Patent Publication Number: US-2020300122-A1

Title: Seal plate lubricant slinger

Description:
BACKGROUND 
     The present disclosure relates to hydrodynamic seal assemblies and, more particularly, to cooling features in a hydrodynamic seal plate. 
     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 
     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. 
     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 
         FIG. 1  is a partial cross-sectional view of a gas turbine engine. 
         FIG. 2A  is a cross-sectional view of a seal assembly including a seal plate. 
         FIG. 2B  is a perspective view of the seal plate in  FIG. 2A . 
         FIG. 3  is a perspective view of a second embodiment of a seal plate. 
         FIG. 4  is a perspective view of a third embodiment of a seal plate. 
     
    
    
     DETAILED DESCRIPTION 
     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. 
       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. 
     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. 
     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. 
     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 . 
     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. 
       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 . 
     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 . 
     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. 
     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. 
     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. 
     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 . 
     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. 
     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. 
     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. 
     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 . 
     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 . 
     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 . 
     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. 
       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 . 
     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 . 
       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   
     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. 
     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. 
     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 . 
     Discussion of Possible Embodiments 
     The following are non-exclusive descriptions of possible embodiments of the present invention. 
     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. 
     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. 
     The plurality of tabs are each rectangular in shape. 
     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. 
     The plurality of tabs each have a front edge facing the direction of rotation that is beveled towards the seal body. 
     The plurality of tabs each have a front edge facing the direction of rotation that is perpendicular to the direction of rotation. 
     A radial depth of the groove is greater than a radial height of each of the plurality of tabs. 
     The seal body has an angled surface on a radially outward side adjacent the groove. 
     The plurality of tabs includes at least ten tabs. 
     A depth of the groove is greater than one-half a height of the seal body. 
     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. 
     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. 
     The lubricant nozzle is angled to direct lubricant partially in a radially inward direction and partially in an axial direction. 
     The lubricant nozzle is angled to direct lubricant partially in the direction of rotation of the seal plate. 
     A shaft radially inward from and coupled to the seal plate such that the seal plate and the shaft rotate in unison. 
     The plurality of tabs of the seal plate are each rectangular in shape. 
     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. 
     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. 
     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. 
     The sealing element is constructed substantially from carbon. 
     A gas turbine engine comprising the above seal assembly. 
     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.