Abstract: A gas turbine engine includes a ceramic wall for bounding an engine core gas path. The ceramic wall has a ceramic wall first side that faces the engine core gas path and a ceramic wall second side that faces away from the engine core gas path. There is a metallic wall adjacent the ceramic wall second side. The metallic wall has a metallic wall first side that faces the ceramic wall and a metallic wall second side that faces away from the ceramic wall. The metallic wall and the ceramic wall are spaced apart such that there is a channel there between. There is a seal on the ceramic wall second side, and the metallic wall has at least one cooling hole adjacent the seal for emitting cooling air to cool the seal.

Abstract: A sealing assembly for sealing a gap between a first component and a second component is provided. The sealing assembly includes a sealing body disposed between the first component and the second component and a pressing member disposed between the sealing body and the second component, configured to press the sealing body toward the first component, and configured to extend and compress in a circumferential direction of the first component.

Abstract: An assembly adapted for use in a gas turbine engine has a carrier component and a supported component. The assembly including a mounting system for coupling the supported component to the carrier component and a seal adapted to resist the movement of gasses between the supported component to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine.

Abstract: A mid-turbine frame (MTF”) for a jet engine is disclosed and comprises a duct that extends between a high pressure jet engine turbine (“HPT”) and a low pressure jet engine turbine (“LPT”), the duct comprising a plurality of segments that together form an outer annular structure and an inner annular structure, the inner annular structure situated radially inward of the outer annular structure, and/or a plurality of vanes that extend radially outward from the inner annular structure toward the outer annular structure, each vane comprising a channel. Each segment may be coupled to an adjacent segment by a seal.

Abstract: One exemplary embodiment of this disclosure relates to a stator segment. The stator segment includes a first circumferential end face, and a second circumferential end face. Further, the first and second circumferential end faces are misaligned relative to one another.

Abstract: The present application and the resultant patent provide improved gas turbine component sealing. In one example embodiment, a gas turbine segment seal assembly may include a first tapered segment seal with a first tapered portion having a first tapered surface and a first taper angle. The gas turbine segment seal assembly may include a second tapered segment seal with a second tapered portion having a second tapered surface and a second taper angle. The gas turbine segment seal assembly may include a seal pin positioned in between the first tapered segment seal and the second segment seal and adjacent to the first tapered surface and the second tapered surface.

Abstract: An air filter cartridge has filter media and a gasket arrangement with a perimeter gasket member against the downstream flow face and a side gasket member adjacent to at least a partial extension of a first side panel. The side gasket member includes no portion against second, third, and fourth side panels of the air filter cartridge. The air filter cartridge can be used in a dust collector having a tubesheet and a frame arrangement extending from the tubesheet. The perimeter gasket member seals against the frame arrangement and the side gasket member seals against the tubesheet.

Abstract: A top cover for use in a disk drive apparatus includes a plate made of a metal and a gasket fixed to the plate. The gasket is made of an elastomer. A surface of the plate includes a fixing region to which the gasket is closely adhered. The fixing region includes a plurality of ridges and in plan view a plurality of filamentous projections extending from each of the plurality of ridges. The plurality of ridges are arranged in the fixing region to increase a surface area of the fixing region. The plurality of ridges and the plurality of filamentous projections extending from each ridge are distributed over the fixing region.

Abstract: A seal structure for an electronic control device having a circuit board housed in a watertight space a housing that is formed by fitting a plurality of fitting members together, has first and second seal portions which are formed at a fitting surface portion between the fitting members that are fitted together. One side of a pair of the fitting members of each of the first and second seal portions is provided with a seal groove, the other side is provided with a protruding line. An auxiliary seal groove and an auxiliary protruding line are formed on opposing surfaces of the seal groove and the protruding line at a merged part where the first and second seal portions meet each other. The auxiliary seal groove and the auxiliary protruding line continuously extend from the seal groove up to an end surface of the protruding line.

