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Between blade edge and static part

Subclass of:

415 - Rotary kinetic fluid motors or pumps

415170100 - BEARING, SEAL, OR LINER BETWEEN RUNNER PORTION AND STATIC PART

Patent class list (only not empty are listed)

Deeper subclasses:

Class / Patent application numberDescriptionNumber of patent applications / Date published
415173400 Erodable or permanently deformable 39
415173300 Resilient, flexible, or resiliently biased 20
415173500 Labyrinth seal 8
415173200 Selectively adjustable 8
Entries
DocumentTitleDate
20090047122Fan outlet guide vane shroud insert repair - A method of repairing a turbine engine component that contains a series of lined apertures. The component is removed from the engine, and then at least one of the aperture liners is also removed. The area adjacent the aperture is machined to remove a portion of the parent material of the component. An insert which replaces the material removed by machining is secured adjacent the aperture. The liner about the aperture is then replaced.02-19-2009
20120171023MOUNTING APPARATUS FOR LOW-DUCTILITY TURBINE SHROUD - A turbine shroud apparatus for a gas turbine engine having a central axis includes: an arcuate shroud segment comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces and collectively defining a shroud cavity; an annular stationary structure surrounding the shroud segment; and a load spreader received in the shroud cavity of the shroud segment and mechanically coupled to the stationary structure. The load spreader includes: a laterally-extending plate with opposed inner and outer faces; and a boss which protrudes radially from the outer face and extends through a mounting hole in the outer wall of one of the shroud segments. A fastener engages the boss and the stationary structure, so as to clamp the boss against the stationary structure in a radial direction.07-05-2012
20090142187SEALS IN STEAM TURBINE - A seal structure for a steam turbine is provided, which is capable of suppressing transfer of heat generated by a friction between a rotating portion and a fixed portion to the rotating portion and of suppressing an increase in the temperature of the rotating portion. A labyrinth seal device serves to suppress the amount of steam leaking from a clearance present between each stator blade (fixed portion) of the steam turbine and a rotor (rotating portion). The seal structure for the steam turbine is formed to ensure that permeable spacers made of a permeable metal are provided on the rotor and a seal stationary body and face respective seal fins provided in the labyrinth seal device.06-04-2009
20090191049TURBOJET COMPRESSOR - The invention relates to a turbojet compressor comprising a shroud and a plurality of blades, each fixed via its root to the shroud. Level with each blade root, the shroud presents a suction-side ramp and a pressure-side ramp extending from the trailing edge of the blade to beyond its leading edge. The pressure-side and suction-side ramps join together upstream from the leading edge of the blade to form a projection presenting a profile that is twisted about the axis of the shroud so as to force the gas stream flowing in each flow passage to go round the blade root essentially on the suction-side thereof, and the suction-side ramp presents a profile that is inclined relative to the outside surface of the shroud so as to deflect the gas stream flowing in the corresponding flow passage from the suction-side surface of the blade towards the pressure-side surface of the adjacent blade.07-30-2009
20100034644HYBRID SEAL ASSEMBLY FOR A FAN-TURBINE ROTOR OF A TIP TURBINE ENGINE - The hybrid seal assembly includes a seal for use with rotating surfaces which may suffer significant deflections such as for sealing between flanges and mating surfaces typical of annular seal face surface of a diffuser section of a tip turbine engine.02-11-2010
20120243976TURBINE SHELL WITH PIN SUPPORT - A turbine is provided and includes a turbine shell including shrouds at multiple stages thereof, and constraining elements, disposed at least at first through fourth substantially regularly spaced perimetrical locations around the turbine shell, which are configured to concentrically constrain the shrouds of the turbine shell.09-27-2012
20130034428SEGMENTED SEAL ASSEMBLY - Systems and devices for sealing portions of a rotary machine are disclosed. In one embodiment, a seal assembly element includes: a head flange; an axial neck connected to the head flange, wherein the axial neck includes a mating flange extending circumferentially from a distal end of the seal assembly element, the mating flange configured to form a multidirectional seal with a recessed portion of a complementary seal assembly element; and a set of axial seal teeth connected to the axial neck.02-07-2013
20130078084AIRFOIL AIR SEAL ASSEMBLY - An air seal assembly for a gas turbine engine the air seal comprises a first assembly and a second assembly. One of the first assembly and the second assembly is rotatable relative to the other of the first assembly and the second assembly. The second assembly is aligned annularly with the first assembly and includes a circumferential surface with an abradable coating disposed annularly adjacent to the first and second airfoil tips. The first assembly includes at least one first airfoil with a first tip having an abrasive coating, and at least one second airfoil with a second tip absent the abrasive coating, the at least one first airfoil co-aligned axially and intermingled with a respective at least one second airfoil around a periphery of the first assembly.03-28-2013
20100104428Molecular drag pumping mechanism - A vacuum pump comprises a drive shaft and a Siegbahn pumping mechanism. The Siegbahn pumping mechanism comprises a rotor element located on the drive shaft and an annular stator element located about the drive shaft and proximate the rotor element, the stator element comprising a plurality of walls extending towards the rotor element and defining a plurality of spiral channels. The stator element comprises a plurality of sections, with means such as a resilient member being located about the sections to urge the sections together, and thereby inhibit gas leakage between the sections of the stator element. The resilient member can also form a seal between the stator sections and a casing located about the pumping mechanism.04-29-2010
20100104427PRESSURE ACTIVATED FLOW PATH SEAL FOR A STEAM TURBINE - A pressure activated flow path seal for a steam turbine is disclosed. In one embodiment a gap closure component is located about a rotary component and the stationary component of the steam turbine. A pressure differential activates the gap closure component to seal or reduce the radial clearance of a steam leakage path between the rotary component and the stationary component.04-29-2010
