Abstract: A dual-ended brush seal assembly that may be for turbine engine includes a first structure having a first surface and a second structure having a second surface. A brush seal of the assembly includes a bent bristle pack having a first end in sealing contact with the first surface and an opposite second end in sealing contact with the second surface. The first and second ends project in respective first and second directions that generally traverse one-another.

Abstract: A brush seal includes a bristle pack disposed between a top plate and a back plate. A sliding backing plate is disposed between the bristle pack and the back plate. The bristle pack includes a first bristle set that extends across a seal gap between a first engine component and a second engine component to prevent leakage across the seal gap and a second bristle set that exerts a force on the sliding backing plate. The sliding backing plate supports at least a portion of the first bristles and extends across the seal cavity to contact the second component. The force exerted on the sliding backing plate drives the sliding backing plate into contact with the second component.

Abstract: The main object of the invention is an angular stator sector (10) for a turbomachine compressor, comprising an outer shroud and an inner shroud (S) arranged coaxially one inside the other, and at least one vane (P) extending radially between the outer shroud and the inner shroud (S) and connected to the latter by its radial ends, characterized in that the inner shroud (S) comprises at least one brush seal (1, 2, 3) forming an obstacle to the recirculation of the downstream gases upstream of the inner shroud (S).

Abstract: A device for attaching seal elements in a recess, particularly in an installation groove designed in a flow machine, is disclosed. At least one fixing body is arranged between a seal carrier element and a clamping body assigned to the seal carrier element, where the fixing body is integrally connected to the seal carrier element and the clamping body by bar-like connections that can be detached when subjected to a force. In addition, at least one plastic deformable structure is designed on the fixing body. An attachment method as well as a production method for the device is also disclosed.

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal arc segment that has a sealing portion and a first interface portion. The first interface portion defines circumferential mate faces. A support includes a mounting portion and a second interface portion. The mounting portion is configured to be fixedly attached to an engine static structure, and the second interface portion is radially inward of the first interface portion. At least one positioning member is dimensioned to abut the first and second interface portions such that the first and second interface portions are spaced apart by a predetermined distance in a radial direction.

Abstract: A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A clamp mechanism couples the inner platform and the outer platform to the ceramic-containing airfoil.

Abstract: A seal assembly, includes a first brush supported between first and second plates, a second brush supported on the first and second plates transverse to the first brush seal, and a third plate attached to the second brush.

Abstract: A shaft sealing mechanism (11) that partitions an annular space (14) that is formed between a fixed part (12) and a rotating shaft (13) into a high-pressure-side region and a low-pressure-side region, that obstructs the flow of a fluid (G), and that is provided with: a plurality of annularly laminated thin-plate seal pieces (22) that are fixed to an annular seal housing (21) that is provided to the fixed part and are in sliding contact with the rotating shaft; and an annular low-pressure-side plate (26) that is sandwiched and held such that a low-pressure-side gap (?L) is formed between the seal housing and a low-pressure-side side edge part (22d) of the thin-plate seal pieces. The thin-plate seal pieces have pressure-conduction holes (31) that are formed further to the inside in the radial direction of the rotating shaft than an inner-circumferential-side tip part (26a) of the low-pressure-side plate.

Abstract: A brush seal assembly is operable to seal a gap between a diaphragm and a rotor of a turbine. A brush seal assembly includes: a brush configured to have one end inserted into one side of a diaphragm and the other end protruding toward a rotor; a support strip configured to support one side of the brush; and a back plate configured to support one side of the support strip.

Abstract: A shaft sealing mechanism (11) that partitions an annular space (14) that is formed between a fixed part (12) and a rotating shaft (13) into a high-pressure-side region and a low-pressure-side region, that obstructs the flow of a fluid (G), and that is provided with: a plurality of annularly laminated thin-plate seal pieces (22) that are fixed to an annular seal housing (21) that is provided to the fixed part and are in sliding contact with the rotating shaft; and an annular low-pressure-side plate (26) that is sandwiched and held such that a low-pressure-side gap (?L) is formed between the seal housing and a low-pressure-side side edge part (22d) of the thin-plate seal pieces. The thin-plate seal pieces have a thick part (31) that is formed further to the inside in the radial direction of the rotating shaft than an inner-circumferential-side tip part (26a) of the low-pressure-side plate.

