Abstract: A power tool includes a tool housing and a motor assembly received in the tool housing. The motor assembly has a rear end portion, a front end portion, and a motor output shaft. A transmission housing is coupled to the motor housing with a transmission received in the transmission housing, to which the motor output shaft is drivingly coupled. A partition assembly includes a rear cover covering a rear end portion of the transmission housing that faces the front end portion of the motor and a seal. The rear cover of the transmission housing, the front end portion of the motor, and the seal together define at least a first labyrinth path and a second labyrinth path therebetween configured to inhibit grease or dust migration between the transmission housing and the motor assembly.

Abstract: A sealing device between a rotor part and a stator part, including at least one abradable coating cooperating with at least two upstream and downstream labyrinth seal lips. Axially upstream of the labyrinth seal lips, the sealing device includes a circumferential wall that radially extends beyond the upstream free axial sealing surface of the coating to create, at the free end of the upstream labyrinth seal lip, a separation of the circulating gas.

Abstract: In an exemplary embodiment, a seal device (10) that seals between a housing (11) and a rotation shaft (20) passing through the housing (11) includes: a floating ring (15) arranged with a gap h with respect to the rotation shaft (20), a seal portion (14) formed by bringing one end face of the floating ring (15) into contact with the housing (11), and a space portion j provided between the floating ring (15) and the housing (11), and the floating ring (15) includes bias means that contactlessly biases the floating ring (15) to the seal portion via the space portion j. The seal device in which the floating ring follows movement of the rotation shaft is capable of exerting a sealing operation so that vibration of the rotation shaft can be reduced.

Abstract: A labyrinth seal system having at least two sealing fins arranged axially one behind the other on a rotor of a turbomachine and having a radially facing run-in element for the at least two sealing fins on a stator of the turbomachine, wherein in each case one radial sealing gap exists between the run-in element and the at least two sealing fins, wherein maxima of the radial sealing gaps are arranged offset with respect to one another in a circumferential direction, such that, in the region of the maxima, a passage exists in targeted fashion, for an air flow to the sealing fins that follow downstream, in the event of rubbing against the stator. This may be applied for example in a gas turbine engine.

Abstract: The present disclosure is directed to a rotor thrust balanced turbine engine that may increase engine performance and efficiency while managing thrust mismatch or imbalance in a low pressure (LP) spool between a fan assembly and a turbine rotor assembly. The gas turbine engine defines a radial direction, a longitudinal direction, and a circumferential direction, an upstream end and a downstream end along the longitudinal direction, and an axial centerline extended along the longitudinal direction. The gas turbine engine includes a turbine rotor assembly and a turbine frame. The turbine rotor assembly defines a first flowpath radius and a second flowpath radius each extended from the axial centerline. The first flowpath radius is disposed at the upstream end of the turbine rotor assembly, and wherein the second flowpath radius is disposed at the downstream end of the turbine rotor assembly.

Abstract: A contactless seal intended for being fitted in a wall and a shaft passing through an opening of the wall, the seal comprising a rotary member intended for being supported by the shaft and a stationary member intended for being supported by the opening, the stationary member being inserted around the rotary member while being rotatably movable relative to same, the rotary member having an outer surface provided with at least one circumferential rib and the stationary member having an inner surface provided with at least one groove, or vice-versa. Each rib is partially inserted into a corresponding groove in order to form a labyrinthine leak path. The rotary member and the stationary member are each made up of a single part, and the rotary member and/or the stationary member are obtained by additive manufacturing.

Abstract: The invention relates to a guide vane segment for an aircraft engine, having at least one guide vane element, having at least one flange formed in a radial extension direction (R) of the guide vane element and at least one positioning member projecting from the flange in the radial extension direction (R), and at least one seal carrier, which is arranged at the flange and is aligned relative to the guide vane element by way of the positioning member, wherein the flange has a supporting surface on which the seal carrier is supported, wherein a partial surface of the positioning member is adjacent to the flange at a transition from the flange to the positioning member, and respective surface normal lines of the supporting surface and of the partial surface enclose between them an angle (?) that is different from a zero angle.

Abstract: A seal for sealing a combustor heat shield against an interior surface of a combustor shell, the seal comprising: a first sealing surface on the interior surface of the combustor shell; and a second sealing surface on a rail on an edge of a heat shield, wherein each of the first and second sealing surfaces include first and second projections defining a non-linear leakage path between the projections.