20100104426TURBINE ENGINE RING SEAL - Aspects of the invention relate to a ring seal for a turbine engine. The ring seal can be made up of a plurality of circumferentially abutted ring seal segments. Each ring seal segment can comprise a plurality of individual channels. The channels can be generally U-shaped in cross-section with a forward span, and aft span and an extension connecting therebetween. The channels can be positioned such that the aft span of one channel can substantially abut the forward span of another channel. The plurality of separate channels can be detachably coupled to each other by, for example, a plurality of pins. The ring seal segment according to aspects of the invention can facilitate numerous advantageous characteristics including greater material selection, selective cooling, improved serviceability, and reduced blade tip leakage. Moreover, the configuration is well suited to handle the operational loads of the turbine.04-29-2010
20130084166SEGMENTED COMPONENT - A component, in particular for a gas turbine, is disclosed. The component has at least two component segments which are arranged relative to one another leaving a gap and are sealed against each other by a sealing device. The sealing device includes at least one brush seal. Also disclosed is a gas turbine, in particular an aircraft engine, having such a component.04-04-2013
20130084167WEAR-RESISTANT COATING AND USE THEREOF - A rotor blade 04-04-2013
20100266391MECHANICAL ATTACHMENT OF CERAMIC OR METALLIC FOAM MATERIALS - A thermal barrier includes a thermal barrier member having at least one material selected from a metal foam or a ceramic foam. The thermal barrier member includes an attachment section for securing the thermal barrier member with a corresponding attachment section of a support.10-21-2010
20090304498MULTISTAGE TURBOMACHINE COMPRESSOR - A multistage compressor for a turbomachine, in particular an airplane turboprop or turbojet, the compressor comprising a double-walled casing having an inner wall made up of shrouds surrounding respective annular rows of moving blades and annular rows of straightening stator vanes, said shrouds being connected to the outer wall of the casing by independent suspension means enabling the radial clearances between the outer ends of the moving blades and the shrouds of the inner wall of the casing to be adjusted independently from one compression stage to another.12-10-2009
20130058765ROTARY MACHINE SEAL ASSEMBLY WITH BUTT GAP SEAL ELEMENTS - Systems and devices for substantially fluidly isolating portions of a rotary machine are disclosed. In one embodiment, a seal assembly for a rotary machine includes: a complementary set of seal segments configured relative one another so as to form a substantially continuous body with butt gaps between the seal segments, the segments including: a head flange; and an axial neck connected to the head flange, wherein the axial neck extends radially inboard and includes an axial slot formed substantially there through; and at least one butt gap seal element, wherein the at least one butt gap seal element includes an axial flange and a radial flange, the axial flange disposed within the axial slots of adjacent seal segments; and the radial flange extending radially inboard from the axial slots to a proximity of the rotary machine substantially forming a barrier to axial flow through the butt gap.03-07-2013
20130058764STEPPED, CONICAL HONEYCOMB SEAL CARRIER - A seal carrier for a seal used between rotating and non-rotating components includes an arcuate sheet metal seal carrier body formed to include a stepped, conical configuration wherein an inner diameter at a forward end is larger than the diameter at an aft end, with plural stepped sections defined by alternating radial and axial portions between the forward end and the aft end. Each axial portion is adapted to carry a seal element, preferably a honeycomb seal. Mounting flanges are provided at the forward end and the aft end of the arcuate sheet metal seal carrier body to enable attachment to the non-rotating component.03-07-2013
20090269188SHROUD SEGMENT ARRANGEMENT FOR GAS TURBINE ENGINES - The gas turbine engine shroud comprises a plurality of circumferentially-disposed and concentric shroud segments. Each shroud segment has an arc-shaped platform with opposite ends, each end comprising an inter-segment seal slot, at least one slot extending substantially across each corresponding end and having a lengthwise-variable depth.10-29-2009
20130164119SEAL STRUCTURE AND CENTRIFUGAL COMPRESSOR - Provided is a seal structure (06-27-2013
20090246006Mechanically Affixed Turbine Shroud Plug - A sealing interface for a component in a turbine machine, wherein a plug is mechanically affixed within an entrance passage of an aperture. The plug is secured in place within the entrance passage through deformation of an inner end of the plug to cause the plug to mechanically engage a groove formed adjacent the entrance passage.10-01-2009
20090010754Bearing-Like Structure to Control Deflections of a Rotating Component - A bearing like surface on a stationary component reduces deflection of an adjacent rotating component. The stationary component is generally parallel to and offset from a rotational component. The rotational component rotates about a central axis. Protrusions located on the stationary component are in contact with the rotational component to prevent deflection of the rotational component while reducing the friction between the rotational and stationary component. The protrusions have a generally flat surface that may be used to affix the protrusions to the stationary component. An arced surface of the protrusions is in contact with the rotating component. The number, size and the shape of the protrusions are determined by the requirements of the application.01-08-2009
20110044803BLADE OUTER AIR SEAL ANTI-ROTATION - A blade outer air seal (BOAS) assembly includes a static turbine shroud formed by BOAS segments and a support ring formed by BOAS support segments. Each BOAS support segment supports one or more BOAS segments. The BOAS assembly further includes an anti-rotation apparatus for restricting relative circumferential movement between the turbine shroud and the support ring. The anti-rotation apparatus includes a stopper provided at least in one of the BOAS support segments and a cast anti-rotation tab integrated with at least one of the BOAS segments supported on that at least one BOAS support segment. The stopper and cast anti-rotation tab circumferentially abut each other.02-24-2011
20110129335Rotor Assembly for a Reheat Steam Turbine - A caseless rotor assembly is provided. The caseless rotor assembly includes a rotor shaft, a high pressure portion with a high pressure rotor blade, a low pressure portion with a low pressure rotor blade, and a common wall between the high pressure portion and the low pressure portion. The common wall extends radially from the rotor shaft. The common wall itself includes a shaft end oriented towards the rotor shaft and an outer end on the other side of the common wall, oriented radially outwards. Additionally, the common wall surrounds circularly the rotor shaft.06-02-2011
