Patent Publication Number: US-10774670-B2

Title: Filled abradable seal component and associated methods thereof

Description:
BACKGROUND 
     Embodiments of the disclosed technique relate to turbomachines, and more specifically to a filled abradable seal component, an associated method of manufacturing, the turbomachines including the filled abradable seal component, and regulating windage heating in turbomachines. 
     Seals are often used to minimize leakage of fluid in a clearance defined between a stationary component and a rotatable component of a turbomachine. Typically, seal includes teeth formed on the rotatable component thereby obstructing a flow of the fluid and minimizing the leakage of the fluid through the clearance. However, during certain transient operational conditions of the turbomachine such as startup, the rotatable component may move along an axial direction or a radial direction in relation to the stationary component. Such movement of the rotatable component may cause the teeth to rub against the stationary component, resulting in damage of the teeth and the stationary component. To address such problems, in the art, an abradable honeycomb seal component including a plurality of honeycomb cells is coupled to the stationary component. Thus, during such movement of the rotatable component, the teeth may rub against the abradable honeycomb seal component, without damaging the teeth and the stationary component. However, the plurality of honeycomb cells in the abradable honeycomb seal component may entrap some portion of the fluid, resulting in losing swirling motion of the fluid along the clearance and increasing tangential slip between the fluid and the rotatable component, thereby increasing windage heating along the clearance. Accordingly, there is a need for an improved abradable seal component, an associated method for manufacturing the improved abradable seal component, and regulating windage heating of fluid in a clearance of a turbomachine. 
     BRIEF DESCRIPTION 
     In accordance with one example embodiment, a method of manufacturing a filled abradable seal component for a turbomachine is disclosed. The method includes positioning an abradable seal component including a plurality of honeycomb cells. Further, the method includes applying a filler material on the abradable seal component to fill the plurality of honeycomb cells. The filler material includes an abradable material, a binder material, and a fluid catalyst. The abradable material includes at least one of nickel chromium aluminum-bentonite, cobalt nickel chromium aluminum yttrium-polyester, cobalt nickel chromium aluminum yttrium-boron nitride, aluminum silicon-bentonite, aluminum bronze-polyester, nickel graphite, or aluminum silicon-boron nitride. The binder material includes at least one of aluminum, nickel-aluminum, aluminum thiophosphate, or aluminum thiosulfate. The fluid catalyst includes a solvent having hydroxyl groups. The method further includes curing the filler material within the plurality of honeycomb cells at a temperature below 250 degrees Celsius to produce the filled abradable seal component. 
     In accordance with another example embodiment, a filled abradable seal component for a turbomachine is disclosed. The abradable seal component includes a plurality of honeycomb cells filled with a filler material, where the filler material is bonded to one or more side walls of the plurality of honeycomb cells. The filler material includes an abradable material, a binder material, and a fluid catalyst. The abradable material includes at least one of nickel chromium aluminum-bentonite, cobalt nickel chromium aluminum yttrium-polyester, cobalt nickel chromium aluminum yttrium-boron nitride, aluminum silicon-bentonite, aluminum bronze-polyester, nickel graphite, or aluminum silicon-boron nitride. The binder material includes at least one of aluminum, nickel-aluminum, aluminum thiophosphate, or aluminum thiosulfate. The fluid catalyst includes a solvent having hydroxyl groups. 
     In accordance with yet another example embodiment, a turbomachine is disclosed. The turbomachine includes a stationary component, a rotatable component, and a filled abradable seal component. The filled abradable seal component is coupled to either one of the stationary component or the rotatable component of the turbomachine and facing teeth of other of the stationary component or the rotatable component to define a clearance there between the filled abradable seal component and the other of the stationary component or the rotatable component. The filled abradable seal component includes an abradable seal component including a plurality of honeycomb cells filled with a filler material. The filler material is bonded to one or more side walls of the plurality of honeycomb cells. The filler material includes an abradable material, a binder material, and a fluid catalyst. The abradable material includes at least one of nickel chromium aluminum-bentonite, cobalt nickel chromium aluminum yttrium-polyester, cobalt nickel chromium aluminum yttrium-boron nitride, aluminum silicon-bentonite, aluminum bronze-polyester, nickel graphite, or aluminum silicon-boron nitride. The binder material includes at least one of aluminum, nickel-aluminum, aluminum thiophosphate, or aluminum thiosulfate. The fluid catalyst includes a solvent having hydroxyl groups. 
    
    
     
       DRAWINGS 
       These and other features and aspects of embodiments of the present disclosure will become better understood when the following detailed description is read with reference to the accompanying drawings in which like characters represent like parts throughout the drawings, wherein: 
         FIG. 1  is a cross-sectional view of a portion of a turbomachine in accordance with one example embodiment of the present disclosure. 
         FIG. 2  is a cross-sectional view of another portion of the turbomachine of  FIG. 1  in accordance with one example embodiment of the present disclosure. 
         FIG. 3  is a flow diagram of a method of manufacturing a filled abradable seal component in accordance with one example embodiment of the present disclosure. 
         FIG. 4  is a flow diagram of a method for regulating windage heating in a turbomachine in accordance with one example embodiment of the present disclosure. 
         FIG. 5  is a perspective view of a filled abradable seal component in accordance with one example embodiment of the present disclosure. 
         FIG. 6  is a perspective view of a filled abradable seal component in accordance with another example embodiment of the present disclosure. 
         FIG. 7  is a perspective view of a filled abradable seal component including a plurality of grooves in accordance with one example embodiment of the present disclosure. 