Abstract: A rotor member is described for a gas turbine that is adapted for rotating about a central axis, the rotor member being a blisk having a rotor blade row that extends around the central axis or a rotor disk having a mounting portion for installing rotor blades of a rotor blade row that extends around the central axis, and being axially offset from the rotor blade row and/or the mounting portion and, extending coaxially, having at least one annular and axially asymmetrical sealing fin that has a radially outer tip portion having a front flank facing the rotor blade row and/or the mounting portion, and an opposite flank facing away from the rotor blade row and/or the mounting portion; the front flank being less steep than the opposite flank; a turbine and a compressor having such a rotor member, and a method for manufacturing such a rotor member having at least one sealing fin coating.

Abstract: A rotary machine satisfies at least one of Dr1<Dh1?Dr2 or Dc1?Dt1>Dc2. Dr1, Dh1, Dr2, Dc1, Dt1, and Dc2 are distances from a rotational center axis of a hub to an upstream end of a first blade-facing surface facing a hub-side end surface of a variable blade, an upstream end of the hub-side end surface when the blade angle is maximum, a downstream end of a first outer peripheral surface adjacent to an upstream side of the blade-facing surface, an upstream end of a second blade-facing surface facing a tip-side end surface of the variable blade, an upstream end of the tip-side end surface when the blade angle is minimum, and a downstream end of a first inner peripheral surface adjacent to an upstream side of the second blade-facing surface, respectively.

Abstract: An axial assembled interlocking labyrinth seal with a rotor and a stator each having a series of separate spiral shaped teeth with a gap formed on each of the separate teeth, so that the rotor can be rotated within the stator and axially advanced by aligning the gaps of the teeth on the rotor with gaps on the stator so that the axial labyrinth seal can be assembled.

Abstract: A turbocharger includes: a bearing housing (housing); a bearing disposed in the housing and having a thrust bearing surface; and a partition wall portion assembled to the housing, the partition wall portion including an inclined surface positioned on an outer side in a radial direction of the thrust bearing surface, extending at least vertically above the thrust bearing surface, and inclined with respect to a direction perpendicular to the axial direction of a shaft.

Abstract: Molten metal transfer pump, in which a shaft (4) with the impeller (5) mounted on the shaft (4) is installed on the upper bearing (2) and the lower journal plain bearing (3). The lower journal plain bearing (3) has rotor (15) and stator (16) parts. The rotor part (15) is made in the form of two split bushings (17) mounted on the shaft (4), and the stator part (16) is made in the form of two split bushings (18) fixed in the cage (19) in axial alignment with the shaft (4). Bushings (17) (18) are fixed correspondingly with flat rings (24) (33) and composed of cylinder segments (20), (28) equidistantly placed in a circumferential direction, located correspondingly in the cylindrical groove (21) on the shaft and cylindrical groove (29) of the cage (19) and fixed with cone hold-down rings (22), (30) radially, and with spring rings (23), (31) axially.

Abstract: A rolling bearing with sealing device provided on each side of the rolling bearing in order to prevent the entry of contaminants inside the rolling bearing, the rolling bearing having a non-rotating outer ring and a rotating inner ring and with a plurality of rolling bodies placed between them. The sealing device provided with first and second shields arranged axially in series between them across a cavity defined by the two rings, the first shields integral with the outer ring and the second shields integral with the inner ring and defining with the first shields an annular gap, which has a substantially constant axial thickness and is radially bounded by a first sealing labyrinth arranged in the region of the outer ring and a second sealing labyrinth arranged in the region of the inner ring.

Abstract: Systems and methods to help provide lubricant to a bearing in a compressor are disclosed. The embodiments disclosed herein generally are directed to systems and methods to provide a lubricant flow to the bearing, where the lubricant flow relies on the rotation of a shaft of the compressor, so that the lubricant flow can be independent of a power supply.

Abstract: Aspects of the disclosure are directed to a seal associated with an engine of an aircraft. The seal includes a plurality of lands, and a barrel coupled to the lands and formed from a plurality of segments, where the segments are coupled to one another such that the barrel is substantially non-linear.

Abstract: A compressor and a method of assembling the compressor are provided. The compressor includes: a shell; a motor arranged in the shell, the motor having a stator, a spacer mounted with a first bearing therein, a drive shaft supported by the first bearing and a rotor fixed onto the drive shaft; a low bearing support; a positioning member positioning the second bearing and being connected to the low bearing support; and a second bearing connected to the positioning member and/or the low bearing support and supporting the drive shaft. Furthermore, the positioning member may be removed from or maintained in the compressor after it is assembled. The present disclosure can avoid the adverse effects of the gravity of the rotor and the drive shaft and/or the magnetic force between the rotor and the stator on positioning the bearings and the drive shaft and can improve positioning accuracy and assembling efficiency.

