Abstract: The invention relates to a mechanical seal assembly comprising a mechanical seal (2) with a rotating slide ring (3) and a stationary slide ring (4) defining a seal gap (5) therebetween, a pretensioning device (6) which biases the stationary slide ring (4) in the axial direction (X-X) of the slide ring seal arrangement, a support ring (7) which is arranged on the stationary slide ring (4), the support ring (7) being axially movable relative to the stationary slide ring (4) the pretensioning device (6) being arranged between the support ring (7) and the stationary slide ring, a fixing device (8) which is arranged for axially movable fixing the support ring (7) to a stationary component, a stop (9) which limits a distance (W1) by which the axially movable support ring (7) can be moved, and a secondary seal (10) which is arranged to seal between the support ring (7) and the stationary component.

Abstract: A multi-plane annular brush seal includes a front plate, a back plate, and a plurality of bristles. Each of the plurality of bristles has a first lengthwise portion extending from the base end, a second lengthwise portion, and a third lengthwise portion. The front plate and back plate are configured to maintain the bristle first lengthwise portions substantially parallel to a first plane, the second lengthwise portion of the bristles through a transition region, and the bristle third lengthwise portions substantially parallel to a second plane. The first plane is skewed from the second plane by an obtuse angle. At least some of the bristle second lengthwise portions are maintained in contact with the front plate through the transition region and at least some of the bristle second lengthwise portions are maintained in contact with the back plate through the transition region.

Abstract: A method of working a brush seal assembly for a turbine engine is disclosed and includes the steps of removing an alignment tab from a used brush seal assembly, restoring at least one dimension of the alignment tab to a desired condition and attaching the restored alignment tab to a new brush seal assembly.

Abstract: Described is an abradable component for a gas turbine engine that includes a base having an outboard side which receives a supply of cooling air in use and an inboard side with a plurality of walls thereon. The walls intersect one another to define an abradable network of open faced cells on a gas washed surface thereof, and at least one of the walls includes one or more through-holes for providing a flow of cooling air from the outboard side to the gas washed surface of the abradable network of open faced cells, when in use.

Abstract: A seal shaft for use in an air cycle machine has two axial edges. An axial distance is measured between contact faces at the axial edges, with a tolerance to the dimension. A greatest variation between the axial distance at a plurality of spaced locations on the edge face is maintained with a ratio of the greatest variation to the tolerance being less than 0.2. A rotor assembly, an air cycle machine and a method are also disclosed.

Abstract: A seal assembly for sealing a fluid passageway from contaminants is disclosed. The fluid passageway is formed by a rotating shaft entering an opening in a housing. The fluid passageway connects an interior of the housing, and any exterior of the housing. The seal assembly includes a first sealing member and a second sealing member, which divides the fluid passage into an interior section, an open section, and a sealed section. The interior section is exposed to the interior of the housing. The sealed section is fluidly sealed between the interior section and the open section. A sensor is disposed within the sealed section. The sensor is configured to sense the contaminants within the sealed section and is electronically coupled to a controller configured to send an alarm signal. The sensor is a moisture sensor and extends into an annular recess formed in the stationary member.

Abstract: A brush seal system for sealing a gap between components of a thermal gas turbine that may be moved relative to one another includes a gas seal housing that receives at least one brush head of a brush seal and a support element by means of which a brush packet projecting from the brush head of the brush seal may be supported against flexing. The support element and the brush seal housing are embodied as separate components. The invention furthermore relates to a method for producing such a brush seal system and to a thermal gas turbine having such a brush seal system.

Abstract: The invention relates to a brush seal (10), in particular for the sealing of gaps occurring in turbomachines, including a plurality of individual fibers (12), individual wires or bundles (14) of individual fibers or wires, wherein, in each case, at least two individual fibers (12) or wires, and/or at least two fiber bundles (14) or wire bundles are braided or twisted into a fiber or wire package (16). In addition, the invention relates to a method for producing a brush seal (10).