20110293410LOW-DUCTILITY TURBINE SHROUD AND MOUNTING APPARATUS - A turbine shroud apparatus for a gas turbine engine includes an arcuate turbine shroud segment of low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces. At least a portion of each of the forward and aft walls is oriented at an acute angle to the outer wall. Radially inner ends of the forward and aft walls are substantially closer together than radially outer ends thereof.12-01-2011
20090148277Gas Turbine Engines and Related Systems Involving Blade Outer Air Seals - Gas turbine engines and related systems involving blade outer air seals are provided. In this regard, a representative blade outer air seal assembly for a gas turbine engine includes: an annular arrangement of outer air seal segments, each of the segments having ends, the segments being positioned in an end-to-end orientation such that each adjacent pair of the segments forms an intersegment gap therebetween, each intersegment gap being defined, at least partially, by a first recess and a first protrusion, the first protrusion being sized and shaped to be received by the first recess, one of the first recess and the first protrusion being located on an end of a first segment of an adjacent pair of the segments, another of the first recess and the first protrusion being located on an end of a second segment of the adjacent pair of the segments.06-11-2009
20120288360TURBINE - A turbine (11-15-2012
20110299976COMPOSITE GAS TURBINE ENGINE COMPONENT - A gas turbine engine component is disclosed having a composite construction. In one embodiment the gas turbine engine component is a blade that includes a shroud. A fiber ply of the composite construction extends from an airfoil part of the blade to the shroud. The shroud can include multiple plies that can be stitched together. In one form a sealing knife is formed and coupled to the shroud. The sealing knife can be coupled to the shroud by stitching. Filler material can be used in the composite construction of the gas turbine engine component.12-08-2011
20090053045Turbine Shroud for Gas Turbine Assemblies and Processes for Forming the Shroud - A gas turbine assembly includes a shroud that includes a plurality of interconnected shroud segments, wherein each one of the shroud segments comprises an arcuate base formed of a first metal material. The arcuate base is made up of an annular member having an axial component and a pair of upstanding ribs having flanges, wherein the arcuate base further comprises a high temperature capable material layer disposed on a surface of the arcuate base so as to define an inner diameter of the shroud segment (i.e., the hot gas path side or environmental side).02-26-2009
20100143102COMPLIANT PLATE SEAL WITH SELF-CORRECTING BEHAVIOR - A self-correcting seal assembly comprises a plurality of compliant plates coupled circumferentially to a stationary component, at least one slot in the compliant plates extending from the stationary component towards a rotor; and a resistance member coupled to a stationary component. The resistance member comprising at least one annular ring extending from the stationary component towards a rotor and through the slot. The seal assembly is configured to create passive feedback on hydrostatic forces in response to a tip-clearance between the rotor and tips of the compliant plates.06-10-2010
20090087306BLADE OUTER AIR SEALS, CORES, AND MANUFACTURE METHODS - A blade outer air seal (BOAS) casting core has first and second end portions and a plurality of legs. Of these legs, first legs each have: a proximal end joining the first end portion; a main body portion; and a free distal portion. Second legs each have: a proximal end joining the second end portion; a main body portion; and a free distal portion.04-02-2009
20090169368BLADE OUTER AIR SEAL - A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. The body comprises a metallic member and a ceramic member. The ceramic member and metallic member are joined along the base portion with the ceramic member inboard of the metallic member.07-02-2009
20090285675Systems and Methods for Modifying Modal Vibration Associated with a Turbine - Shroud assemblies and methods for modifying modal vibrations associated with a turbine are described. A shroud assembly includes an inner shroud and an outer shroud. The inner shroud includes a body with a first end portion, a second end portion opposite to the first end portion, an upper surface and a lower surface, wherein the lower surface is adjacent to a plurality of rotating turbine blades. The inner shroud further includes at least two rails formed on the upper surface and extending between the first end portion and the second end portion, wherein an impingement cooling area is defined between the at least two rails. Additionally, the inner shroud includes at least one cross-member formed on the upper surface in a direction transverse to the at least two rails.11-19-2009
20110171010Sealing System Between a Shroud Segment and a Rotor Blade Tip and Manufacturing Method for Such a Segment - An arrangement including a turbine blade is provided. The turbine blade includes at least a root, an airfoil and a tip which is mounted to a rotor by means of the root. The rotor extends along a machine axis. The arrangement also includes a circumferential casing segment which includes a surface. The surface faces tips of the blades, wherein the surface is structured. A method to produce a casing segment is also provided. In order to increase efficiency without limiting the operational range of the turbine, the surface is provided at least partially with an at least partially ceramic coating. The method includes machining a first structure into the surface and providing the surface with a ceramic coating.07-14-2011
20090104026CONTROL OF CLEARANCE AT BLADE TIPS IN A HIGH-PRESSURE TURBINE OF A TURBINE ENGINE - Turbine stage in a turbine engine, including a wheel with blades rotating inside a sealing ring (04-23-2009
20090104025Gas Turbine Engines and Related Systems Involving Blade Outer Air Seals - Gas turbine engines and related systems involving blade outer air seals are provided. In this regard, a representative blade outer air seal assembly for a gas turbine engine includes: an annular arrangement of outer air seal segments defining an inner diameter surface; intersegment gaps located between the outer air seal segments, each of the gaps being located between a corresponding adjacent pair of the segments; and recesses spaced about the inner diameter surface, each of the recesses communicating with a corresponding one of the gaps.04-23-2009