         FIG. 8  is a schematic diagram of a filled abradable seal component including a plurality of grooves in accordance with another example embodiment of the present disclosure. 
         FIG. 9  is a schematic diagram of a filled abradable seal component coupled to a stationary component, and facing a rotatable component of a turbomachine in accordance with one example embodiment of the present disclosure. 
         FIG. 10  is a schematic diagram of a filled abradable seal component coupled to a rotatable component, and facing a stationary component of a turbomachine in accordance with another example embodiment of the present disclosure. 
     
    
    
     DETAILED DESCRIPTION 
     To more clearly and concisely describe and point out the subject matter, the following definitions are provided for specific terms, which are used throughout the following description and the appended claims, unless specifically denoted otherwise with respect to a particular embodiment. The term “melting point” as used in the context refers to liquefaction point of a material. Specifically, the melting point of the material refers to a temperature at which the material changes its physical state from solid to liquid, at atmospheric pressure. The term “solvent” as used in the context refers to a substance that is used to dissolve two materials. The term “hydroxyl groups” as used in the context refers to the chemical moiety “—OH”. 
     Embodiments of the present disclosure discussed herein relate to a method of manufacturing a filled abradable seal component. In some embodiments, such a filled abradable seal component may be used to regulate windage heating in a turbomachine. In certain embodiments, the method includes positioning an abradable seal component including a plurality of honeycomb cells. Further, the method includes applying a filler material on the abradable seal component to fill the plurality of honeycomb cells. The method further includes curing the filler material within the plurality of honeycomb cells at a temperature below 250 degrees Celsius to produce the filled abradable seal component. In some embodiments, the filler material includes an abradable material, a binder material, and a fluid catalyst. In some embodiments, the abradable material includes at least one of nickel chromium aluminum-bentonite, cobalt nickel chromium aluminum yttrium-polyester, cobalt nickel chromium aluminum yttrium-boron nitride, aluminum silicon-bentonite, aluminum bronze-polyester, nickel graphite, or aluminum silicon-boron nitride. The binder material includes at least one of aluminum, nickel-aluminum, aluminum thiophosphate, or aluminum thiosulfate. The fluid catalyst includes a solvent having hydroxyl groups. In some specific embodiments, the fluid catalyst is water. In certain embodiments, the curing of the filler material within the plurality of honeycomb cells is performed below a melting point of the filler material. 
     In some embodiments, applying the filler material includes i) mixing the abradable material and the binder material to produce a mixture, ii) filling the mixture in the plurality of honeycomb cells, and iii) providing the fluid catalyst to the mixture filled in the plurality of honeycomb cells. In some embodiments, a volume ratio of the abradable material to the binder material in the filler material to produce the mixture is in a range from 0.5 to 3. In certain embodiments, filling the mixture includes transferring the mixture into the plurality of honeycomb cells to fill the honeycomb cells. In some embodiments, providing the fluid catalyst includes spraying or wetting the fluid catalyst (e.g., water or alcohol) on the mixture filled in the plurality of honeycomb cells. The fluid catalyst initiates reaction of the mixture to produce a reacted mixture and bond the reacted mixture to one or more side walls of the plurality of honeycomb cells. In some other embodiments, providing the fluid catalyst includes disposing the abradable seal component having the mixture filled in the plurality of honeycomb cells over a pack of ice. In such an embodiment, the pack of ice may allow condensation of water (i.e., the fluid catalyst) on the mixture from atmosphere. Upon contacting with the mixture, water, initiates a chemical reaction of the mixture to form a reacted mixture and facilitates the bonding of the reacted mixture to one or more side walls of the plurality of honeycomb cells. In such an embodiment, curing the filler material includes disposing the abradable seal component including the plurality of filled honeycomb cells in a heater such as oven to remove excess water from the mixture, and produce the filled abradable seal component. 
     In one example embodiment, the abradable material is nickel chromium aluminum-bentonite, the binder material is aluminum, and the fluid catalyst is water. In some embodiments, a volume ratio of the nickel chromium aluminum-bentonite to the aluminum in the filler material to produce the mixture is in a range from 0.5 to 3. In some other embodiments, a volume ratio of the nickel chromium aluminum-bentonite to the aluminum in the filler material to produce the mixture is in a range from 0.7 to 2. In one example embodiment, the volume ratio of the nickel chromium aluminum-bentonite to the aluminum in the filler material to produce the mixture is 1. In some embodiments, the curing the filler material including nickel chromium aluminum-bentonite, aluminum and water in the plurality of honeycomb cells is performed at a temperature below 250 degrees Celsius at atmospheric pressure to produce the filled abradable seal component. In some other embodiment, the curing is performed below 100 degrees Celsius. In some example embodiment, the curing is performed below 50 degrees Celsius. Further, in such embodiment, curing is performed at a room temperature. For example, the room temperature is in a range from 20 degrees Celsius to 30 degrees Celsius. In some specific examples, the room temperature is in a range from 20 degrees Celsius to 30 degrees Celsius at atmospheric pressure. 
     In some other embodiments, applying the filler material includes i) mixing the abradable material and the binder material to produce a mixture, ii) mixing the fluid catalyst with the mixture to produce a slurry, and iii) filling the slurry in the plurality of honeycomb cells. In one embodiment, the steps (i) and (ii) are performed simultaneously. In another embodiment, the steps (i) and (ii) are performed sequentially. In some embodiments, filling the slurry includes pouring the slurry into the plurality of honeycomb cells to fill the plurality of honeycomb cells. In some other embodiments, filling the slurry includes dipping the abradable seal component in the slurry of filler material to fill the plurality of honeycomb cells. 