Abstract: Rotodynamic pumps having an inner drive permanent magnet coupling disposed inside an impeller are provided. The impeller has a casing having a pumping region generally in a pumping plane that is perpendicular to the rotational axis of the impeller and aligned with a permanent magnet coupling that includes outer magnets that are connected to the impeller and at least partially aligned with the pumping region of the impeller, and inner magnets that are connected to an inner magnet ring and are axially aligned with the outer magnets. A canister is sealed to the casing and separates the outer magnets from the inner magnets.

Abstract: Rotodynamic pumps having an inner drive permanent magnet coupling disposed inside an impeller are provided. The impeller has a casing having a pumping region generally in a pumping plane that is perpendicular to the rotational axis of the impeller and aligned with a permanent magnet coupling that includes outer magnets that are connected to the impeller and at least partially aligned with the pumping region of the impeller, and inner magnets that are connected to an inner magnet ring and are axially aligned with the outer magnets. A canister is sealed to the casing and separates the outer magnets from the inner magnets.

Abstract: A seal assembly for an axial flow gas turbine engine includes a rotatable component having a radially extending mate face, a seal slot formed in the mate face, and a seal member slidably disposed in the seal slot. The seal slot includes a radially outer wall and an opposing radially inner wall extending into the component in a circumferential direction from the mate face. The radially outer wall is angled radially inwardly from the mate face toward an inner end portion of the seal slot. Rotation of the seal assembly during operation of the engine produces a centrifugal force on the seal member to effect movement of the seal member in the circumferential direction out of the seal slot.

Abstract: An annular metal gasket for sealing a space between members by being pressed in the vertical direction in a state of being mounted between the members, the metal gasket comprising an annular outer ring having a substantially C-shaped cross-section and having a circumferential-direction opening formed therein, and an annular inner ring fitted inside the outer ring. The inner ring is formed so as to have a polygonal cross-section. Bend parts having an Inner angle larger than 180° are formed between the upper corner part and the inner- and outer-circumference-side corner parts; and between the lower corner part and the inner- and outer-circumference-side corner parts.

Abstract: A spring seal assembly includes a first plate and a second plate. One or more spring elements are located between the first plate and the second plate and compressible therebetween. The spring seal assembly is insertable into a gap between two adjacent components such that at least one of the first plate and the second plate at least partially block a flow between the two adjacent components while exerting a force on the two adjacent components to prevent vibration of the seal in the gap. A method of sealing between adjacent components includes at least partially compressing a spring seal assembly. The spring seal assembly is inserted into the gap and allowed to expand in the gap thereby at least partially blocking a flow between the two adjacent components while exerting a force on the two adjacent components to prevent vibration of the seal in the gap.

Abstract: A spring loaded seal assembly is disclosed for sealing a gap between adjacent turbine components. The seal assembly may generally include a turbine seal and a spring member. The turbine seal may extend between the adjacent turbine components and may be configured to seal the gap defined between the turbine components. The spring member may be configured to engage the turbine seal so as to maintain the seal in sealing engagement with the adjacent turbine components.

Abstract: An annular-gap seal for a valve, blocks the fluid flow from a high-pressure side to a low-pressure side. The valve has a cylinder, through which the fluid flows and in which a piston is axially displaced. In the blocked position, an annular gap between the piston and the cylinder can be sealed by the annular gap seal, which lies in a groove that runs around the cylinder. To increase the sealing action of the gap seal, two sealing rings lie adjacent to one another mirror-symmetrically in the groove. In the blocked position, fluid from the high-pressure side causes a sealing lip of a first sealing ring that faces the low-pressure side to be pressed in a fluid-tight manner against the piston and a sealing face of the first sealing ring to be pressed in a fluid-tight manner against the wall of the groove.