20080267770SEAL - A turbofan gas turbine engine (10-30-2008
20100202875COMPRESSOR-SIDE SHAFT SEAL OF AN EXHAUST-GAS TURBOCHARGER - The piston ring sealing points of a sealing apparatus between the rotor and the housing of a continuous-flow machine each have a piston ring, a cylindrical contact surface, which is directed radially inward, on the housing, as well as an axial stop on the rotor. In this case, the piston ring of the outer piston ring sealing point has a larger external radius and a smaller internal radius than the piston ring of the inner piston ring sealing point. At the same time, the outer piston ring sealing point has a smaller internal radius than the inner piston ring sealing point. Because of the V-shaped arrangement concept, there is no need for a steel ring, shrunk onto the rotor, between the piston ring sealing points.08-12-2010
20100143101COMPLIANT FOIL SEAL FOR ROTARY MACHINES - A compliant foil seal comprises a bottom foil configured to be located circumferentially around at least a portion of a rotor, and one or more upper foils configured to cooperate with a stator to position the bottom foil to compliantly face the rotor and be located between the stator and the rotor. A compliant foil seal assembly and a rotary machine are also presented.06-10-2010
20100135775TURBOMACHINE, ESPECIALLY STEAM TURBINE - A turbomachine includes a turbine stage having a plurality of blades including a first and a second blade disposed adjacent to each other, each blade having a radial longitudinal axis and a blade tip and configured to twist around the radial longitudinal axis in an operating state in a twist direction, wherein the first and the second blades are pretwisted in a direction of twist in a non-operating state, and wherein a connecting element interconnects the first and the second blades to each other in a circumferential direction in a region of the respective blade tip so as to maintain the pretwisting.06-03-2010
20120195742TURBINE BUCKET FOR USE IN GAS TURBINE ENGINES AND METHODS FOR FABRICATING THE SAME - A turbine bucket for use with a turbine engine. The turbine bucket includes a dovetail that is coupled to a rotor assembly that is positioned within a turbine casing. A platform extends from the dovetail. An airfoil extends from the platform. The airfoil includes a root end and a tip end. The tip end extends outwardly from the root end towards the turbine casing. A tip shroud extends from the tip end. The tip shroud includes a shroud plate. A first shroud rail extending a first radial distance from the shroud plate towards the turbine casing. A second shroud rail extends a second radial distance from the shroud plate towards the turbine casing that is different than the first radial distance.08-02-2012
20090129917SEALING A ROTOR RING IN A TURBINE STAGE - A turbine stage in a turbomachine, the stage comprising a wheel mounted in a ring carried by a turbine casing, and a nozzle situated upstream from the wheel and including an annular fastener rim for fastening to the turbine casing, sealing being provided between the outer rim of the nozzle and the upstream end of the ring by a radial annular sheet bearing axially at its inner and outer peripheries against a downstream face of the outer rim of the nozzle, with its middle annular portion being axially spaced apart from the outer rim of the nozzle and bearing axially against the upstream end of the ring.05-21-2009
20120070272METHOD FOR PRODUCING METAL ELEMENTS, IN PARTICULAR SEALING ELEMENTS - A method for producing metallic elements, and more particularly sealing elements, wherein a sheet metal strip or a foil strip having a predefinable length, width, and thickness is generated and the sheet metal strip or foil strip is formed to obtain a tube, the mutually opposing end regions or parts, or the entire contact surface of the sheet metal strip or foil strip, are connected to each other non-positively or positively or by bonding, or combinations thereof, and the entire length of the tube, or portions thereof, is subjected to a mechanical shape-forming process so that predefinable contours are introduced into the outer or inner circumferential surface of the tube in defined locations by a means, and the tube is divided into an appropriate number of individual elements, and in particular sealing elements, especially sealing rings for turbochargers.03-22-2012
20090053047Turbine bucket tip shroud edge profile - A turbine bucket includes a bucket airfoil having a tip shroud with a leading edge comprising two scalloped faces and a trailing edge comprising a third scalloped face defining leading and trailing edge profiles substantially in accordance with Cartesian coordinate values of X and Y as points 1-41 set forth in Table I. The X and Y values are distances in inches which, when respective points are connected by smooth, continuing arcs define the leading and trailing edge tip shroud scalloped profiles. The tip shroud further has first and second, upper and lower, Z form edge profiles substantially in accordance with Cartesian coordinate values of X and Y as points 42-59 and 60-77, respectively of Table II.02-26-2009
20090053048STEAM TURBINE - A steam turbine has a stationary section, a turbine rotor, nozzle diaphragms, a steam passage section, a nozzle box and a sealing. The stationary section includes a casing. The turbine rotor includes moving blade stages. Each of the moving blade stages has turbine moving blades. Each of the nozzle diaphragms has turbine nozzles. The moving blade portions and the turbine nozzle portions constitute the steam passage. The nozzle box is held by the stationary section and arranged at an upstream side of the steam passage coaxially with the turbine rotor. The sealing divides a space between the turbine rotor and the casing into a first space provided at an inner side and a second space provided at an outer side of the nozzle box.02-26-2009
20100150703STACKED LAMINATE BOLTED RING SEGMENT - A ceramic ring segment for a turbine engine that may be used as a replacement for one or more metal components. The ceramic ring segment may be formed from a plurality of ceramic plates, such as ceramic matrix composite plates, that are joined together using a strengthening mechanism to reinforce the ceramic plates while permitting the resulting ceramic article to be used as a replacement for components for turbine systems that are typically metal, thereby taking advantage of the properties provided by ceramic materials. The strengthening mechanism may include a bolt or a plurality of bolts designed to prevent delamination of the ceramic plates when in use by keeping the ceramic plates in compression.06-17-2010
20090116956MANUFACTURABLE AND INSPECTABLE COOLING MICROCIRCUITS FOR BLADE-OUTER-AIR-SEALS - A method for manufacturing a cooling microcircuit in a blade-outer-air-seal is provided. The method broadly comprises the steps of forming a first section of the blade-outer-air-seal having a first exposed internal wall, forming a second section of the blade-outer-air-seal having a second exposed internal wall, and forming at least one cooling microcircuit on at least one of the first and second exposed internal walls.05-07-2009