       FIG. 1  illustrates a cross-sectional view of a portion of a turbomachine such as a gas turbine engine  10  in accordance with one example embodiment. The gas turbine engine  10  includes a compressor  12 , a combustor  14 , and a turbine  16 . In the illustrated embodiment, the compressor  12  is a multistage compressor and the turbine  16  is a multistage turbine. The compressor  12  is coupled to the combustor  14 . The turbine  16  is coupled to the combustor  14  and the compressor  12 . A leakage flow path  26  extends from the compressor  12  to the turbine  16  bypassing the combustor  14 . During operation, the compressor  12  is configured to receive a fluid  11 , such as air and compress the received fluid  11  to generate a compressed fluid  13 , which typically has a swirling motion. The combustor  14  is configured to receive a main compressed fluid  15  from the compressor  12  and a fuel  17 , such as natural gas, from a plurality of fuel injectors  18  and burn the fuel  17  and the main compressed fluid  15  within a combustion zone  22  to generate exhaust gases  19 . The turbine  16  is configured to receive the exhaust gases  19  from the combustor  14  and expand the exhaust gases  19  to convert energy of the exhaust gases  19  to work. The turbine  16  is configured to drive the compressor  12  through a mid-shaft  82 . It should be noted herein that the term “main compressed fluid” as used in the context refers to a major portion or fraction of the compressed fluid  13  discharged from the compressor  12 . In some embodiments, the major portion means more than 80 percent. The compressor  12  is further configured to release a bypass compressed fluid  23  to the turbine  16  via the leakage flow path  26 . The terms “bypass compressed fluid” as used in the context refers to a minor portion or fraction of the compressed fluid  13  discharged from the compressor  12 . In some embodiments, the minor portion means less than 20 percent. 
     In the illustrated embodiment, the turbine  16  includes four-stages represented by four rotors  38 ,  40 ,  42 ,  44  connected to the mid-shaft  82  for rotation therewith. Each rotor  38 ,  40 ,  42 ,  44  includes airfoils such as rotor blades  46 ,  48 ,  50 ,  52 , which are arranged alternately between nozzles such as stator blades  54 ,  56 ,  58 ,  60  respectively. The stator blades  54 ,  56 ,  58 ,  60  are fixed to a turbine casing  70  of the turbine  16 . The turbine  16  further includes three spacer wheels  62 ,  64 ,  66  coupled to and disposed alternately between rotors  38 ,  40 ,  42 ,  44 . Specifically, the turbine  16  includes a first stage having the stator blade  54  and the rotor blade  46 , a second stage having the stator blade  56 , the spacer wheel  62 , and the rotor blade  48 , a third stage having the stator blade  58 , the spacer wheel  64 , and the rotor blade  50 , and a fourth stage having the stator blade  60 , the spacer wheel  66 , and the rotor blade  52 . 
     The gas turbine engine  10  further includes a stationary component such as a compressor discharge casing  80 , a rotatable component such as the mid-shaft  82 , and a filled abradable seal component  68 . In such an embodiment, the filled abradable seal component  68  is disposed in the leakage flow path  26 . Specifically, the filled abradable seal component  68  is coupled to the compressor discharge casing  80  facing the mid-shaft  82  having teeth  84  to define a clearance  21  there between the compressor discharge casing  80  and the mid-shaft  82 . Specifically, the clearance  21  is defined between the compressor discharge casing  80  and the mid-shaft  82 . In some embodiments, the filled abradable seal component  68  includes a plurality of honeycomb cells (not shown) filled with a filler material (not shown), which is bonded to one or more side walls of the plurality of honeycomb cells. Further, the filled abradable seal component  68  may include a plurality of grooves (not shown), where individual grooves of the plurality of grooves may be spaced apart from each other along the axial direction  90  of the gas turbine engine  10 . During operation, the filled abradable seal component  68  is configured to regulate windage heating along the clearance  21 . Further, the plurality of grooves is configured to control leakage of a bypass compressed fluid  23  flowing through the clearance  21 . The filled abradable seal component  68  is discussed in greater detail below with reference to subsequent figures. 
     The gas turbine engine  10  further includes a stationary component such as the turbine casing  70 , a rotatable component such as the rotor blade  50 , and a filled abradable seal component  94 . In such an embodiment, the filled abradable seal component  94  is coupled to the turbine casing  70  facing teeth  96  at a tip  99  of the rotor blade  50  to define a clearance  25  there between the tip  99  of the rotor blade  50  and the turbine casing  70 . The filled abradable seal component  94  may be similar to the filled abradable seal component  68 . In such an embodiment, the filled abradable seal component  94  is configured to regulate windage heating along the clearance  25  and to control leakage of the exhaust gases  19  through the clearance  25 , bypassing the rotor blade  50 . Although not illustrated, in certain embodiments, the filled abradable seal component  94  may be coupled to the turbine casing  70  facing teeth (not labeled) of respective rotor blades  46 ,  48 ,  52  to define a clearance (not labeled) there between the respective rotor blades  46 ,  48 ,  52  and the turbine casing  70 . 
     The gas turbine engine  10  further includes a stationary component such as the stator blade  56 , a rotatable component such as the spacer wheel  62 , and a filled abradable seal component  98 . In such an embodiment, the filled abradable seal component  98  is coupled to a tip  55  of the stator blade  56  facing teeth  100  in the spacer wheel  62  to define a clearance  27  there between the tip  55  of the stator blade  56  and the spacer wheel  62 . The filled abradable seal component  98  may be similar to the filled abradable seal component  68 . In such an embodiment, the filled abradable seal component  98  is configured to regulate windage heating along the clearance  27  and to control leakage of the exhaust gases  19  through the clearance  27 . Although not illustrated, the filled abradable seal component  98  may be coupled to the tip (not labeled) of the respective stator blades  58 ,  60  facing teeth (not labeled) formed in the respective spacer wheels  64 ,  66 . 