Abstract: A seal comprises a metal seal ring with a first slanted mating surface for sealing engagement with a mating surface on a body and a second slanted mating surface for sealing engagement with a mating surface on a bonnet. The mating surfaces are the same angle as measured from the axis of the ram of the BOP. The seal also defines opposing slanting surfaces which provide a degree of flexure to the seal for sealing engagement. With the application of pressure on the inside surfaces of the seal, the mating surfaces are pressed even harder against the mating surfaces of the body and bonnet.

Abstract: A seal assembly (60) for sealing first and second static parts (40A, 40B) with opposed slots (44A, 44B) together forming a pocket (46). The seal assembly (60) comprises a floor strip (70) positioned adjacent the pocket's floor (48) and a ceiling strip (80) positioned adjacent the pocket's ceiling (50). A connection (90) of the strips' central portions (72, 82) provides a flat hinge between cooperating hinge portions (76, 86). A first set of the hinge portions (76A-86A) converge for insertion into the first slot (44A) and a second set of hinge portions (76B-96B) converge for insertion into the second slot (44B). After such slot insertion and pocket installation, the converged hinge portions (76A-86A, 76B-86B) resiliently diverge within the pocket to seat the floor strip's end portions (74A, 74B) against the pocket's floor (48) and to seat the ceiling strip's end portions (84A, 84B) against the pocket's ceiling (50).

Abstract: Dock leveler seals and associated methods and systems are described herein. A dock leveler having a rear hinge seal configured in accordance with one embodiment of the disclosure includes a rear support frame and a movable deck. The rear support frame includes a plurality of first support members extending therefrom, and the aft edge portion of the deck includes a plurality of second support members pivotally coupled to the first support members along an axis. The seal of this embodiment includes a first edge portion extending outwardly from a medial portion in a first direction, and a second edge portion extending outwardly from the medial portion in a second direction. The medial portion urges the first edge portion against the support frame and the second edge portion against the aft edge portion of the deck as the deck pivots about the axis in operation.

Abstract: The present invention features a flange to flange dynamic seal and sealing system, particularly suited for use within high temperature, high pressure environments, such as a delayed coking process. The dynamic flange seal and sealing system comprises two primary elements or seals, each of which are capable of independently forming a flange seal between two flanged components or combining to create a flange seal. Specifically, these primary seals are an iconel bellows seal and a bi-material gasket, each of which surround a flange opening along a sealing surface. The flange seal created by the dynamic flange seal and sealing system is capable of being maintained in light of, or rather the sealing system adapts to, any structural or environmental changes within the connected flanges. As such, the flange seal may be a dynamic flange seal or a static flange seal or both.

Abstract: A heat shield according to the invention on a support structure comprises a number of heat shield elements, which are configured and arranged on the support structure such that they abut each other leaving gaps. The support structure of the heat shield according to the invention has a peripheral direction and an axial direction, the heat shield elements abutting each other in the peripheral direction of the support structure leaving a gap, hereafter referred to as a peripheral gap, and in the axial direction of the support structure leaving a gap, hereafter referred to as an axial gap. Both the peripheral gaps and the axial gaps are also sealed by sealing elements, the sealing elements sealing the axial gaps being at a different distance from the support structure from the sealing elements sealing the peripheral gaps.

Abstract: An aft closure assembly manufactured from two separate and distinct pieces made from different materials is provided for a rocket motor case. The aft closure assembly includes at least a retaining ring piece made from a first material similar to or having a coefficient of thermal expansion similar to that of the motor case. The aft closure assembly includes a blast tube and closure piece that can be manufactured from a second material that does not need to be similar to nor have a coefficient of thermal expansion similar to the motor case and retaining ring piece. This is possible because the blast tube and closure piece includes a face seal that seals against a face of the retaining ring.

Abstract: A transparent vehicle license plate frame has an elastomeric gasket. The frame includes a periphery and an inner side for disposal adjacent to a license plate. The elastomeric gasket is disposed on the inner side near the periphery of the frame and is injection-molded into an annular frame channel.