20100158674ADAPTIVE COMPLIANT PLATE SEAL ASSEMBLIES AND METHODS - A steam turbine comprises a steam turbine casing, a rotor, and at least one compliant plate seal assembly situated between the casing and the rotor. The compliant plate seal assembly comprises a supporting member being stationary with respect to the casing, a plurality of plate members movably mounted to the supporting member and extending towards the rotor, each plate member being inclined with respect to a rotation direction of the rotor, and an actuator for selectively exerting a pressure to retract the plate members in a direction away from the rotor.06-24-2010
20120243975COMPRESSOR AIRFOIL WITH TIP DIHEDRAL - An airfoil for a compressor is described. The airfoil has a root, an airfoil tip, a leading edge, a trailing edge, airfoil pressure and suction sides extending between the leading edge and the trailing edge. The airfoil has an inner span region and an outer span region and the trailing edge has a dihedral profile such that the trailing edge dihedral angle decreases in at least a portion of the inner span region and the outer span region.09-27-2012
20100226760TURBINE ENGINE SEALING ARRANGEMENT - An example turbine engine sealing arrangement includes a blade array rotatable about an axis. The blade array has a plurality of blades extending radially from the axis. A control ring is circumferentially disposed about the blade array. A plurality of tiles are secured relative to the control ring and configured to establish an axially extending seal with one of the blades.09-09-2010
20100247297ACTIVE TIP CLEARANCE CONTROL ARRANGEMENT FOR GAS TURBINE ENGINE - An active tip clearance control (ATCC) apparatus of an aircraft gas turbine engine is situated within a pressurized core case of the engine. First and second portions of bypass air flow passing through the respective compressed core compartment and the ATCC apparatus, are isolated from one another in order to improve both the ATCC performance and bypass air duct performance.09-30-2010
20100061842STEAM TURBINE ROTATING BLADE FOR A LOW PRESSURE SECTION OF A STEAM TURBINE ENGINE - A steam turbine rotating blade for a low pressure section of a steam turbine engine is disclosed. The steam turbine rotating blade includes an airfoil portion. A root section is attached to one end of the airfoil portion. A dovetail section projects from the root section, wherein the dovetail section includes a straight axial entry dovetail. A tip section is attached to the airfoil portion at an end opposite from the root section. A cover is integrally formed as part of the tip section. The cover has a first portion that overhangs a pressure side of the airfoil portion and a second portion that overhangs a suction side of the airfoil portion. The cover is positioned at an angle relative to the tip section, wherein the angle ranges from about 15 degrees to about 35 degrees.03-11-2010
20100196147VANE FRAME FOR A TURBOMACHINE AND METHOD OF MINIMIZING WEIGHT THEREOF - A vane frame for a turbomachine and a method for minimizing the weight of a vane frame. The vane frame includes an inner shroud made up of a plurality of inner shroud segments, an outer shroud circumscribing the inner shroud and made up of a plurality of outer shroud segments, and guide vanes structurally interconnecting the inner and outer shrouds. The guide vanes include a plurality of first guide vanes between and connecting first pairs of the inner and outer shroud segments, and a plurality of second guide vanes between and connecting second pairs of the inner and outer shroud segments. The first and second guide vanes are formed of different first and second materials, respectively, with the first material having lower strength, modulus, and/or density than the second material. The structural interconnection between the inner and outer shrouds is dominated by the second guide vanes.08-05-2010
20090274552TURBO MACHINE AND GAS TURBINE - A gas turbine (11-05-2009
20090067996BLADE BEARING RING ASSEMBLY OF A TURBOCHARGER WITH A VARIABLE TURBINE GEOMETRY - The invention relates to a turbocharger with a variable turbine geometry. Said turbocharger comprises a blade bearing ring assembly (03-12-2009
20090110545Systems and Methods for Controlling Seal Clearance In A Turbine Engine - In one embodiment, a method for controlling seal clearance in a turbine engine includes positioning a seal ring within a turbine engine, the seal ring having an inner annular surface and an outer annular surface, the inner annular surface and the outer annular surface both being circular but non-concentric, rotating the seal ring within the engine until the seal ring is placed in an aligned orientation at which a center of a circle that defines the inner annular surface coincides with a centerline of the engine, and securing the seal ring while in the aligned orientation.04-30-2009
20130136582SHROUD SEGMENT PRODUCING METHOD AND SHROUD SEGMENT - Disclosed herein is a production method of a shroud segment that includes a forming process of molding a cylindrical fiber fabric (05-30-2013
20110110770HYDROELECTRIC TURBINE HAVING A MAGNETIC BEARING - The present invention provides an open centred hydroelectric turbine having an annular stator and a rotor mounted for rotation within the stator, the turbine comprising a magnetic bearing which is adapted, by having opposing sets of rotor and stator magnets which are offset at a top and bottom of the stator, to provide both axial and radial support to the rotor.05-12-2011
20110044804BLADE OUTER AIR SEAL SUPPORT - A blade outer air seal (BOAS) support segment for supporting at least one BOAS segment of a static turbine shroud of a gas turbine engine, includes a radially and outwardly extending front leg for engagement with an outer case of the engine. The BOAS support segment further includes a pair of radially elongated rear prongs circumferentially spaced apart from each other and radially outwardly abutting the outer case.02-24-2011
20110044801BLADE OUTER AIR SEAL COOLING - A blade outer air seal (BOAS) segment has a plurality of cooling passages axially extending through a platform of the BOAS segment. The passages each have an inlet defined in a radially outer surface and an exit defined on a leading edge of the platform. At least one of the passages positioned close to respective circumferential sides of the platform extends linearly from one of the inlets and is skewed away from the axial direction to cool a corner area of the platform.02-24-2011