Abstract: An arrangement of a rotating component and a stationary component of a gas turbine engine includes a rotating component, a stationary component positioned to define an actual gap between the rotating component and the stationary component, and a flow restriction feature formed at one of the stationary component or the rotating component. The flow restriction feature is configured to induce a recirculation flow at the actual gap, thereby defining an effective gap between the rotating component and the stationary component to reduce a leakage flow therebetween, while maintaining the actual gap greater than the effective gap.

Abstract: In a seal structure that seals a gap between a first structure and a second structure which faces the first structure in a radial direction and rotates relative to the first structure, one of the first structure and the second structure has a base surface and a step surface that protrudes toward the other side from the base surface, and the other is provided with: a first fin which extends toward the step surface and forms a first gap between the step surface; a second fin that, on the downstream side of the first fin, extends toward the base surface and forms a second gap between the base surface; and a protrusion part that is disposed between the first fin and the second fin and that divides a leak flow, into a first vortex along the first fin and a second vortex along the second fin.

Abstract: Aspirating face seal between high and low pressure regions of turbomachine between rotatable and non-rotatable members of turbomachine includes gas bearing rotatable and non-rotatable face surfaces, non-rotatable face surface mounted on annular slider on non-rotatable member. Retracting means retracts annular slider away from rotatable member and non-rotatable face surface away from rotatable surface and includes circumferentially spaced apart non-coiled springs axially disposed between slider and non-rotatable engine member. Leaf springs may include first and second ends mounted or attached to first and second mounting lugs or tabs attached to non-rotatable member and slider respectively and middle portion between ends. Springs oriented for retracting slider if slider contacts rotatable member. Primary and starter seal teeth may be mounted on carrier on rotatable member. Primary seal tooth may be on non-rotatable member and starter seal tooth on rotatable member.

Abstract: The present disclosure relates to a tip clearance control assembly of a gas turbine including a casing, a plurality of blades, a labyrinth seal, and a shroud. The casing guides a flow of combustion gas. The plurality of blades is located inside the casing in such a manner as to be coupled to a rotary shaft of the gas turbine. The labyrinth seal is located at the front end portion of each blade. The shroud surrounds the front end portion of each blade. The casing includes an outer casing having dove tail slots and an inner ring segment having dove tail coupling portions, so that the dove tail coupling portions moves in an axial direction and a radial direction with respect to the gas turbine.

Abstract: A turbine vane assembly for a gas turbine engine is disclosed and includes an airfoil rotatable about a first axis transverse to an engine longitudinal axis. The airfoil includes an endwall and at least one protrusion disposed on the endwall configured for obstructing flow through a gap between the endwall and a static structure of the gas turbine engine.

Abstract: The fluid machine includes a stationary member (6), a rotary member (5) and a labyrinth seal (9) including a succession of stationary steps (11) formed on the stationary member (6), and a succession of rotary steps (14) formed on the rotary member (5). The labyrinth seal (9) further includes a plurality of stationary recesses (18) each formed in a radial wall portion (12) of a respective stationary step (11), and a plurality of rotary recesses (21) each formed in a radial wall portion (16) of a respective rotary step (14). Each stationary step (11) defines a stationary projection (19) delimited by the stationary recess (18) formed on said stationary step (11), and each rotary step (14) defines a rotary projection (22) delimited by the rotary recess (21) formed on said rotary step (14). The axial width (Wr) of each of the stationary recesses (18) and of the rotary recesses (21) substantially equals the axial width (Wp) of each of the stationary projections (19) and of the rotary projections (22).

Abstract: Provided is a turbine. One of a tip portion of a blade and a portion of a partition plate outer ring corresponding to the tip portion of the blade is provided with a step part having a step face that protrudes toward the other, and the other is provided with seal fins) extending out with respect to the step part and forming minute clearance between the step part and the other. The step part facing the seal fins is configured to protrude so that a cavity forming a main vortex and counter vortex being formed by the main vortex are formed on an upstream side of the seal fins. The cavity is formed so that an axial width dimension and a radial height dimension satisfy Formula expressed by 0.45?D/W?2.67.