Abstract: A shaft seal mechanism (11) that blocks a fluid (G) flowing within a ring-shaped space (14) is equipped with: a ring-shaped seal housing (21) disposed on a fixed section (12); a plurality of thin-plate seal pieces (22) that are secured to the seal housing (21), are in sliding contact with a rotating shaft (13), and are layered in a ring shape; a ring-shaped high-pressure-side plate (25) that forms a high-pressure-side gap (?H) between itself and the seal housing (21); a ring-shaped low-pressure-side plate (26) that forms a low-pressure-side gap (?L) between the seal housing (21) and the thin-plate seal pieces (22); stepped sections (31, 32) that are formed on side edge sections (22c, 22d) of the thin-plate seal pieces (22); and locking sections (25b, 26b) that lock the stepped sections (31, 32).

Abstract: A sealing structure according to the embodiment includes a first cylinder, a second cylinder, an intermediate cylinder, a first sealing part, and a second sealing part. The first cylinder forms a flow passage of a working fluid of a turbine therein. The second cylinder is disposed at one end of the first cylinder and downstream from the flow passage. The intermediate cylinder is disposed between the first and second cylinders. The first sealing part is disposed at one of a first region between the first cylinder and the intermediate cylinder and a second region between the second cylinder and the intermediate cylinder, and follows a positional displacement in a radial direction. The second sealing part is disposed at the other of the first and second regions, and follows a positional displacement in an axial direction.

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

Abstract: The present disclosure relates to sealing systems for gas turbine engines. In one embodiment, a seal support structure for a gas turbine engine includes a seal support configured to retain a circumferential seal and an engine support configured for mounting the seal support structure to a gas turbine engine mount. The engine support includes at least one channel configured to provide radial movement of the seal support structure and circumferential retention of the seal support. Another embodiment is directed to a sealing system including a circumferential seal and seal support structure configured to provide radial movement.

Abstract: A seal configuration (100) for a turbo machine having a rotor (5), wherein the seal configuration (100) has a sealing element (300) to create a seal with respect to the rotor (5) in an installed position and a supporting device (200). The supporting device (200) has, in at least one section of the supporting device, a material (9) that melts when it comes into contact with the rotating rotor (5) in the installed position. A turbo machine having a seal configuration (100) is also provided.

Abstract: A system for providing a seal between a combustor and a turbine vane. The system includes a flange configured to extend radially from the combustor, and a seal. The flange includes a flange surface configured to face in an axial direction toward a surface of the vane. The seal is configured to be axially loaded between the flange surface and the surface of the vane.

Abstract: A rotary machine (100) includes a rotor (5) that rotates about an axis, a seal housing (30) that is disposed so as to face an outer peripheral surface of the rotor (5), and a seal body (10) that includes a plurality of thin plates (20) extending inward from the seal housing (30) in a radial direction and laminated in a circumferential direction. One thin plate (20) of the plurality of thin plates (20) has a shape in which the thin plate comes into contact with the other thin plates (20) provided on front and rear sides in a rotational direction in a state in which the thin plate does not come into contact with the rotor (5).

Abstract: A seal sub-assembly may comprise a spacer, at least one secondary seal, and a secondary seal cover. At least a portion of the at least one secondary seal are located axially between the spacer and the secondary seal cover. The spacer is attached to the secondary seal cover. The spacer may comprise a first flange and a second flange. The at least one secondary seal may be located axially in line with and radially inward from the first flange. At least a portion of the secondary seal cover may be located axially in line with and radially inward from the second flange.

Abstract: A brush seal includes a bristle part formed by multiple bristles attached to a stationary part between the stationary part and a rotational part that undergo relative motion by maintaining a space in between and a back plate to restrict the movement of the bristle part. Such brush seal for sealing a fluid between the stationary part and the rotational part includes the bristle part formed by the multiple bristles such that the multiple bristles arranged in a direction of pressure difference between the high-pressure side and the low-pressure side are mutually fixed between a base end and a free end to form planar bristles, and these planar bristles are arranged continuously in layers in a circumferential direction to form a circular bristle part, wherein circumferential grooves are formed on the sliding surface of the bristle part on its free end side.

Abstract: A system for sealing an oil chamber from an adjoining exterior volume, and a turbo-machine including a sealing system. The system for sealing the oil chamber from the adjoining exterior volume, both of which are delimited by a mobile rotor in rotation about an axis and a part, fixed or mobile, includes: a first seal arranged between the rotor and the part; a second seal that is mounted between the rotor and the part and which is offset longitudinally relative to the first seal, to form with the first seal a sealing chamber delimited by the rotor, the part, and the two seals; and a mechanism for supplying gas to the sealing chamber, such that the gas can be compressed when the rotor begins to rotate, the chamber communicating with the oil chamber and/or the adjoining exterior volume via the first and second seals alone, respectively.