20110044802BLADE OUTER AIR SEAL SUPPORT COOLING AIR DISTRIBUTION SYSTEM - A blade outer air seal (BOAS) of a gas turbine engine has a segmented support ring to support a segmented turbine shroud. The support ring has a cooling air distribution system which includes a plurality of inlet cavities extending axially and inwardly to communicate with an inner cooling air passage within the respective support segments. The inlet cavities each are formed with two recesses defined in respective adjacent two support segments.02-24-2011
20110044800Compressor Blade and Production and Use of a Compressor Blade - The invention relates to a compressor blade of a compressor which, along a main axis, comprises a blade base, a platform area and an adjacent blade profile having a profile tip. The blade profile is configured by a convex wall at the suction end and a concave wall at the pressure end opposite the wall at the suction end. These surfaces extend, with respect to a flow medium, from a leading edge to a trailing edge, a profile center line extending in the center between the two. A front face is arranged on the profile tip at an angle to the main axis, a sealing lip at least partially extending from the leading edge to the trailing edge and the blade profile including the sealing lip having a blade profile height extending in the direction of the main axis. In order to allow for an inexpensive compressor blade having improved aerodynamic properties and a modified sealing lip while having the same sealing properties, the height of the sealing lip is less than 2 percent of the height of the blade profile.02-24-2011
20090053046METHOD, SYSTEM AND APPARATUS FOR TURBINE DIFFUSER SEALING - A turbine diffuser is disclosed. The turbine diffuser includes a diffuser segment having a forward end and an aft end with a flange disposed at the aft end of the diffuser segment. The diffuser segment is joinable to an adjacent diffuser segment via the flange, which includes a seal retainer that is securedly connectable in a radial direction with a seal.02-26-2009
20110243714SEALING STRUCTURE ON A SHROUD OF A TURBINE BLADE - A device on a shroud which is provided on a turbine rotor blade tip has a cutting structure designed like a line of ribs, locally projecting over the shroud radially to the rotational axis around which the turbine rotor blade is rotatably arranged. The sealing structure has a longitudinal extent (S) oriented in the direction of rotation (U) of the turbine rotor blade, tapers with increasing radial distance from the shroud, and terminates with a flat end face (St) which radially faces away from the turbine rotor blade, and can be divided into five interrelated surfaces.10-06-2011
20100008768PUMP - A pump, in particular a centrifugal pump, includes at least one flow-leading part with an at least regional surface layer (01-14-2010
20110081237SEALING FOR VANE SEGMENTS - A seal housing is provided to substantially cover at least one duct wall of vane array duct of a gas turbine engine, and one example arrangement is employed in a mid-turbine frame. The arrangement provides improved sealing of the vane array duct through the provision of a plurality of cavities extending along the duct wall. The arrangement may also include insulation tubes to assist in sealing around load transfer spokes passing through the vane array.04-07-2011
20110164961COATING SYSTEM FOR CLEARANCE CONTROL IN ROTATING MACHINERY - The invention relates to gas turbine engine seal systems having a rotating member with an abrasive tip surface disposed in rub relationship to a stationary seal member with an abradable surface. The abrasive tip surface is coated with a metallic alloy matrix having ceramic abrasive particles embedded in and projecting from the matrix. The abradable seal surface is coated with a ceramic coating. The rub relationship affords a tight operating clearance between the rotating member and the stationary seal member, thereby improving engine efficiency, reducing fuel consumption and minimizing overhaul downtime.07-07-2011
20100284795Plasma Clearance Controlled Compressor - A plasma leakage flow control system for a compressor is disclosed, comprising a circumferential row of compressor blades, an annular casing surrounding the tips of the blades, located radially apart from the tips of the blades and at least one annular plasma generator located on the annular casing. The annular plasma generator comprises an inner electrode and an outer electrode separated by a dielectric material. A gas turbine engine having a plasma leakage flow control system further comprises an engine control system which controls the operation of the annular plasma generator such that the blade tip leakage flow can be changed.11-11-2010
20100068041SHROUD FOR A TURBOMACHINE - A turbomachine includes a casing defining a hot gas path, and a shroud member attached to the casing. The shroud member is spaced from the casing to define a gap. The shroud member includes a first end having a first hook member provided with a first sealing surface and a second end including a second hook member provided with a second sealing surface. At least one of the first and second sealing surfaces includes a plurality of labyrinth seal elements that reduce air leakage through the gap into the hot gas path.03-18-2010
20120308367SEAL ASSEMBLY FOR GAS TURBINE ENGINE - A seal assembly for a gas turbine engine includes a seal body and a biasing support member. The seal body includes a generally annular shape that defines an outer diameter surface. The biasing support member is circumferentially disposed about the outer diameter surface of the ceramic matrix composite seal body and includes an array of spring fingers that circumferentially overlap about the biasing support member. The array of spring fingers contacts the seal body and centers the seal body relative to the centerline axis of the gas turbine engine.12-06-2012
20120148389SEALS IN STEAM TURBINE - A seal structure for a steam turbine is provided, which is capable of suppressing transfer of heat generated by a friction between a rotating portion and a fixed portion to the rotating portion and of suppressing an increase in the temperature of the rotating portion. A labyrinth seal device serves to suppress the amount of steam leaking from a clearance present between each stator blade (fixed portion) of the steam turbine and a rotor (rotating portion). The seal structure for the steam turbine is formed to ensure that permeable spacers made of a permeable metal are provided on the rotor and a seal stationary body and face respective seal fins provided in the labyrinth seal device.06-14-2012
20080206046Rotor seal segment - A ceramic seal segment for a shroud ring of a rotor of a gas turbine engine, the ceramic seal segment positioned radially adjacent the rotor and characterized by being a hollow section that defines an inlet and an outlet for the passage of coolant therethrough.08-28-2008