Abstract: A tolerance ring including a sidewall having a first and a second opposite major surfaces spaced apart by a thickness, wherein the first major surface defines an inner diameter of the tolerance ring at a first location of the sidewall and an outer diameter of the tolerance ring at a second location of the sidewall. A method of forming a tolerance ring including providing a strip of material comprising a first, a second, a third, and a fourth edge, shaping the first edge of the strip toward the third edge, and shaping the second edge of the strip toward the fourth edge.

Abstract: An air seal includes a sealing gland configured to retain a ferro-fluid and one or more seals. A portion of the one or more seals is configured to extend into the sealing gland. A gas turbine engine, includes the air seal. A method of sealing low pressure air from high pressure air, includes the steps of providing a sealing gland configured to retain a ferro-fluid, distributing the ferro-fluid into the sealing gland, providing one or more seals, wherein a portion of the one or more seals is configured to extend into the sealing gland, and removing the ferro-fluid from the sealing gland.

Abstract: A first aspect of the invention provides an axially faced seal system for a radial tip of a turbine component, the system comprising: a stationary turbine component; a rotating turbine component; and a seal ring mounted to the stationary turbine component, the seal ring extending axially to the rotating turbine component and engaging the rotating turbine component on a side surface, wherein the side surface of the rotating turbine component is on a continuous, rotating mating ring having a 360 degree arc.

Abstract: A carrier bearing assembly includes a bracket, a mounting structure permitting the bracket to be mounted to a frame of a vehicle, an opening in the bracket extending through the bracket, from a first lateral side of the bracket to a second lateral side of the bracket, the opening substantially offset (e.g., an inch or more off center) in a direction; and a bearing fitted into the opening permitting a driveshaft of the vehicle to pass through and to substantially constrain movement of the driveshaft. Additionally, the opening can be formed as a non-straight hole allowing the driveshaft to pass through the bearing at a non-perpendicular angle. The carrier bearing assembly permits a substantial correction one more operating angle of the driveshaft by constraining the angle of a portion of the driveshaft.

Abstract: A rotary machine includes turbine moving blades (50); a casing (10) covering the turbine moving blades (50) so as to define a gap at an outer circumferential side of the turbine moving blades; a leaf seal (70) having a seal body (71) that is disposed in the gap so as to protrude radially inward from the casing (10) and is capable of coming into contact with the turbine moving blades (50), and a high-pressure-side plate member (73) that is disposed along a face facing a high pressure side of the seal body (71); and a swirling flow inhibitor (80) that is provided on the high pressure side of the leaf seal (70) in the gap and inhibits a swirl flow flowing through the gap in a circumferential direction.

Abstract: An assembly can include a first radial compressor wheel that has a rotational axis and that includes a hub surface that includes an annular ridge disposed at a radius measured from the rotational axis; a second radial compressor wheel that includes a hub surface; and an annular baffle disposed at least in part between the hub surfaces where the annular baffle includes an outer surface and an inner edge that defines an opening having a central axis where the outer surface includes a surface portion to one side of the inner edge that faces the hub surface of the first radial compressor wheel, where the surface portion includes an annular channel over a radial width measured from the central axis and where the radial width spans the radius of the annular ridge.

Abstract: According to an embodiment, a rotor blade cover section is integrated with the rotor blades at leading ends thereof. A plurality of sealing fins is disposed at the rotor blade cover section, the sealing fins forming a predetermined clearance relative to an inner peripheral portion of the nozzle outer ring. An annular solid particle trapping space is disposed at the inner peripheral portion of the nozzle outer ring, the solid particle trapping space communicating with an inlet of a steam leak and trapping solid particles that flow in with steam. In the sealing structure, the nozzle outer ring has a through hole through which the solid particles are to be discharged from the solid particle trapping space toward a downstream stage of the steam turbine.

Abstract: A non-locating bearing assembly is configured to rotatably support a shaft relative to a housing while permitting relative axial displacement of the shaft relative to the housing. The bearing assembly includes a bearing having inner and outer rings and that is configured for transmitting radial and axial forces, and a bearing support attachable to the housing and including a support section having a partially cylindrical seat surface for receiving one of the inner and outer bearing rings and forming a sliding seat therefor. The sliding seat allows a relative axial displacement between the support section and one of the inner and outer bearing rings. A spring is disposed on or in the bearing support for generating a force in the axial direction between the bearing support and the one of the inner and outer bearing rings, and the spring element is formed from a segment of the bearing support.