Abstract: A static gasket configured for establishing a seal between a cylinder head and an engine block including at least one layer having an opening and at least one compression bead. The compression bead extends circumferentially about the opening and projects out of a plane for deforming elastically when the gasket is compressed between the cylinder head and the engine block. A compression limiter which is formed from a metal wire is disposed radially between the opening and the compression bead for preventing the compression bead from being fully flattened, even if the cylinder head is overloaded onto the engine block. The compression bead is preferably induction and/or resistance welded to at least one of the layer(s).

Abstract: A method for temporarily sealing a turbocharger compressor outlet and the seal for doing same are disclosed. The seal may include a layer of lubricant, a cover, and a layer of heat-shrink material. The seal creates a temporary water-tight seal around a turbocharger compressor outlet preventing damage to the inside of the turbocharger while the turbocharger is not in use.

Abstract: A method for fabricating a brush seal assembly comprising, bending a first plate member to a helical shape, bending a second plate member to a helical shape, securing the first plate member to a drum, winding a wire material around the drum and the first plate member, securing the second plate member to the drum, attaching the second plate member and the first plate member to the wire, and cutting the wire to define a bristle length.

Abstract: A leaf seal is proposed for effecting a seal between two coaxial and relatively rotating components. The seal has an annular pack of stacked leaves, the pack being mountable to a first one of the components at root portions of the leaves and extending towards the other component such that end edges of the leaves cooperate to define a seal surface of the pack which is presented for air-riding interaction with a surface of the other component during relative rotation between the components such that, in use, a pressure drop is maintained axially across the pack. The seal surface of the pack incorporates a plurality of hydrodynamic lift-generating recesses spaced circumferentially around the pack. Each said recess extends circumferentially across a plurality of adjacent leaves in the pack, each of which leaves being spaced radially from said surface of the other component along at least part of its end edge.

Abstract: Disclosed is a fluid encapsulating apparatus and method. The apparatus includes a fluid injection nozzle for injecting gas and oil into a tube of the shock absorber through a fluid injection aperture formed in the tube; a position securing mechanism supporting a seal unit of the shock absorber at a certain position in cooperation with a supporter provided to a piston rod of the shock absorber during oil injection; and a seal securing mechanism sealingly securing the seal unit after injection of the gas and oil. Shock absorbers manufactured thereby are also disclosed.

Abstract: In a method for manufacturing a channel-type brush seal of an embodiment, a cored bar is made to abut on a bundle of thin wires and the bundle of thin wires is bent at a part at which the cored bar abuts on the bundle of thin wires. Here, the cored bar is made to abut on the bundle of thin wires so that an extending direction of the thin wires in the bundle of thin wires is inclined with respect to an extending direction of the cored bar, and then the bundle of thin wires is bent, to thereby make extending directions of the bent thin wires intersect. Next, the channel is bent so that the channel sandwiches and fastens the bundle of thin wires and the cored bar at a part at which the bundle of thin wires is bent.

Abstract: A sealing assembly may include a support, an engine component, and a seal. The engine component may be mounted relative to the support to define a gap between the engine component and the support. The seal may be arranged between the support and the engine component to block gasses from passing through the gap. The seal may be adapted to compress and expand to fill the gap during expansion and contraction of the adjacent components that occurs during operation of a gas turbine engine including the sealing assembly.

Abstract: A sealing assembly for establishing a gas and fluid tight seal in an internal combustion engine is provided. The sealing assembly includes a plate of metal which has a plurality of openings and at least one generally flat surface. The plate also has at least one shelf which circumferentially surrounds one of the openings and which opens to the generally flat surface and the opening. The sealing assembly further includes at least one sealing bead of an elastically compressible material which is engaged with the shelf and extends outwardly therefrom past the generally flat surface for sealing the plate with another component in the internal combustion engine.

Abstract: A fluid seal assembly (the assembly) of the present invention is disposed between an outer surface, i.e. engine block or any other part that requires application of the assembly and a rotatable member, such as, for example a shaft, wherein the assembly circumscribes the shaft and lubricated the shaft and the same rotates around the axis. The assembly includes a primary seal and a wear sleeve. The primary seal includes a casing and a seal element that contacts a sealing surface on the wear sleeve. The casing includes an outer diameter and an outer seal molded onto the outer diameter. The wear sleeve has a cylindrical portion defining an inner diameter and an inner seal molded into the inner diameter of the wear sleeve. The outer and inner seals of the present invention provide improved retention in metal bores during thermal expansion and eliminate spring back effect of the assembly after installation.