       FIG. 2  illustrates a cross-sectional view of another portion of the gas turbine engine  10  of  FIG. 1  in accordance with one example embodiment. In some embodiments, the gas turbine engine  10  includes a stationary component such as a bearing housing  112 , a rotatable component such as an aft-shaft  24 , and a filled abradable seal component  108 . In the illustrated embodiment, a turbine  16  of the gas turbine engine  10  includes a rotor blade  52  mounted on a rotor  44  of the last stage of the gas turbine engine  10 . The rotor  44  is coupled to the aft-shaft  24  via a connecting element  106  and the aft-shaft  24  is supported by a bearing  110  disposed within the bearing housing  112 . The filled abradable seal component  108  is coupled to aft-shaft  24  and facing teeth  109  of the bearing housing  112  to define a clearance  29  there between the aft-shaft  24  and the bearing housing  112 . In such an embodiment, the filled abradable seal component  108  is configured to regulate windage heating along the clearance  29  and to control leakage of a portion of the exhaust gases  19  through the clearance  29 . 
       FIG. 3  is a flow diagram of a method  200  of manufacturing a filled abradable seal component in accordance with one example embodiment. In one embodiment, the method  200  includes a step  202  of positioning an abradable seal component including a plurality of honeycomb cells. The abradable seal component includes a plurality of honeycomb cells disposed adjacent to each other along an axial direction and a circumferential direction of the turbomachine. In some embodiments, the step  202  of positioning the abradable seal component includes accessing a turbomachine during maintenance of the turbomachine, where the turbomachine includes the abradable seal component including a plurality of honeycomb cells, coupled to the turbomachine. In some other embodiments, the step  202  of positioning the abradable seal component includes receiving the abradable seal component including a plurality of honeycomb cells, which is not coupled to the turbomachine. In some other embodiments, the step  202  of positioning the abradable seal component may include forming the abradable seal component including a plurality of honeycomb cells directly on a surface of either one of the stationary component or the rotatable component using an additive manufacturing technique. In some other embodiments, the step  202  of positioning the abradable seal component may include receiving the abradable seal component including a plurality of honeycomb cells and coupling the abradable seal component to the surface of either one of the stationary component or the rotatable component by brazing. 
     The method  200  further includes a step  204  of applying a filler material on the abradable seal component to fill the plurality of honeycomb cells. In one embodiment, the filler material includes an abradable material, a binder material, and a fluid catalyst. In certain embodiments, the abradable material includes at least one of nickel chromium aluminum-bentonite, cobalt nickel chromium aluminum yttrium-polyester, cobalt nickel chromium aluminum yttrium-boron nitride, aluminum silicon-bentonite, aluminum bronze-polyester, nickel graphite, or aluminum silicon-boron nitride. The binder material includes at least one of aluminum, nickel-aluminum, aluminum thiophosphate, or aluminum thiosulfate. The fluid catalyst includes a solvent including hydroxyl groups. In certain embodiments, the solvent may be an alcohol, water, water-alcohol mixture, an aqueous hydroxide, or combination thereof. Suitable alcohols that may be used in the methods disclosed herein include, but not limited to, methanol, ethanol, and isopropyl alcohol. In one specific embodiment, the aqueous hydroxide is an aqueous solution of metal hydroxide. In one example embodiment, the abradable material is nickel chromium aluminum-bentonite, the binder material is aluminum, and the fluid catalyst is water. In some embodiment, the volume ratio of the nickel chromium aluminum-bentonite to aluminum in the filler material is 1. In another example embodiment, the abradable material is nickel graphite, the binder material is nickel-aluminum, and the fluid catalyst is alcohol, water, or combination of water and alcohol. In yet another example embodiment, the abradable material is cobalt nickel chromium aluminum yttrium-boron nitride, the binder is aluminum thiosulfate, and the fluid catalyst is an aqueous hydroxide. 