Abstract: A bearing assembly includes a housing having an interior cavity, an opening, and an inward facing seal mounting surface. The assembly includes a bearing and a shaft mounted in the bearing for rotation about a central axis. The assembly includes a seal positioned axially between the interior cavity and the exterior of the housing to inhibit contaminants from entering the housing and damaging the bearing. The seal has a bearing side, an opening side, and a gap surface facing a corresponding surface that is either an outward facing surface of the shaft or thee inward facing seal mounting surface of the housing. The gap surface is spaced from the corresponding surface by a clearance gap. The width of the clearance gap increases from the bearing side to the opening side to direct fluid in the clearance gap away from the interior cavity as the shaft rotates.

Abstract: A labyrinth seal is provided for sealing the annular interspace between the rotor and the stator of a steam turbine or gas turbine. The labyrinth seal includes a multiplicity of sealing strips which are arranged in series in the axial direction and fastened on the stator and project into the interspace. The sealing strips interact, with sealing effect, with rotor-side sealing elements which are arranged in a staggered manner. An improved sealing effect is achieved by the sealing strips in the cold installed state being offset in relation to a symmetrical position, wherein the offset has the reverse direction and the same amount as the distance by which the sealing strip is displaced relative to adjacent rotor-side sealing elements as a result of thermal expansions of the stationary and rotating components and support structure when being heated from the cold installed state to a hot steady-state operating condition.

Abstract: A sealing element for sealing a cylindrical inner surface of a first machine component and a cylindrical outer surface of a second machine component includes an inner ring, an outer ring arranged coaxially with respect to the inner ring, and a sealing gap, which is formed by an exterior lateral face of the inner ring and an interior lateral face of the outer ring. In an axial section through the common axis of the inner ring and the outer ring the sealing gap has a profile having an inlet section as a first end portion of the sealing gap having a first radius to the common axis; an outlet section as a second end portion of the sealing gap having a second radius to the common axis, wherein the second radius is smaller than the first radius; and a meander section, which adjoins the inlet section and which has a monotonically decreasing radius.

Abstract: A ring seal for a machine component is provided. The ring seal includes a main body. The main body includes an inner surface defining an inner periphery. The main body also includes an outer surface defining an outer periphery. The ring seal also includes a tab having a height and a width. The tab extends from the main body. The tab is configured to contact at least one of a first interfacing surface and a second interfacing surface of the machine component to provide sealing therebetween.

Abstract: A gearing having a shaft that projects from the gear interior into the environment, the shaft being sealed with the aid of at least one contactless seal, and the opening of the contactless seal, which is oriented toward the interior of the gearing, i.e., the spatial region of the gearing that contains the lubricating oil, being disposed above the lubricating oil level that comes about when the gearing is not in operation, a tin piece being disposed between the opening and the gear-tooth piece situated closest to this opening and generating lubricating oil waves and/or lubricating oil foam from the lubricating oil bath.

Abstract: A turbine includes a blade, a structure installed at a tip section side of the blade via a gap and configured to relatively rotate with respect to the blade, a step section formed at the tip section of the blade, having at least one step surface, and protruding toward a portion opposite to the tip section of the structure, a seal fin formed at the portion opposite to the tip section of the structure, extending toward the step section, and configured to form a micro gap between the step section and the seal fin, and a cutout section formed at the step surface to be connected to an upper surface of the step section. The cutout section guides a separation vortex separated from a main stream of a fluid passing through the gap toward the seal fin on the upper surface of the step section.

Abstract: Spark suppression shield for electric motors relates to universal commutator motors and to permanent magnet DC motors operating in environment containing flammable or explosive gases. The collar shaped as a wall is extending from bearing frame and surrounding commutator in approximately it's total height, where the gap in radial direction between commutator and collar is up to 3 mm and the collar might or might not have collar openings.

Abstract: Provided is a pinhole inspection apparatus for can bodies capable of effectively preventing entrance of ambient light to a photodetector side through a gap between a movable plate and a rotating turret that may be formed due to a surface condition or the like. The pinhole inspection apparatus of the present invention includes: a rotating turret having a penetrating through hole; a movable plate provided on a stationary frame opposite the rotating turret; a can body holding member supporting a can body; a photodetector detecting light leaking inside the can body; and a light source irradiating the can body with light. The pinhole inspection apparatus is characterized in that a detour path formed by a pair of shield parts spaced apart a predetermined distance and opposite from each other is provided as a shield mechanism in an entire outer peripheral region of the rotating turret.