Abstract: A brush seal assembly may seal a gap between a diaphragm and a rotor of a turbine. The brush seal assembly includes a brush, one end of which is inserted in a rotor facing surface of a diaphragm while the other end thereof protrudes toward a rotor, and a support strip spaced apart from one side of the brush so that one side end portion of the support strip is fixed and the other side end portion thereof supports one side of the brush.

Abstract: A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.

Abstract: A seal includes a housing having a back plate and a front plate. A supporting bristle layer is disposed adjacent to the back plate, and bristles in the supporting bristle layer have a first diameter. A sealing bristle layer is disposed adjacent to the supporting bristle layer, and bristles in the sealing bristle layer have a second diameter. A shielding/protecting bristle layer is disposed adjacent to the sealing bristle layer, and bristles in the shielding/protecting bristle layer have a third diameter. The second diameter is smaller than both the first diameter and the third diameter.

Abstract: A brush seal for a gas turbine, in particular an aircraft engine, is disclosed. The brush seal includes a support ring which has a support plate and a support structure, where the support structure is arranged downstream with respect to the support plate. The brush seal also includes bristles which are arranged upstream with respect to the support ring, where ends of the bristles protrude radially inward beyond the support plate. The support structure yields when a scraping force acting radially outward occurs on a first lateral surface of the support structure, where the first lateral surface is directed radially inward, and the support structure does not yield when an axial operating force occurs on a second lateral surface of the support structure.

Abstract: This invention relates to a seal for sealing between a stator and rotor, including a generally annular carrier, an array of adjacent leaves mounted in the annular carrier for sealing between the stator and the rotor with their panes lying parallel to the axis of the carrier and front and back plates disposed on respective axial sides of the leaves, characterized in the front and back plates have one or more apertures dimensioned for providing a substantially symmetric pressure drop across the leaves.

Abstract: A rotational shaft seal member which does not cause leakage of powder and which has a slit capable of being enlarged as a result of occurrence of springback. Cylindrical shaft seal member 4b at powder container 1 includes pile 5 including woven/knit pile fabric 7 having cut pile 7b at the inside of cylindrical shaft seal member 4b and pile cylindrical support member 4c; the outside diameter 4e being capable of shrinkage as a result of external pressure, and being capable of enlargement as a result of pressure on the inside diameter 4d. When cylindrical shaft seal member 4b is inserted in attachment hole 2a of support frame 2 at the rotating body, attachment is achieved because slit 8 causes shrinkage of outside diameter 4e of cylindrical shaft seal member 4b, enlargement due to springback of slit 8 causing intimate contact with attachment hole 2a.

Abstract: An assembly forming a seal for a turbine engine, comprising a brush seal formed by a plurality of sealing bristles surrounding a core, a retaining cap comprising a portion at least partially housing the brush seal, and a support cover placed in contact with the brush seal in order to hold it in position against the retaining cap, the brush seal being situated between the retaining cap and the support cover. The support cover comprises a structure for lubricating the bristles of the brush seal, comprising an opening for collecting lubricating oil, a lubricating oil distribution groove connected to the opening, and at least one channel for flow of lubricating oil towards the bristles of the brush seal, connected to the groove.

Abstract: A turbine section of a gas turbine engine includes a seal that extends between a vane platform and a Blade Outer Air Seal.

Abstract: As assembly is provided for a gas turbine engine. This assembly includes a component and a brush seal. The component includes a first surface and a second surface. The brush seal includes an annular bundle of bristles which extends longitudinally along an axis to a bundle tip. The bundle of bristles axially contacts the first surface at the bundle tip. The bundle of bristles proximate the bundle tip axially overlaps the second surface, and the bundle of bristles is operable to radially contact the second surface.

Abstract: Aspects of the disclosure are directed to a brush seal comprising: a bristle pack that includes: a first plurality of bristles, each of the first plurality of bristles having a first dimension, and a second plurality of bristles, each of the second plurality of bristles having a second dimension that is different from the first dimension, where a ratio of the first dimension to the second dimension has a range of 2:1 to 5:1.

Abstract: Provided is a shaft sealing apparatus, which includes a seal ring that is installed in an annular space between a rotor and a stator surrounding an outer circumference side of the rotor, that is formed in a divided structure from a movable seal ring and a stationary seal ring whose circumferential ends are adjacent to each other, and that is configured so that the movable seal ring is biased toward a radial outer side thereof by an elastic body, a seal body that is formed by stacking a plurality of thin seal pieces, which extend from the seal ring toward a radial inner side of the rotor, in a circumferential direction of the rotor, and a communicating part that causes the low-pressure side region and the high-pressure side region to communicate with each other.