Abstract: A seal rubber 3 is placed in a first peripheral groove 2 formed in one main surface 1A of an approximately flat-plate-shaped metal body 1. A second peripheral groove 4 and multiple communicating holes 5 to communicate between the second peripheral groove 4 and the first peripheral groove 2 are formed in the other main surface 1B of the metal body 1. A retaining rubber 6 disposed in the second peripheral groove 4, the seal rubber 3, and a bridge rubber 7 disposed in the communicating hole 5 are integrated. The first peripheral groove 2 is made to be a dovetail groove, the second peripheral groove 4 is made to have an inner surface inclined to reduce the groove width from a groove opening side to a groove bottom surface side, and the groove width D4-2 of the groove bottom surface and the inner diameter D3 of the communicating hole 5 are made to be substantially the same.

Abstract: An apparatus includes a crankshaft provided with a first bearing and a second bearing. The apparatus further includes a first bearing seal positioned adjacent the first bearing and a second bearing seal positioned adjacent the second bearing. The apparatus further includes a preformed one-piece seal including a first endless loop, a second endless loop and a first intermediate seal portion connected between the first and second endless loops. The first endless loop engages a peripheral surface of the first bearing seal while the second endless loop engages a peripheral surface of the second bearing seal.

Abstract: A seal for sealing a seal groove in a shroud of a turbine vane. The seal may include a cooling system configured to pass cooling fluids through a cooling fluid supply port in a shroud, through a cooling system in which the cooling fluids contact the shroud and the seal, and exhaust the fluids through a gap between adjacent turbine vanes. The seal may include an elongated cooling channel for channeling cooling fluids from a supply to an exhaust channel at a first end. The cooling system may remove heat from the turbine vane shroud, the seal, and other related components, thereby reducing the likelihood of premature failure.

Abstract: A sealing construction provided with a plate member of metal and a rubber member forming a sealing portion and unitedly fixed to the plate member on which a ring concave groove is formed on an obverse face. And, plural through holes, having enlarged opening end portions on a reverse face, are formed through a bottom face of the ring concave groove and the reverse face. Further, a ring plate is disposed as to contact the bottom face of the ring concave groove and partially close the opening portions of the through holes toward the bottom face, and the rubber member, fit to the through hole and surrounding the ring plate, is unitedly connected to the sealing portion in the ring concave groove.

Abstract: A sealing arrangement that can be employed to maintain a seal in any suitable pressure vessel including but not limited to a gas turbine engine. The sealing arrangement is forg sealing a leakage gap between at least two relatively moveable parts that are adjacent to each other in a flow path between a region of high fluid pressure and a region of low fluid pressure. The sealing arrangement comprises at least two resilient sealing strips, each strip having a portion formed along at least part of its width to locate in a groove provided along adjacent faces of the relatively moveable parts. The remaining portion of each of the sealing strips has a substantially flat surface which, in operation, abuts a corresponding flat surface of an adjacent sealing strip, thereby forming a seal.

Abstract: A turbine engine shroud segment having a body including a circumferentially arcuate radially inner surface defining a circumferential arc and a radially outer surface is provided, at least at one axially spaced apart outer surface edge portion surface, with a surface depression extending circumferentially across the outer edge portion and including a planar seal surface. The planar seal surface is spaced apart radially outwardly from the circumferential arc defining a spaced apart chord of the arc. The planar seal surface is joined with the segment body radially outer surface through an arcuate transition surface. In a circumferential assembly of a plurality of the shroud segments into a turbine engine shroud assembly, at least one of the outer surface edge portions and its respective depression portion and fluid seal surface is distinct axially from an axially juxtaposed engine member by a separation therebetween.

Abstract: A biased, wear resistant seal assembly for sealing gas flow paths in a turbine system includes a planar shim having transverse legs at each end, a flattened leaf spring to urge the shim into sealing contact with the sealing surfaces of the turbine parts, and a shim protection material to avoid wear to the shim on the contact side. The shim protection material can include one or more metal fiber cloth layers secured to the shim, for example, by seam welding to a pair of rails or to the legs of the shim.