Abstract: The present disclosure relates to a seal assembly for a turbomachine that includes at least one arcuate plate, a biasing member, and a packing ring. In addition, the seal assembly includes a plurality of arcuate teeth disposed intermediate to the packing ring and the rotor. The plurality of arcuate teeth includes at least one subset of arcuate teeth. The clearance of at least one of the arcuate teeth is different from the clearances of the rest of the arcuate teeth. The clearances of the arcuate teeth of the at least one subset do not progressively increase going from an upstream to a downstream side of the turbomachinery.

Abstract: An example housing of a cabin air compressor assembly includes a main body portion and a motor outlet duct extending radially from the main body portion. The motor outlet duct interfaces with the main body portion at an interface area. A ratio of a radius of the interface area to an inner diameter of the motor outlet duct is from 0.113 to 0.162.

Abstract: A labyrinth seal includes a first labyrinth ring and a second labyrinth ring. In an installed state of the labyrinth seal, the first labyrinth ring and the second labyrinth ring engage in each other in an at least partially overlapping manner and are rotatable relative to each other. Furthermore, in the installed state, mutually-opposing surfaces of the first and of the second labyrinth ring have different wear resistances.

Abstract: A bearing isolator seal includes a rotor and stator wherein the stator has inboard and outboard radial projections which define a groove bounded by groove side faces and a groove bottom face. The rotor extends radially and then axially so as to lie closely adjacent to the terminal end of the outboard radial projection on the stator to define an entrance passageway. The bearing isolator seal includes a surface geometry which is believed to result in improved exclusion of contaminants, particularly from high velocity water spray, wherein the entrance passageway is angled to increase the rotational effects of exclusion during shaft rotation, and wherein the groove side faces are also angled to assist in redirecting spray and other contaminants away from the passageway.

Abstract: The present disclosure relates to a seal assembly for a turbomachine that includes at least one arcuate plate, a biasing member, and at least one packing ring segment. The packing ring segment includes at least one barrier that restricts circumferential flow of a fluid along the packing ring segment. In addition, the seal assembly includes a plurality of arcuate teeth disposed intermediate to the packing ring segment and the rotor. The clearances of at least two of the arcuate teeth are different from one another.

Abstract: A shroud for a turbine and a method of assembling is provided. The turbine includes a housing, a rotatable shaft and a bucket extending outward therefrom. The shroud includes an alignment member which is coupled to the housing, wherein the alignment member includes a first end, a second end and a body extending between the first and second ends. The second end includes an arcuate portion to facilitate fluid flow downstream from the bucket. The shroud further includes a seal coupled to the body to facilitate sealing a gap defined between the bucket and the body.

Abstract: A seal assembly for sealing a stationary component and a rotating component including a seal tooth mating surface for mating with a seal tooth, the seal tooth mating surface including a plateau portion for sealingly receiving the seal tooth during a steady-state operation of the seal assembly and a first concave portion adjacent to the plateau portion for receiving the seal tooth with a clearance during a first non-steady-state operation of the seal assembly, wherein the seal tooth is coupled to one of the stationary component and the rotating component and the seal tooth mating surface is coupled to the other of the stationary component and the rotating component.

Abstract: A knife edge seal assembly includes at least one knife edge and at least one honeycomb ring seal. The at least one knife edge has material removed to a first knife edge radial height and the least one honeycomb ring seal has material removed to a finished radial thickness for sealable engagement with the at least one knife edge. The finished radial thickness of the replacement honeycomb ring seal establishes a first radial gap between an inner annular surface of the replacement honeycomb ring seal and the knife edge before the knife edge seal assembly begins rotating in the gas turbine.

Abstract: A labyrinth sealing device is disclosed for use between a rotating shaft and a bearing housing. In some embodiments, an internal stator engages the housing and a rotor engages the shaft. A labyrinth pathway is defined between the rotor and stator to prevent the migration of lubricants and/or contaminants in either direction. The rotor acts as a running surface for the sealing element, but may also with a ground surface of the rotor to provide a pump that continuously draws lubricant away from the sealing lip toward a sump. In another embodiment, the stator and sealing element are combined as a single element formed from a sealing material. A recess in the sealing lip creates a pressure differential at the sealing surface and minimizes wear.

Abstract: A seal assembly including first and second components; a seal arranged between the first and second components to seal a secondary flow region from a primary flow region; and a second recess portion provided on a surface of the second component between the seal and the primary flow region, the second recess portion further being arranged to receive a first portion of a flow from the secondary flow region and being configured to promote a second flow feature within the second recess portion, wherein the second recess portion is set back from the surface of the second component such that a second portion of the flow from the secondary flow region bypasses the second recess portion.