     In some embodiments, the step  204  of applying a filler material on the abradable seal component includes sub-steps (i) of mixing the abradable material and the binder material to produce a mixture, (ii) of filling the mixture in the plurality of honeycomb cells, and (iii) of providing the fluid catalyst to the mixture filled in the plurality of honeycomb cells. In some embodiments, the sub-step (i) of mixing the abradable material and the binder material includes selecting the abradable material to the binder material in a volume ratio ranging from 0.5 to 3. In one example embodiment, the volume ratio of the nickel chromium aluminum-bentonite to aluminum in the filler material is 1. In such an example embodiment, the mixture of nickel chromium aluminum-bentonite to aluminum in the volume ratio of 1 may be obtained by mixing 29 grams of nickel chromium aluminum-bentonite with 11 grams of aluminum. In certain embodiments, the sub-step (i) of mixing the abradable material and the binder material may be performed using a mixer machine such as a mechanical mill. It should be noted herein that the mechanical mill may be a grinder, which may be configured to grind and blend the abradable material and the binder material to form the mixture. In some embodiments, the sub-step (ii) of filling the mixture in the plurality of honeycomb cells includes transferring the mixture into the plurality of honeycomb cells. In certain embodiments, the abradable seal component may be disposed on an agitator machine such as a mechanical vibrator while transferring the mixture into the plurality of honeycomb cells to maximize pack density of the mixture in the plurality of honeycomb cells. In other words, the use of mechanical vibrator may ensure that there are no voids left within the honeycomb cells during transferring the mixture into the plurality of honeycomb cells. In certain embodiments, transferring the mixture into the plurality of honeycomb cells includes completely or partially filling an internal volume of the plurality of honeycomb cells. In some embodiments, the term “partially filling” may refer to filling at least 80 percent to 95 percent of the internal volume of the plurality of honeycomb cells. Similarly, the term “completely filling” refers to filling 100 percent of the internal volume of the plurality of honeycomb cells. In some embodiments, the sub-step (iii) of providing the fluid catalyst to the mixture filled in the plurality of honeycomb cells includes spraying or wetting the fluid catalyst such as water on the plurality of honeycomb cells filled with the mixture, thereby initiating a reaction such as hydrolysis to form the reacted mixture and bond the reacted mixture within and to one or more side walls of the plurality of honeycomb cells. For example, water may be sprayed on the plurality of filled honeycomb cells for initiating the reaction between the nickel chromium aluminum-bentonite and aluminum. It should be noted herein that the “hydrolysis” refers to reaction, which forms the bonds of the mixture with the fluid catalyst (e.g., water or alcohol). In certain embodiment, hydrolysis may be exothermic in nature, thereby resulting in bonding the resultant reacted mixture of nickel chromium aluminum-bentonite and aluminum to one or more sidewalls of the plurality of honeycomb cells. In some embodiments, the term “bonding” as used in the context herein means either chemically joining or physically joining the resultant reacted mixture of nickel chromium aluminum-bentonite and aluminum to the one or more side walls of the plurality of honeycomb cells. In one example embodiment, the resultant reacted mixture of nickel chromium aluminum-bentonite and aluminum is chemically bonded to the one or more side walls of the plurality of honeycomb cells, when the resultant reacted mixture forms a surface oxide layer there between. In some other embodiments, the term “bonding” as used in the context means cementing the resultant reacted mixture of nickel chromium aluminum-bentonite and aluminum to the one or more side walls of the plurality of honeycomb cells such that the resultant reacted mixture is retained within the plurality of honeycomb cells. In one example embodiment, the resultant reacted mixture of nickel chromium aluminum-bentonite and aluminum is physically bonded to the one or more side walls of the plurality of honeycomb cells, when the resultant reacted mixture forms cement there between. In some embodiment, the fluid catalyst such as water may be sprayed on a plastic sheet and cover the plastic sheet including the sprayed water over the abradable seal component. In such an embodiment, the water in vapor form may condense into the mixture filled in the plurality of honeycomb cells, thereby initiating hydrolysis reaction. In some other embodiments, the sub-step (iii) of providing the fluid catalyst to the mixture filled in the plurality of filled honeycomb cells includes disposing the abradable seal component including the mixture filled in the plurality of honeycomb cells on a pack of ice. It should be noted herein that the term “pack of ice” includes, but not limited to, to a group of ice formed by freezing of water such as sea water, or hard water, or drinking water, and the like. The pack of ice may result in condensation of water from an atmosphere on the mixture of nickel chromium aluminum-bentonite and aluminum, thereby initiating reaction of the mixture, and bond the resultant reacted mixture of nickel chromium aluminum-bentonite and aluminum to one or more side walls of the plurality of honeycomb cells. In some embodiments, subsequent to the sub-step (iii) the reaction of nickel chromium aluminum-bentonite and aluminum may result in marginally reducing quantity of the resultant reacted mixture within the plurality of honeycomb cells, thereby increasing the density of the resultant reacted mixture. For example, the resultant reacted mixture of nickel chromium aluminum-bentonite and aluminum may get reduced by 5 percent of the internal volume of the plurality of honeycomb cells. 
     In some other embodiments, the step  204  of applying a filler material on the abradable seal component includes a sub-steps (i) of mixing the abradable material and the binder material to produce a mixture (ii) of mixing the fluid catalyst with the mixture to produce a slurry, and (iii) of filling the slurry in the plurality of honeycomb cells. In one embodiment, the sub-steps (i) and (ii) may be performed simultaneously. In another embodiment, the sub-steps (i) and (ii) may be performed sequentially. In some embodiments, the sub-step (ii) of mixing the fluid catalyst with the mixture includes mixing water with the mixture of nickel chromium aluminum-bentonite and aluminum to form the slurry of nickel chromium aluminum-bentonite and aluminum in water. In some embodiments, the sub-step (iii) of filling the slurry includes pouring the slurry into the plurality of honeycomb cells to fill the slurry into the plurality of honeycomb cells. As discussed herein, the slurry may react and bond with one or more side walls of the plurality of honeycomb cells. In some other embodiments, the sub-step (iii) of filling the slurry includes dipping the abradable seal component in the slurry of nickel chromium aluminum-bentonite and aluminum to fill the plurality of honeycomb cells. The slurry may react and bond with one or more side walls of the plurality of honeycomb cells. 