Abstract: A brush seal assembly may include: a packing body configured to be positioned between a rotating body and a fixing body and provided with an insertion groove; a brush seal part configured to include a brush extending toward the rotating body in a state in which one end of the brush seal part is inserted into the insertion groove and a support member supporting the brush; a thermal expansion member configured to adhere to a side of the support member and be thermally expanded in a circumferential direction of the packing body; and a fixing member configured to be fitted in the insertion groove to face the thermal expansion member to simultaneously fix the brush seal part in the circumferential direction and a radial direction of the packing body.

Abstract: A sealing arrangement for sealing between adjacent first and second exit frames each associated with a transition piece of a turbine. The arrangement includes a transition side seal having bristles that extend from a rail wherein the rail is bendable in a plurality of directions to accommodate bowing of an associated exit frame. The first exit frame includes a rail slot for receiving the rail. The second exit frame includes a bristle slot for receiving the bristles to form a seal between the first and second exit frames, wherein the bristle slot includes a bottom section. The bristles are separated from the bottom section by a bristle gap that is sized to accommodate movement of at least one transition piece to maintain a seal between the first and second exit frames or avoid damage to the bristles.

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: 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: It comprises a first member with a plate attached and substantially covering at least one portion of a second member (20), both members being rotatable relative to each other and defining a tortuous way, and it further comprises a brush sealing attached to the first member and resting on a siding plate in the second member such that an inner gap formed between said first and second members is sealed. A flexible member may be provided between the brush sealing and the first member for joining them in a flexible way.

Abstract: A brush seal includes a bristle part formed by multiple bristles such that the multiple bristles arranged in a direction of pressure difference between a high-pressure side and a low-pressure side are mutually fixed between a base end and a free end to form planar bristles, wherein these planar bristles are arranged continuously in layers in a circumferential direction to form a circular bristle part. Multiple dynamic-pressure generating grooves that generate dynamic pressure by turning and sliding relative to a rotational part are formed independently in the circumferential direction, on the sliding surface of the bristle part on the free end side, in a manner open to the high-pressure side.

Abstract: The present disclosure relates to an aircraft brush seal comprising a first brush seal member and a second brush seal member comprising a channel that receives a plurality of interwoven brush fibers. The interwoven brush fibers may be coupled to the first brush seal member and/or may extend into the second brush seal member. The interwoven brush fibers may not couple to the second brush seal member and/or may form an air seal. The air seal may be formed between a first air compartment and a second air compartment.

Abstract: The present invention is to provide a brush seal device capable of following displacement in a radial direction of a rotational shaft appropriately. The brush seal device prevents leakage of process fluid, wear of a brush seal etc., and leakage of process fluid from an outer circumferential side. The brush seal device 100 of the present invention integrally includes an inner circumferential brush seal 120 and an outer circumferential brush seal 140. The inner circumferential brush seal 120 has a brush portion 123 and an inner-circumferential-side free end portion 125 at the inner circumferential side. The outer circumferential brush seal 140 has a brush portion 143 and an outer-circumferential-side free end portion 145 at the outer circumferential side.

Abstract: A shaft sealing device and a rotary machine equipped therewith are provided with a sealing body configured by stacking a plurality of thin sealing pieces; and a low-pressure-side side sealing plate in which a plate surface facing the low-pressure side is pressed against an inner wall surface of the housing facing the direction of the axis by means of the pressure of a fluid applied from a high-pressure side to the low-pressure side. A protrusion for blocking a downward flow toward the inside of the low-pressure-side side sealing plate in the radial direction along the low-pressure side of the sealing body is formed on the inside of the low-pressure-side side sealing plate in the radial direction, and a communication path for guiding the downward flow blocked by means of the protrusion to a low-pressure-side region is formed on the housing.

Abstract: Disclosed is a shaft seal device comprising: a seal body made by layering a plurality of thin-plate seal pieces in the circumferential direction of the rotor, and a housing that is fixed to the stator, holds the seal body so as to surround the same from radially outside, and includes a first facing surface that faces the high-pressure-side edge of the seal body and a second facing surface that faces the low-pressure-side edge of the seal body. The high-pressure-side clearance between the seal body and the first facing surface is smaller than the low-pressure-side clearance between the seal body and the second facing surface, and a slope part that slopes gradually toward the high-pressure side toward the tip end, which is on the rotor side, is formed in the low-pressure-side edge of each thin-plate seal piece of the seal body.