20110318171TURBINE SHROUD SEALING APPARATUS - A turbine shroud sealing apparatus for a gas turbine engine includes: (a) an arcuate shroud segment comprising a low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces of the segment; and (b) a first seal assembly received in at least one slot formed in the first end face, the first seal assembly comprising one or more spline seals which protrude from the first end face and which are arranged to define a continuous sealing surface around the perimeter of the first end face.12-29-2011
20090148276SEAL ASSEMBLY FOR A FAN ROTOR OF A TIP TURBINE ENGINE - A seal assembly (06-11-2009
20120003078TURBINE SHROUD - A turbine blade assembly is disclosed. The turbine blade assembly includes a turbine blade and an outer shroud section at the radially outer end of the turbine blade. The turbine blade intersects or joins the shroud section. For increased stiffness, the shroud section has a reinforcing rib extending along its outer face and extending substantially in the direction of the principal axis of inertia.01-05-2012
20120301279HOUSING SYSTEM FOR AN AXIAL TURBOMACHINE - The English-language Abstract from the international application is to be retained and is therefore not duplicated in the specification.11-29-2012
20100290897Tip Shrouded Turbine Blade - A turbine blade is provided comprising: an airfoil including upper and lower ends; a root coupled to the airfoil lower end; a shroud coupled to the airfoil upper end; and at least one sealing rail extending radially outwardly from an upper surface of the shroud and extending generally along a circumferential length of the shroud. The sealing rail may comprise a mid-section, opposing end sections and at least one intermediate section located between the mid-section and one of the opposing end sections. An axial thickness of the rail may vary.11-18-2010
20120121394TURBINE AND TURBINE ROTOR BLADE - An object is to provide a turbine and a turbine rotor blade in which it is possible to ensure the strength of the turbine rotor blade and to improve the performance thereof. The turbine includes: rotor blades that rotate about a rotational axis in a main flow channel of a casing; stator vanes that are disposed in the casing; a tip shroud that is disposed at a radially-outward end of each of the rotor blades and whose length in the direction along the rotational axis is reduced as the distance from the rotor blade increases; and a cavity portion that is formed at a position in the casing facing the rotor blades and in which the tip shroud is accommodated. An inclination angle of the inner periphery of the tip shroud is larger than an average inclination angle that is an inclination angle of the inner periphery of the casing, averaged from the trailing edge of the stator vanes disposed at the upstream side of a main flow to the cavity portion disposed at the downstream side of the main flow.05-17-2012
20120121393TURBINE - The turbine is provided with a blade (05-17-2012
20120163960GAS TURBINE ENGINE AND VARIABLE CAMBER VANE SYSTEM - One embodiment of the present invention is a unique variable camber vane system for a gas turbine engine. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and variable camber vane systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.06-28-2012
20100247298TURBINE SHROUD - A turbine shroud (09-30-2010
20110182719METHOD AND APPARTUS FOR LABYRINTH SEAL PACKING RINGS - A seal assembly for a turbomachine may include at least one arcuate plate coupled to an interior surface of a stationary housing; a circumferentially-segmented packing ring disposed intermediate to a rotor and the plate; a plurality of arcuate teeth disposed intermediate to the ring and the rotor, wherein a clearance of each tooth decreases progressively going from an upstream side of the turbomachinery to a downstream side; wherein the progressive decrease in the clearances of the teeth creates a passive feedback, such that as a tip clearance decreases, outward radial forces cause the packing ring to move away from the rotor and as the tip clearance increases, inward radial forces cause the packing ring to move toward the rotor; and a biasing member disposed intermediate to the arcuate plate and the ring and coupled to both.07-28-2011
20120219404TURBINE SHROUD AND A METHOD FOR MANUFACTURING THE TURBINE SHROUD - A turbine shroud includes a body having a plurality of sides. A first inward facing groove is defined by a first side of the body, and a first seal covers the first inward facing groove to define a first fluid passage in the first inward facing groove along the first side of the body. A first inlet port through the first seal fluid communication through the first seal into the first fluid passage. A method for forming a turbine shroud includes forming an inner surface and forming an outer surface opposed to the inner surface, wherein the outer surface is configured for exposure to a hot gas path. The method further includes defining a first slot in the inner surface and extending a first seal across the first slot to define a first fluid passage in the first slot along the inner surface.08-30-2012
20100054924Brush seal and turbine using the same - A brush seal in which an increase in steady-state wear is prevented and the influence of turbulence is eliminated is provided. The invention includes a brush seal including brush seal bristles formed of a plurality of wires and mounted to a seal box in such a manner that one end thereof is in contact with a downstream cylindrical portion; and a downstream support plate mounted next to the brush seal bristles in a direction in which combustion gas flows, for restricting the motion of the brush seal bristles. The brush seal seals the combustion gas flowing between the seal box and the downstream cylindrical portion. The brush seal includes restraint bristles mounted opposite to the downstream support plate and next to the brush seal bristles in the direction in which the combustion gas flows. The restraint bristles have a degree of elasticity such that the downstream cylindrical portion is not damaged even if coming into contact with the downstream cylindrical portion and such that the contact deformation of the brush seal bristles is not hindered.03-04-2010
20120076642SEALING ASSEMBLY FOR USE IN TURBOMACHINES AND METHOD OF ASSEMBLING SAME - A method of assembling a sealing assembly for a turbomachine is provided. The method includes positioning at least one sealing element that includes a substantially tortuous flow path defined therein within at least one channel defined in a rotatable element of the turbomachine. The sealing element is extended circumferentially about the rotatable element such that the sealing element extends into a cavity defined between the rotatable element and a stationary element. This facilitates substantially reducing flow leakage from an upstream region of the cavity to a downstream region of the cavity.03-29-2012
20100047061GRID CERAMIC MATRIX COMPOSITE STRUCTURE FOR GAS TURBINE SHROUD RING SEGMENT - A ceramic matrix composite (CMC) component such as a ring seal segment (02-25-2010