Abstract: A lathe cut sealing ring includes a substantially cylindrical ring of elastomeric material formed about a central axis. The ring includes a rectangular cross-section and has an inner diameter, an outer diameter, opposite planar upper and lower surfaces, and a plurality of angularly spaced positioning ribs protruding inwardly from the inner diameter. This sealing ring and the groove in which it is located can advantageously be formed with simple and cost-effective lathe cutting operations.

Abstract: Cooling is facilitated in stationary flowpath components, such as turbine nozzle segments and shrouds, by providing circumferential edges defining a non-linear curvature that matches the curvature of the flow line defined by the gas flow past the stationary flowpath component. A flexible seal member is provided to accommodate the non-linear edges.

Abstract: A rotating blade group 90 for a turbo-machine having an improved device for sealing the gap 110 between the edges 112,114 of adjacent blade platforms 96,104. The gap 110 between adjacent blades 92,100 is sealed by a seal pin 20 its central portion 110 and by a seal plate 58,60 at each of the front 54 and rear 56 portions. The seal plates 58,60 are inserted into corresponding grooves 62,64 formed in the adjacent edges 112,114 of adjoining blades 92,100 and held in place by end plates 40,42. The end of the seal plates 58,60 may be chamfered 78,80 to improve the seal against the end plate 40,42. The seal pin 20 provides the required damping between the blades 92,100 and the seal plates 58,60 provide improved sealing effectiveness.

Abstract: A seal for use in spherical disc type butterfly valves. The seal is T-shaped on the inside diameter region where contact is made with the disc and is cupped on radially opposite sides by contoured lips on the seal retainer ring and valve body such that the seal cannot be deformed by pressure by being pressed radially outwardly but rather is cupped by lips of retainer and valve body. The seal also has a rectangularly shaped region on the outside diameter for press fitting into the valve body. The seal has a groove containing a compressed spring element. The seal allows slight twisting motion about the fixed base region and radially toward the compressed spring element such that the seal can move axially with the disc under pressure to maintain uniform sealing contact with the disc without the seal becoming damaged.

Abstract: A seal assembly that seals a gap formed by a groove comprises a seal body, a biasing element, and a connection that connects the seal body to the biasing element to form the seal assembly. The seal assembly further comprises a concave-shaped center section and convex-shaped contact portions at each end of the seal body. The biasing element is formed from an elastic material and comprises a convex-shaped center section and concave-shaped biasing zones that are opposed to the convex-shaped contact portions. The biasing element is adapted to be compressed to change a width of the seal assembly from a first width to a second width that is smaller than the first width. In the compressed state, the seal assembly can be disposed in the groove. After release of the compressing force, the seal assembly expands. The contact portions will move toward a surface of the groove and the biasing zones will move into contact with another surface of the groove.

Abstract: A turbine spline seal includes an elongated turbine seal member. The seal member has an elongated, imperforate, and manually-flexible first portion and a manually-rigid second portion lengthwise adjoining the first portion. The turbine assembly includes the turbine spline seal and also includes first and second turbine members. The first and second turbine members are spaced apart to define a fluid-path leakage gap therebetween, and the seal member is placed in the gap. Each lengthwise edge of the seal member engages a respective one of two opposing surface grooves of the first and second turbine members.

Abstract: The invention relates to a boot seal for a ball and socket joint having a boot seal. The boot seal includes a bulb on a sealing lip. The bulb is compressed within a compression nest that is defined between cooperating radial notches that are formed on the socket ceiling and a bearing surface, respectively, when the bearing is fully installed in the housing. The radial notch in the socket ceiling serves to hold the boot seal in place to permit an assembled bearing and a ball stud assembly to be inserted within the cavity and thereby mechanically secure the boot seal within the socket.