     The method  200  further includes a step  206  of curing the filler material within the plurality of honeycomb cells at a temperature below 250 degrees Celsius to produce the filled abradable seal component. In some embodiments, curing the filler material (i.e., bonded filler material) includes disposing the abradable seal component including the filler material within the plurality of honeycomb cells in a heating machine such as oven to remove excess fluid catalyst (e.g., water or alcohol) from the bonded filler material and produce the filled abradable seal component. In some embodiments, the curing the filler material is performed at a temperature below 250 degrees Celsius at atmospheric pressure to produce the filled abradable seal component. In some other embodiment, the curing is performed below 100 degrees Celsius. In some example embodiment, the curing is performed below 50 degrees Celsius. Further, in such embodiment, curing is performed at a room temperature. For example, the room temperature is in a range from 20 degrees Celsius to 30 degrees Celsius. In some specific examples, the room temperature is in a range from 20 degrees Celsius to 30 degrees Celsius at atmospheric pressure. The atmospheric pressure may be in a range from 80 kilopascals to 100 kilopascals. In certain embodiments, curing is performed below the melting point of the filler material. In one specific example, curing is performed below the melting point of the nickel chromium aluminum-bentonite and aluminum materials. It should be noted herein that the melting point of the mixture of nickel chromium aluminum-bentonite and aluminum may be above 800 degrees Centigrade. In one example embodiment, the filled abradable seal component manufactured as per the foregoing steps discussed herein includes the abradable seal component including the plurality of honeycomb cells filled with the nickel chromium aluminum-bentonite and aluminum, which are bonded to one or more side walls of the plurality of honeycomb cells to form the filled abradable seal component. 
       FIG. 4  is a flow diagram of a method  300  for regulating windage heating in a turbomachine in accordance with one example embodiment. In one embodiment, the method  300  includes a step  302  of placing a filled abradable seal component coupled to either one of a stationary component or a rotatable component of the turbomachine and facing teeth of other of the stationary component or the rotatable component to define a clearance there between. In one example embodiment, the filled abradable seal component includes the abradable seal component including the plurality of honeycomb cells filled with a filler material, which is bonded to one or more side walls of the plurality of honeycomb cells. In one example embodiment, the filler material includes an abradable material such as nickel chromium aluminum-bentonite, a binder material such as aluminum, and a fluid catalyst such as water. In some embodiments, the abradable material may include at least one of nickel chromium aluminum-bentonite, cobalt nickel chromium aluminum yttrium-polyester, cobalt nickel chromium aluminum yttrium-boron nitride, aluminum silicon-bentonite, aluminum bronze-polyester, nickel graphite, or aluminum silicon-boron nitride. The binder material may include at least one of aluminum, nickel-aluminum, aluminum thiophosphate, or aluminum thiosulfate. The fluid catalyst may include a solvent with hydroxyl groups. 
     In some embodiments, the step  302  of placing the filled abradable seal component includes disposing the filled abradable seal component along the clearance defined between a stationary component such as a compressor discharge casing and a rotatable component such as a mid-shaft which is coupled to a compressor and a turbine of the turbomachine. In such an embodiment, the filled abradable seal component is coupled to the compressor discharge casing facing teeth formed in the mid-shaft. In some other embodiments, the step  302  of placing the filled abradable seal component includes disposing the filled abradable seal component along a clearance defined between a tip of a rotatable component such as a rotor blade and a stationary component such as a turbine casing of the turbomachine. In such an embodiment, the filled abradable seal component is coupled to the turbine casing facing teeth formed in the rotor blade. In some other embodiments, the step  302  of placing the filled abradable seal component includes disposing the filled abradable seal component along a clearance defined between a tip of a stationary component such as a stator blade and a rotatable component such as a spacer wheel of the turbomachine. In such an embodiment, the filled abradable seal component is coupled to the turbine casing facing teeth formed in the spacer wheel. In some other embodiments, the step  302  of placing the filled abradable seal component includes disposing the filled abradable seal component along a clearance defined between a stationary component such as a bearing housing and a rotatable component such as an aft-shaft of the turbomachine. In such an embodiment, the filled abradable seal component is coupled to the aft-shaft facing teeth formed in the bearing housing. 
     The method  300  further includes a step  304  of receiving a flow of a swirling fluid along the clearance from the turbomachine. In some embodiments, the swirling fluid may be by-pass fluid released from the compressor bypassing a combustor of the turbomachine. In some other embodiments, the swirling fluid may be a flow of exhaust gases in the turbine, which is released from the combustor. 
     The method  300  further includes a step  306  of restraining de-swirling of the swirling fluid by reducing entrapment of the swirling fluid within the filled abradable seal component to regulate the windage heating in the turbomachine. In one embodiment, the filled abradable seal component prevents the movement of the swirling fluid within the plurality of honeycomb cells, which are filled with the filler material, thereby reducing the entrapment of the swirling fluid within the plurality of honeycomb cells. Thus, the filled abradable seal component restrain de-swirling of the swirling fluid, thereby regulating the windage heating along the clearance. Specifically, the filled abradable seal component preserves swirling motion of the swirling fluid along the clearance and decreases tangential slip between the swirling fluid and the rotatable component, thereby decreases the windage heating along the clearance. 
     The method  300  may further includes a step of regulating the flow of the swirling fluid along the clearance using a plurality of grooves disposed in the filled abradable seal component. In one embodiment, individual grooves of the plurality of grooves are spaced apart from each other along an axial direction of the turbomachine and extends along a circumferential direction of the turbomachine. In some embodiments, the individual grooves of the plurality of grooves may be pre-formed on the filled abradable seal component. For example, the grooves such as at least one of a rectangular groove, a triangular groove, a triangular-rectangular groove, or a convex-rectangular groove may be formed in the filled abradable seal component before the step  302  of placing the filled abradable seal component coupled to either one of the stationary component or the rotatable component of the turbomachine. In some other embodiments, the individual grooves of the plurality of grooves may be formed during the operation of the turbomachine. For example, during certain transient operational conditions of the turbomachine such as startup, the rotatable component may move along the axial direction or a radial direction in relation to the stationary component, thereby causing the teeth in other of the stationary component or the rotatable component to rub against the filled abradable seal component and form the plurality of grooves on the filled abradable seal component. In such an embodiment, each of the plurality of grooves may have different shape without restricting to any a particular shape such as rectangular groove, a triangular groove, a triangular-rectangular groove, or a convex-rectangular groove. 
