embodiments
[0036] The following are non-exclusive descriptions of possible
embodiments of the present invention.
[0037] A seal plate is disclosed herein that is annular in shape
and configured to rotate about a centerline. The seal plate
includes a seal body having a first axial end forming a sealing
surface and a second axial end opposite the first axial end, a
slinger ring axially rearward of the seal body and having a
plurality of radially extending tabs separated by a plurality of
slots, and a groove between the seal body and the slinger ring. The
tabs on the slinger ring are configured to direct lubricant at
least partially radially inward into the groove and at least
partially in a direction of rotation of the seal plate to cool the
seal body.
[0038] The seal plate of the preceding paragraph can optionally
include, additionally and/or alternatively, any one or more of the
following features, configurations and/or additional elements.
[0039] The plurality of tabs are each rectangular in shape.
[0040] The plurality of tabs each have a front edge facing the
direction of rotation of the seal plate that is angled in a radial
direction towards the direction of rotation.
[0041] The plurality of tabs each have a front edge facing the
direction of rotation that is beveled towards the seal body.
[0042] The plurality of tabs each have a front edge facing the
direction of rotation that is perpendicular to the direction of
rotation.
[0043] A radial depth of the groove is greater than a radial height
of each of the plurality of tabs.
[0044] The seal body has an angled surface on a radially outward
side adjacent the groove.
[0045] The plurality of tabs includes at least ten tabs.
[0046] A depth of the groove is greater than one-half a height of
the seal body.
[0047] A seal assembly centered about a centerline includes a
sealing element, a seal plate, and a lubricant nozzle. The sealing
element is annular and nonrotating and has a first sealing surface
on one axial end. The seal plate is annular and configured to
rotate about the centerline. The seal plate includes a seal body
having a second sealing surface on a first axial end that is
configured to form a seal with the first sealing surface of the
sealing element and a second axial end opposite the first axial
end, a slinger ring that is adjacent the second axial end of the
seal body and has a plurality of radially extending tabs
circumferentially separated by a plurality of slots, and a groove
between the seal body and the slinger ring. The lubricant nozzle is
radially outward from the seal plate and configured to direct
lubricant at the seal plate. The tabs of the seal plate are
configured to direct lubricant at least partially radially inward
into the groove and at least partially in a direction of rotation
of the seal plate to cool the seal body.
[0048] The seal assembly of the preceding paragraph can optionally
include, additionally and/or alternatively, any one or more of the
following features, configurations and/or additional elements.
[0049] The lubricant nozzle is angled to direct lubricant partially
in a radially inward direction and partially in an axial
direction.
[0050] The lubricant nozzle is angled to direct lubricant partially
in the direction of rotation of the seal plate.
[0051] A shaft radially inward from and coupled to the seal plate
such that the seal plate and the shaft rotate in unison.
[0052] The plurality of tabs of the seal plate are each rectangular
in shape.
[0053] The plurality of tabs of the seal plate each have a front
edge facing the direction of rotation that is angled in a radial
direction towards the direction of rotation.
[0054] The plurality of tabs of the seal plate each have a front
edge facing the direction of rotation that is beveled towards the
seal body.
[0055] The plurality of tabs of the seal plate each have a front
edge facing the direction of rotation that is perpendicular to the
direction of rotation. The seal body has an angled notch on a
radially outward side adjacent the groove.
[0056] The sealing element is constructed substantially from
carbon.
[0057] A gas turbine engine comprising the above seal assembly.
[0058] 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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