Abstract: A seal plate at the platform portion of a gas turbine moving blade. The seal plate is inserted in a gap between the adjacent platforms at each end portion of a seal pin to prevent air from leaking to the outside. A groove is provided at each of four corners of the end portion of platform of the moving blade, and the seal plate is inserted to cover the gap so as to extend the end portions of the adjacent platforms, by which the gap between the platforms is blocked. A seal pin and end seal pins are inserted between the platforms to seal this portion. However, there is a gap at the end portions, so that cooling air leaks from the lower part of platform. Since the seal plate is inserted in the groove to block the gap, the sealing property is increased.

Abstract: Seal plates for gas turbine stationary blade inner shrouds are made in a double cross type seal structure with a view to enhance sealing ability. Seal plates 1, 2 are mutually lapped and disposed in a turbine axial direction between inner shrouds 12 of stationary blades 11. End portion seal plate 5 is lapped on an end portion of the seal plate 2 and end portion seal plate 6 is lapped under an end portion of the seal plate 1. All these seal plates are fitted with their side end portions being inserted into groove 9a provided in the inner shrouds 12. Seal plates 3, 4 and seal plates 7, 8 engaged with the seal plates 3, 4 are also fitted between flange portions of the inner shrouds 12 with their side end portions being inserted into grooves 10a, 10b and grooves 9b, 9c, respectively.

Abstract: Disclosed is a method for implementing a vacuum seal between an interface of a transport chamber interface port of a transport chamber and another chamber. The transport chamber being configured to mate with the another chamber in an adjacent relationship. The method includes placing an insert plate having a sealing surface containing a first O-ring into the transport chamber interface port such that the first O-ring is sandwiched between the sealing surface and a surface of the another chamber. Therefore, a vacuum seal is achieved between the transport chamber and the another chamber within the transport chamber interface port via the first O-ring.

Abstract: A sealing element seals a gap which may be formed between two components that are movable thermally relative to one another. Each component has a component groove located one opposite the other. The sealing element is directed along a center line, in a cross-section essentially perpendicular to a main line, and has a first end, a second end located opposite the first end and a toothed middle region located between the ends. The sealing element is suitable in particular for sealing off a gap between guide blades at high temperatures in a gas turbine plant for the purpose of preventing a gas flow out of a cooling-gas region into a hot-gas region. A gas turbine plant is provided with the sealing element for sealing the gap.

Abstract: A gas-path leakage seal for generally sealing a gas-path leakage-gap between spaced-apart first and second members of a turbine (such as combustor casing segments of a gas turbine). The seal includes a flexible and generally imperforate metal sheet assemblage having opposing first and second surfaces and two opposing raised edges extending a generally identical distance above and below the surfaces. A first cloth layer assemblage has a thickness generally equal to the previously-defined identical distance and is superimposed on the first surface between the raised edges. A second cloth layer assemblage is generally identical to the first cloth layer assemblage and is superimposed on the second surface between the raised edges.

Abstract: A seal for stator vane segments within a gas turbine engine is provided which includes an axial member and an end member. The axial member includes a central portion and at least one axial joint element extending out from the central portion. The central portion has across-section which includes a pair of substantially u-shaped circumferential ends connected by an arcuate midsection. The axial joint element transitions from the arcuate midsection to a substantially flat end. The end member includes an end joint element attached to a radial portion. The axial and end joint elements contact each other to prevent leakage therebetween, and also sidably cooperate with each other to accommodate misalignment between the axial member and the end member.

Abstract: A baffle plate (12A) is constructed such that two belt-like elements, bent in a warped arc, are joined by spot welding (13) or brazing (14) at a central portion thereof along a central circumferential portion. Thus, even if there is a difference in a radial directional deflection of grooves (11) between adjacent discs (9), the baffle plate (12A) will maintain close contact with the inner surfaces of the grooves (11) due to a spring effect and gas leakage is thereby prevented.