       FIG. 5  illustrates a perspective view of a filled abradable seal component  68  in accordance with one example embodiment of the present disclosure. In one embodiment, the filled abradable seal component  68  is an abradable seal component  120  including a plurality of honeycomb cells  122 . The plurality of honeycomb cells  122  is disposed adjacent to each other and filled with a filler material  124 . In such an embodiment, the filler material  124  is bonded to one or more side walls  126  of the plurality of honeycomb cells  122 . In the illustrated embodiment, the filler material  124  is filled completely in an internal volume of some of the plurality of honeycomb cells  122 . Although not illustrated, in some other embodiments, the filler material  124  may be filled completely in the internal volume of all honeycomb cells of the plurality of honeycomb cells  122 . 
     In some embodiments, the filler material  124  includes an abradable material, a binder material, and a fluid catalyst. It should be noted herein the fluid catalyst may be used to initiate reaction between the abradable material and the binder material to bond to the abradable material and/or the binder to the one or more side walls  126  of the plurality of honeycomb cells  122 . In certain embodiments, the abradable material includes at least one of nickel chromium aluminum-bentonite, cobalt nickel chromium aluminum yttrium-polyester, cobalt nickel chromium aluminum yttrium-boron nitride, aluminum silicon-bentonite, aluminum bronze-polyester, nickel graphite, or aluminum silicon-boron nitride. The binder material includes at least one of aluminum, nickel-aluminum, aluminum thiophosphate, or aluminum thiosulfate. The fluid catalyst includes a solvent with hydroxyl groups. In one example embodiment, the abradable material is nickel chromium aluminum-bentonite, the binder material is aluminum, and the fluid catalyst is water. 
       FIG. 6  illustrates a perspective view of a filled abradable seal component  468  in accordance with another example embodiment of the present disclosure. In one embodiment, the filled abradable seal component  468  includes an abradable seal component  420  including a plurality of honeycomb cells  422  filled with a filler material. In such an embodiment, the filler material  424  is bonded to one or more side walls  426  of the plurality of honeycomb cells  422 . In the illustrated embodiment, the filler material  424  is filled partially in an internal volume of some of the plurality of honeycomb cells  422 . The filled abradable seal component  468  may be configured to regulate windage heating along a clearance. In some embodiments, the filler material  424  may be filled in a range from 75 percent to 95 percent of the internal volume of at least some of the plurality of filled honeycomb cells  422 . In one example embodiment, the filled abradable seal component  468  has 95 percent of the internal volume filled with the filler material  424 . In such an embodiment, the filled abradable seal component  468  may additionally allow substantially little quantity of the swirling fluid to move into the plurality of honeycomb cells, thereby entrapping the little quantity of the swirling fluid in the honeycomb cells, and resulting in regulating both the winding heating and the leakage of the swirling fluid along the clearance. 
       FIG. 7  illustrates a perspective view of a filled abradable seal component  68  including a plurality of grooves  128  in accordance with one example embodiment. In one embodiment, the plurality of grooves  128  is formed in the filled abradable seal component  68 . Specifically, individual grooves of the plurality of grooves  128  are spaced apart from each other along an axial direction  90  of a turbomachine and extending along a circumferential direction  92  of the turbomachine. As discussed herein, the plurality of grooves  128  may be formed during operation of the turbomachine. For example, during certain transient operational conditions of the turbomachine such as startup, a rotatable component of the turbomachine may move along the axial direction  90  or a radial direction  95  of the turbomachine in relation to a stationary component of the turbomachine, thereby causing teeth in other of the stationary component or the rotatable component to rub against the filled abradable seal component  68  and form the plurality of grooves  128  on the filled abradable seal component  68 . Such a filled abradable seal component  68  may regulate windage heating along a clearance and also control leakage of the swirling fluid through the clearance. 
       FIG. 8  illustrates a schematic diagram of an abradable seal component  468  including a plurality of grooves  428  in accordance with another example embodiment. In one embodiment, the plurality of grooves  428  is formed in the filled abradable seal component  468 . Individual grooves of the plurality of grooves  428  are spaced apart from each other along an axial direction  90  of a turbomachine and extends along a circumferential direction  92  of the turbomachine. As discussed herein, the plurality of grooves  428  may be pre-formed in the filled abradable seal component  468  using machines such as drilling machine, grouting machine, and the like. For example, the plurality of grooves  428  includes at least one of a triangular-rectangular groove  428   a , a rectangular groove  428   b , a triangular groove  428   c , or a convex-rectangular groove  428   d . The filled abradable seal component  468  may be coupled to either one of a stationary component or a rotatable component of the turbomachine and facing teeth of other of the stationary component or the rotatable component to define a clearance there between. For example, the filled abradable seal component  468  may be coupled using brazing technique. During operation, the filled abradable seal component  468  may regulate windage heating along a clearance and control leakage of the swirling fluid through the clearance. Specifically, the plurality of filled honeycomb cells  422  may i) restrain de-swirling of the swirling fluid by reducing movement of the swirling fluid within the plurality of honeycomb cells  422  and entrapment of the swirling fluid within the plurality of filled honeycomb cells  422 , thereby regulating the windage heating along the clearance and ii) regulate a flow of the swirling fluid through the clearance, using the plurality of grooves  428  and the teeth, thereby reducing an amount of the swirling fluid flowing through the clearance. 