Abstract: A process is provided for manufacturing leaf seals for effecting seals between coaxial, relatively rotating components. Each leaf seal has an annular pack of leaves which are stacked face-to-face, and are mountable to one of the components at respective root portions of the leaves. The annular pack has a pack radius at the wiping contact edges which is matched within tolerance limits to the radius of the sealing surface. The process includes: determining production parameters for the production of a plurality of leaf seals, the parameters being determined such that at least a portion of the produced leaf seals will have pack radii which violate the tolerance limit; producing the leaf seals using the determined production parameters; and modifying the pack radii of the portion of the produced leaf seals which violate the tolerance limit such that the modified pack radii match the sealing surface within the tolerance limits.

Abstract: Disclosed is a turbomachine having an annular flow duct and a housing structure surrounding the flow duct and a multiplicity of guide vanes and rotor blades which are arranged in the flow duct. The rotor blades are rotatably accommodated in the housing structure whereas the guide vanes are fixed in the housing structure, a plurality of guide vanes forming an annular guide vane ring. The housing structure has a seal in the region of the radially inner flow duct boundary in order to prevent hot gas escaping from the flow duct, which seal is arranged on guide vane roots of the guide vanes of the guide vane ring via a seal support and forms a seal against a rotatable seal surface, the seal support being formed from an intermetallic material, in particular a TiAl material.

Abstract: A blade outer air seal (BOAS) for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion and a shiplap structure that at least partially overlaps at least a portion of at least one of the leading edge portion and the trailing edge portion.

Abstract: A method for molding a plug and a hose or a pipe, wherein the plug is part of a pipe connection and the pipe connection is constructed as a sealing plug-in connection between a connecting piece and the plug. The plug includes an outer part and an inner part connected to each other in one piece and a rear free end of the plug forms an annular gap. The deformation forces acting on expanding jaws of an expanding device during the molding of the plug and the hose or the pipe are directly recorded and the molding of the plug and the hose or the pipe is performed in dependency on these directly recorded deformation forces. As a result, a constant molding degree is achieved in case of plugs and hoses or pipes with varying wall thicknesses.

Abstract: A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion and a seal land that extends from the seal body and includes an inward pointing extension that extends radially inwardly from the radially inner face.

Abstract: Method for removing a front seal plate (11) from an aircraft engine (1), the method comprising at least the following steps: a) separating a part engine unit (5) from the aircraft engine (1), the part engine unit (5) comprising the core engine (6) and the low-pressure turbine (7) of the aircraft engine (1), b) removing a front seal plate nut (10) from the part engine unit (5), c) removing the front seal plate (11) from the part engine unit (5).

Abstract: A fan assembly is provided. The fan assembly includes a rotor having a hub and a plurality of rotor blades extending radially outward from the hub. Each rotor blade includes a blade tip at a radially distal end of each blade. The rotor blade tips define a rotor diameter. The fan assembly also includes a first cylindrical casing substantially axially aligned with the blade tips, the first casing including a first inner diameter that is greater than the rotor diameter. The fan assembly further includes a brush seal assembly coupled to the blade tip of a least one of the plurality of rotor blades, the brush seal assembly configured to contact the casing segment during a first operational mode of the fan assembly, the brush seal assembly configured to avoid contact with the casing segment during a second operational mode of the fan assembly.

Abstract: A seal (48) between a compressor rotor blade (26) and compressor casing (28) comprises an abradable structure (59) on the compressor casing (28). The abradable structure (59) comprises a metallic foam (60) having pores (66, 68). The metallic foam (60) has a first a region (62) and a second region (64). The first region (62) of the metallic foam (60) is arranged adjacent to the compressor casing (28) and the second region (64) of the metallic foam (60) is spaced from the compressor casing (28) by the first region (62) of the metallic foam (60). The pores (68) of the second region (64) of the metallic foam (60) contain an abradable material (70) and the pores (66) of the first region (62) of the metallic foam (60) do not contain an abradable material.