Abstract: A seal retaining assembly includes a first segment coupled to a first structure. Also included is a recess of the first segment, the recess defined by a first and second wall, the first wall defining a first wall aperture, the second wall defining a second wall aperture. Further included is a second segment having a tab disposed within the recess in fitted contact with the first and second wall to retain the second segment to the first segment in a radial direction, the tab defining a tab aperture, the first and second segment defining an axial gap therebetween, the first wall aperture, the second wall aperture and the tab aperture are aligned to form a passage. Yet further included is a flex seal within the axial gap. Also included is a pin in the passage to fix the second segment to the first segment in axial and circumferential directions.

Abstract: A bearing assembly for a rotating shaft, with brush rings on both sides of the bearing mechanism for damping bearing motion. In a foil gas bearing embodiment, the bearing itself comprises a hollow sleeve, a compliant layer, and a top foil layer. These bearing elements are arranged in a conventional manner except that the top foil layer extends beyond the sleeve. A sleeve extension extends over the extended portion of the top foil layer. Two opposing brush rings, an inner brush ring and an outer brush ring, are attached to the top foil layer extension and the sleeve extension, respectively. The bristles of an inner brush ring and the bristles of an outer brush ring are interposed and provide damping during operation of the bearing.

Abstract: A seal assembly for sealing a circumferential leakage gap between outlet portions of first and second adjacent transition ducts in a gas turbine engine includes a first seal member affixed to the outlet portion of the first transition duct and a second seal member movable with respect to the first seal member. The second seal member is positionable in a non-sealing first position and a sealing second position. While in the first position, the second seal member is circumferentially spaced from the outlet portion of the second transition duct. While in the second position, the second seal member extends across the leakage gap and creates a seal with the outlet portion of the second transition duct to substantially prevent leakage through the leakage gap.

Abstract: An inner wall surface of a low-pressure-side side plate opposite to a lateral surface of a thin plate is formed along a direction crossing an axial direction of a rotating shaft such that a gap between the inner wall surface and the thin plate gradually decreases from a radially inner side toward a radially outer side of the low-pressure-side side plate.

Abstract: A seal assembly for a rotary machine is provided. The seal assembly includes multiple sealing device segments disposed circumferentially intermediate to a stationary housing and a rotor. Each of the segments includes a shoe plate with a forward-shoe section and an aft-shoe section having one or more labyrinth teeth therebetween facing the rotor. The sealing device includes a stator interface element having a groove or slot for allowing disposal of a spline seal for preventing segment leakages. The sealing device segment also includes multiple bellow springs or flexures connected to the shoe plate and to the stator interface element. Further, the sealing device segments include a secondary seal integrated with the stator interface element at one end and positioned about the multiple bellow springs or flexures and the shoe plate at the other end.

Abstract: The current diverter rings and bearing isolators serve to dissipate an electrical charge from a rotating piece of equipment to ground, such as from a motor shaft to a motor housing. One embodiment of the current diverter ring includes an inner body and an outer body configured to clamp at least one conductive segment between them. In the preferred embodiments of the current diverter ring, the conductive segments are positioned in radial channels. The outer body may be affixed to a shaft, a motor housing, a bearing isolator, or other structure. The bearing isolator may incorporate a retention chamber for holding conductive segments within the stator of the bearing isolator, or the bearing isolator may be fashioned with a receptor groove into which a current diverter ring may be mounted.

Abstract: Embodiments of a gas turbine engine including a finger-foil seal are provided, as are embodiments of a finger-foil seal. In one embodiment, the finger-foil seal includes an aerodynamic foil having a generally annular body through which a first opening is formed. A finger seal retention structure is disposed around the aerodynamic foil. A finger seal backing spring is coupled to the finger seal retention structure and extends radially inward therefrom to contact an outer circumference of the aerodynamic foil. A first anti-rotation pin extends radially from the finger seal retention structure and into the first opening formed in the aerodynamic foil to inhibit rotation of the aerodynamic foil during operation of the finger-foil seal.

Abstract: A floating brush seal in a rim cavity of a turbine in a gas turbine engine, where the floating brush seal includes a seal holder in which the floating brush seal floats, and a expandable seal that fits within two radial extending seal slots that maintains a seal with radial displacement of the floating brush seal and the seal holder.

Abstract: A sealing arrangement (100) in an axial turbomachine between, on the one hand, a rotor (1) and, on the other hand, a stator (3) and/or a housing, including a support device (7, 7?) and a sealing element, whereby the support device (7, 7?) extends essentially in the radial direction (r). In the axial direction (u) of the turbomachine, the support device (7, 7?) has an axial contour that effectuates a stiffening effect for the support device (7, 7?).