       FIG. 9  illustrates a schematic diagram of a filled abradable seal component  568  coupled to a turbomachine  500  in accordance with one example embodiment of the present disclosure. The turbomachine  500  includes a stationary component  502 , a rotatable component  504 , and the filled abradable seal component  568 . The filled abradable seal component  568  includes a plurality of honeycomb cells  522  filled with a filler material  524 , and a plurality of triangular-rectangular grooves  528  formed in the plurality of honeycomb cells  522  filled with the filler material  524 . In other words, the plurality of triangular-rectangular grooves  528  is formed in the filled abradable seal component  568  only after the plurality of honeycomb cells  522  are filled and cured the filler material. The plurality of honeycomb cells  522  filled with the filler material  524  is disposed facing teeth  510  of the rotatable component  504  to define a clearance  516  there between. The filled abradable seal component  568  is coupled to a surface  512  of the stationary component  502  such that each triangular-rectangular groove  528  faces a seal pocket from a plurality of labyrinth seal pockets  514  formed between adjacent teeth  510  of the rotatable component  504 . 
     During operation, the plurality of honeycomb cells  522  filled with the filler material  524  is configured to regulate windage heating along the clearance  516  and the plurality of triangular-rectangular grooves  528  is configured to regulate a flow of a swirling fluid  526  through the clearance  516 . In some embodiments, the plurality of honeycomb cells  522  filled with the filler material  524  reduces entrapment of the swirling fluid  526  within the plurality of honeycomb cells  522  resulting in restraining de-swirling of the swirling fluid  526  within the plurality of honeycomb cells  522 , thereby regulating the windage heating along the clearance  516 . A flow of the swirling fluid  526  through the clearance  516  is regulated using the plurality of triangular-rectangular grooves  528 , the teeth  510 , and the plurality of labyrinth seal pockets  514 . In one example embodiment, regulating the swirling fluid  526  may involve recirculating a portion of the swirling fluid  526  within each triangular-rectangular groove  528  and then deflecting the portion of the swirling fluid  526  using each triangular-rectangular groove  528  to each labyrinth seal pocket  514  to further recirculate the portion of the swirling fluid  526  within each labyrinth seal pocket  514 , thereby restraining the flow of the swirling fluid  526  through the clearance  516 . 
       FIG. 10  illustrates a schematic diagram of a filled abradable seal component  108  coupled to a turbomachine such as a gas turbine engine  10  in accordance with another example embodiment. The gas turbine engine  10  includes the rotatable component such as the aft-shaft  24  and the stationary component such as the bearing housing  112  having teeth  109 , and the filled abradable seal component  108 . The filled abradable seal component  108  includes a plurality of honeycomb cells  122  filled with a filler material  124 , and a plurality of triangular-rectangular grooves  128  formed in the plurality of honeycomb cells  122  filled with the filler material  124 . The plurality of honeycomb cells  122  filled with the filler material  124  is disposed facing teeth  109  of the bearing housing  112  to define clearance  29  there between. The filled abradable seal component  108  is coupled to a surface  116  of the aft-shaft  24  such that each triangular-rectangular groove  128  faces a seal pocket from a plurality of labyrinth seal pockets  114  formed between adjacent teeth  109  of the bearing housing  112 . 
     During operation, the plurality of honeycomb cells  122  filled with the filler material  124  is configured to regulate windage heating along the clearance  29  and the plurality of triangular-rectangular grooves  128  is configured to regulate a flow of a swirling fluid such as the exhaust gases  19  through the clearance  29 . In some embodiments, the plurality of honeycomb cells  122  filled with the filler material  124  reduces movement of the exhaust gases  19  in the plurality of honeycomb cells  122 , thereby regulating the entrapment of the exhaust gases  19  within the plurality of honeycomb cells  122 . Thus, the plurality of honeycomb cells  122  filled with the filler material  124  results in restraining de-swirling of the exhaust gases  19  within the plurality of honeycomb cells  122 , thereby regulating the windage heating along the clearance  29 . A flow of the exhaust gases  19  through the clearance  29  is regulated using the plurality of triangular-rectangular grooves  128 , the teeth  109 , and the plurality of labyrinth seal pockets  114 . In one example embodiment, regulating the exhaust gases  19  may involve recirculating a portion of the exhaust gases  19  within each triangular-rectangular groove  128  and then deflecting the portion of the exhaust gases  19  using each triangular-rectangular groove  128  to each labyrinth seal pocket  114  to further recirculate the portion of the exhaust gases  19  within each labyrinth seal pocket  114 , thereby restraining the flow of the exhaust gases  19  through the clearance  29 . 
     In accordance with one or more embodiments discussed herein, a filled abradable seal component may be configured to regulate windage heating along a clearance of a turbomachine. Further, the filled abradable seal component having a plurality of grooves may be further configured to regulate a flow of swirling fluid along the clearance. The filled abradable seal component may be manufactured using a filler material filled within at least some of a plurality of honeycomb cells of an abradable seal component at an ambient temperature, for example, temperature ranging from 20 degrees Centigrade to 30 degrees Centigrade, without melting the filler material. 
     While only certain features of embodiments have been illustrated, and described herein, many modifications and changes will occur to those skilled in the art. It is, therefore, to be understood that the appended embodiments are intended to cover all such modifications and changes as falling within the spirit of the disclosure.