Abstract: A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. At least one of the leading edge portion and the trailing edge portion includes a solid wall and a perforated wall. At least a portion of the perforated wall is spaced from the solid wall such that a passage extends between the solid wall and the perforated wall.

Abstract: A ceramic header configured to form a portion of an electronic device package includes a mounting portion configured to provide a mounting surface for an electronic device. In addition, the ceramic header includes one or more conductive input-output connectors operable to provide electrical connections from a first surface of the ceramic header to a second surface of the ceramic header. The ceramic header also includes one or more thermally polished surfaces.

Abstract: A sealing assembly for use in a gas turbine engine having a disk arranged relative to an axis, the assembly including a circumferential groove defined in the disk and an annular wire seal positioned at least partially within the groove. The groove includes a first sidewall, a base portion adjoining the first sidewall, and a second sidewall adjoining the base portion opposite the first sidewall, wherein the second sidewall is angled in a range greater than 0° and less than 90° with respect to the axis.

Abstract: A stator seal for a turbine assembly includes a seal base securable to a turbine stator and including an annular inner surface, and an abradable coating disposed on the annular inner surface. The abradable coating and the annular inner surface have a predefined cross-sectional profile including a transient operation section that facilitates axial expansion and a steady state operation section that facilitates a tighter clearance.

Abstract: A low cost and simple seal installation method provides for easy installation of bonded pistons and lip seals in an automatic transmission or other industrial machine. The installation method utilizes a flexible circular disc that can be inserted in a gap between the bore and the shaft and is pressed against the seal lip to flip the seal lip to its desired orientation while the disc is rolled around the circumference of the gap to orientate the entire seal in its proper position.

Abstract: A static gasket configured for establishing a seal between a cylinder head and an engine block including at least one layer having an opening and at least one compression bead. The compression bead extends circumferentially about the opening and projects out of a plane for deforming elastically when the gasket is compressed between the cylinder head and the engine block. A compression limiter which is formed from a metal wire is disposed radially between the opening and the compression bead for preventing the compression bead from being fully flattened, even if the cylinder head is overloaded onto the engine block. The compression bead is preferably induction and/or resistance welded to at least one of the layer(s).

Abstract: A sealing system and method is disclosed. The sealing system includes a brush sealing element and an accommodating element with an accommodating chamber. The brush sealing element is disposed in the accommodating chamber and a bendable strap is disposed on the accommodating element. The method includes fastening the brush sealing element in the accommodating chamber of the accommodating element. The accommodating element is arranged in a groove of a housing segment and a position of the accommodating element is secured on the housing element by bending the strap of the accommodating element to engage with a side wall of the housing segment.

Abstract: A seal assembly for use with a turbine having a rotor and at least one turbine blade facilitates the use of a wire seal with seal plate segments. The seal assembly includes a plurality of seal plate segments and a plurality of retainers disposed on a rotor flange on the rotor. A seal member is disposed between the retainers and the seal plate segments. The seal assembly includes at least one attachment member disposed through the rotor flange that limits radial displacement of the seal plate segments.

Abstract: A method of assembling a seal in a horizontal split plane gas turbine engine including providing a rotor assembly including a turbine blade assembly defining a forward face and a seal ring extending axially from the forward face. The rotor assembly is positioned extending through a lower compressor casing and a lower turbine casing, the positioning including tilting the rotor assembly at an angle relative to the longitudinal axis for the engine. An upper turbine casing is positioned over the tilted rotor assembly, and the upper and lower turbine casings define a circumferentially extending seal groove. The rotor assembly is moved in an axially forward direction to position the seal ring in axially overlapping relation within the seal groove. The longitudinal axis of the rotor assembly is then aligned with the longitudinal axis of the turbine engine to further position the seal ring within the seal groove.

Abstract: A machining or processing apparatus (14) for machining or processing a sealing element (16) located within a housing (12) of a gas turbine (10), the machining or processing apparatus (14), at least in the partially assembled state of the gas turbine (10), being at least partly introducible through a port (22) of the housing (12) into an interior space (24) of the gas turbine (10) and including a machining or processing device (15) which allows work to be performed on the sealing element (16) upon introduction of the machining or processing apparatus (14) under relative movement of the machining or processing device (15) and the sealing element (16). In addition, a method for machining or processing a sealing element (16) located within a housing (12) of a gas turbine (10).

Abstract: In one aspect, the present subject matter discloses a seal including a substrate material. The substrate material has a first portion having a first abradability and a second portion having a second abradability, the first abradability being different from the second abradability.

Abstract: An abradable honeycomb is integrally formed in a turbine nozzle sealing flange for engagement with a bucket angel wing to reduce the leakage of air into the turbine's hot gas path. The honeycomb is integrally formed in a turbine nozzle sealing flange using a sinker EDM method to directly sink the honeycomb into the sealing flange itself, so that the honeycomb is an integral part of the flange. For repair, an entirely new honeycomb flange can be made and welded or brazed on to the turbine nozzle.

Abstract: A multi-layer insert for a gasket having a resilient retention tab having a first position and a second position is provided. The multi-layer insert includes a first plate, a second plate having the resilient retention tab formed therein, and a third plate. The first plate and the second plate are coupled to the third plate. The resilient retention tab in the first position extends outwardly from a central planar portion of the second plate and the resilient retention tab in the second position extends over the central planar portion. An indent formed in the first plate and the third plate receives a portion of the resilient retention tab when the resilient retention tab is placed in the second position.

Abstract: A fuel injector cup assembly (26) includes a fuel injector cup (10) having an opening (18) to receive fuel from a fuel rail (15). An open end (27) receives an inlet of a fuel injector (10) therein such that an O-ring (16) seals with the injector cup. A mounting portion (20) extends from a body (29) of the cup and mounts the cup with respect to a cylinder head. Rotation limiting structure (26) is associated with the mounting portion such that when the cup is coupled to the cylinder head and when a first moment is created about the mounting portion causing rotation of the cup with respect to the fuel injector, the rotation limiting structure will engage at least the mounting portion of the cup and create a second moment equal and opposite to the first moment, to prevent further rotation of the cup.

Abstract: A multi-layer insert for a gasket having a retention tab having a first position and a second position is provided. The multi-layer insert includes a first plate, a second plate having the retention tab formed therein, and a third plate. The first plate and the second plate are coupled to the third plate. The retention tab in the first position partially defines a first profile of the second plate and the retention tab in the second position extends outwardly from the first profile of the second plate. An indent formed in the third plate receives a portion of the second plate when the retention tab is placed in the second position.

Abstract: A process is provided for manufacturing leaf seals for effecting seals between coaxial, relatively rotating components. Each leaf seal has an annular pack of leaves which are stacked face-to-face, and are mountable to one of the components at respective root portions of the leaves. The annular pack has a pack radius at the wiping contact edges which is matched within tolerance limits to the radius of the sealing surface, The process includes: determining production parameters for the production of a plurality of leaf seals, the parameters being determined such that at least a portion of the produced leaf seals will have pack radii which violate the tolerance limit; producing the leaf seals using the determined production parameters; and modifying the pack radii of the portion of the produced leaf seals which violate the tolerance limit such that the modified pack radii match the sealing surface within the tolerance limits.

Abstract: A turbine section of a gas turbine engine includes a housing, a rotor assembly, and a seal assembly. The rotor assembly includes a rotor disk, a rotor platform coupled to the rotor disk, and a rotor blade extending from the rotor platform into the mainstream hot gas flow path. The stator assembly includes a stator platform with a stator vane that extends from the stator platform into the mainstream hot gas flow path. The seal assembly includes a first flow discourager extending in a first direction from the rotor platform, a second flow discourager extending in a second direction from the stator platform, the first flow discourager axially overlapping the second flow discourager such that the second flow discourager is interior to the first flow discourager in a radial direction, a hard coating applied to the first flow discourager, and an abradable coating applied to the second flow discourager.

Abstract: A turbomachinery includes a labyrinth seal (2) to prevent unstable vibration of a rotor formed by dividing the seal into segments (7) in a circumferential direction and combining the segments (7) whose comb teeth (5) differ in height. The labyrinth seal (2) preferably includes two kinds of segments (7) whose comb teeth (5) differ in height for each kind of segment, and the segments (7a) of the greater comb tooth height are arranged in a certain reference direction on a cross section right-angled to a rotational axis, and in a direction opposite to the reference direction, and the segments (7b) of the smaller comb tooth height are arranged in a direction right-angled to the reference direction, and in a direction opposite to that right-angled to the reference direction.

Abstract: A seal for a gas turbine engine is shown. The engine may have a first vane for imparting a first twist to air passing thereby and/or a second vane for imparting a second, different twist to air passing thereby, each of the first and second vanes having a mounting area for mounting the seal thereto. The seal includes a top, a bottom, a left side, a right side a back, and a front. The back is parallel to the front and the left side is parallel to the right side such that a non-square shape is formed by the intersection of the back, the left side, the front and the right side so that the seal may mate with the mounting area of the first vane and, if the seal is inverted, may mate with the mounting area of the second vane.

Abstract: A seal assembly includes a body having two circumferential sides, a leading end, and a trailing end. At least one of the circumferential sides includes a first channel sidewall, a second channel sidewall, and a channel bottom wall that together define a seal channel for receiving a seal. The seal channel includes a slot that cooperates with a tab on the seal to facilitate securing the seal within the seal channel.

Abstract: Processes for producing near net-shape panels and panels formed thereby. The processes include forming a preform to comprise a stack of multiple plies that contain an uncured expandable foam material. The preform has regions that differ from each other by the number and/or volume of the plies therein. The preform and its plies are then cured within a restricted volume to produce a near net-shape panel. The curing step causes the expandable foam material to expand, and the restricted volume is sized so that the number and volume of the plies within the regions of the preform cause zones within the panel to have different densities and/or thicknesses.

Abstract: A production method of an annular gasket comprising a metal base and an elastic seal layer laminated to each side thereof, comprising the steps of subjecting a metal sheet to punching out process to obtain a plurality of divided constituent members for the metal base, each of the divided constituent member having a slightly wider width than a given gasket width and a predetermined shape for constituting an annular shape of the given gasket, butting these constituent members to temporarily configure the annular shape and bonding the butt parts to each other by welding to form an annular object, subsequently laminating an elastic compound material to each side of the annular object to form elastic seal layers after applying pressurizing process to the annular object, and punching a given shape out of the annular object to obtain the annular gasket.

Abstract: A seal assembly for a turbomachine is provided. The seal assembly includes multiple arcuate packing ring segments disposed intermediate to a stationary housing and a rotatable element about an axis. The seal assembly further includes multiple flexures mechanically coupled to the stationary housing and the multiple arcuate packing ring segments, wherein the multiple flexures are attached to the stationary housing and the arcuate packing ring segments at positions predetermined to control packing ring twist under differential pressure conditions.

Abstract: A seal ring whose abutment joint portion is opened is fitted into an annular gap while the abutment joint portion is substantially closed. The annular gap is formed between an inner circumferential surface of a hole portion provided in an outer circumferential jig and an outer circumferential surface of an inner circumferential jig disposed in the hole portion, and has a heating region and a cooling region. The seal ring is passed through the heating region and then passed through the cooling region in the annular gap. The outer circumferential jig and the inner circumferential jig are maintained at a constant temperature higher than a glass transition temperature of a resin material for the seal ring in the heating region, and maintained at a constant temperature lower than the glass transition temperature of the resin material for the seal ring in the cooling region.

Abstract: A seal assembly has a first seal member, a second seal member, and a third seal member. The first seal member has a wear surface that contacts a first wall of the cavity at two sealing locations. The second seal member has a wear surface that contacts a second wall of the cavity at two sealing locations. The third seal member extends between and resiliently connects the first seal member to the second seal member.