20100047060Plasma Enhanced Compressor - A gas turbine engine is disclosed, comprising a compressor having a circumferential row of blades, a casing surrounding the tips of the blades, located radially apart from the tips of the blades and at least one plasma generator located on the casing. The plasma generator comprises a first electrode and a second electrode separated by a dielectric material. The gas turbine engine further comprises an engine control system which controls the operation of the plasma generator such that the stable operating range of the compressor is increased.02-25-2010
20100272559Chamfer rail pockets for turbine vane shrouds - A shroud rail for retaining a feather seal in a vane shroud of a gas turbine engine comprises a slot for, receiving the feather seal, and a chamfer rail pocket for lightening the shroud rail. The slot traverses the vane shroud and includes a slot base extending from a leading edge to a trailing edge of the shroud rail, and a slot wall extending generally perpendicularly from the slot base. The chamfer rail pocket comprises a pocket wall extending along the slot wall, and a chamfer wall extending from the pocket wall at an angle oblique to the slot base.10-28-2010
20090067994Blade outer air seal - A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. At least one cover plate is secured to the body to define at least one cavity. The cover plate has a plurality of feed holes. A plurality of outlet holes extend through the base portion to the ID face. At least one of the base portion and cover plate comprises a protruding portion protruding into the cavity to form a partial restriction separating forward and aft cavity portions.03-12-2009
20100284796PUMP - In a pump, a main shaft (11-11-2010
20090060724METHODS AND APPARATUS FOR FABRICATING GAS TURBINE ENGINES - Methods and apparatus of fabricating a gas turbine engine component are provided. The method includes selecting a surface of a component to apply a wear-resistant material, applying a formed wear pad fabricated from a wear-resistant alloy and a braze material, and vacuum brazing the component and applied wear pad wherein the wear-resistant alloy is bonded to the component surface using the braze material.03-05-2009
20120082540LOW-DUCTILITY OPEN CHANNEL TURBINE SHROUD - A turbine shroud apparatus for a gas turbine engine includes: a plurality of arcuate shroud segments arranged as an annular shroud, each of the shroud segments comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein an open channel is formed through the outer wall of each shroud segment; an annular stationary structure surrounding the shroud segments; and a hanger received in the open channel of each shroud segment and mechanically coupled to the stationary structure, each of the hangers passing through the respective open channel and including an enlarged portion having greater cross-sectional area than the open channel, the enlarged portion engaging the outer wall of the respective shroud segment, so as to retain the shroud segment radially relative to the stationary structure.04-05-2012
20080298956Shroud configuration having sloped seal - A stator shroud segment is provided that includes an outer shroud having a leading edge groove and a trailing edge groove; and a plurality of inner shrouds each having a leading edge hook and a trailing edge hook, the leading and trailing hooks of each of the inner shrouds being respectively engaged with the leading and trailing edge grooves of the outer shroud so as to axially and radially lock the inner shrouds to the outer shrouds. At least one of the trailing edge hook of the inner shroud and the trailing edge groove of the outer shroud includes a sloped surface disposed at an angle to an axial direction of the rotor and to a radial direction of the rotor and facing the other of the inner and outer shrouds whereby a radial inward force on the inner shroud is transformed into a force in axial and radial directions to force the inner shroud to tightly seal a radial gap between the inner and outer shrouds.12-04-2008
20110038718Fluid Flow Machine - A fluid flow machine has a stator, a rotor which is supported so as to be rotatable relative to the stator, and a brush seal which seals a gap formed between the stator and rotor in a radial direction to prevent the passage of fluid. The brush seal has a brush holder and a plurality of sealing bristles, each of which has a first end that is fastened to the brush holder and a second end that contacts a sealing surface. The sealing surface is rotationally displaceable relative to the second ends of the respective sealing bristles. The sealing surface is formed by a circumferential surface of an intermediate sleeve which is arranged between the stator and rotor and which radially divides the gap.02-17-2011
20110236188BLADE OUTER SEAL FOR A GAS TURBINE ENGINE - A blade outer air seal for a gas turbine engine is provided. The blade outer air seal includes a body having an outer radial surface, an inner radial surface, and a plurality of cooling air apertures. The body extends between a forward edge and an aft edge. The inner radial surface includes at least one first seal section, at least one second seal section, and a riser extending radially between the first seal section and the second seal section. Each of the plurality of cooling air apertures extends between the outer radial surface and the riser, and each cooling air aperture has an exit configured to direct cooling air substantially parallel to the second seal section of the inner radial surface.09-29-2011
20100232941TURBINE SHROUD SUPPORT COUPLING ASSEMBLY - A coupling assembly for a turbine shroud is provided. The coupling assembly comprises a rotatable positioning block having a first surface, and a biasing spring having a second surface, the second surface generally facing the first surface, and the biasing spring adapted to exert a force toward the positioning block when compressed.09-16-2010
20100232940TURBINE ENGINE SHROUD RING - In one embodiment, a system includes a turbine engine that includes a rotor including multiple blades. The turbine engine also includes a shroud disposed about the blades. The shroud includes multiple segments engaged with one another via mating teeth. The mating teeth are oriented in an axial direction along a longitudinal axis of the turbine engine.09-16-2010
20100232939Machine Seal Assembly - A machine and a seal assembly for a machine having a rotating shaft, a wheel coupled to the rotating shaft, the wheel including a bucket coupled to the wheel comprising a seal that extends along a side of the bucket and the wheel, covering an interface there between.09-16-2010
20100232938Gas Turbine Having Seal Assembly with Coverplate and Seal - A gas turbine and a seal assembly for a machine having a rotating shaft, a wheel coupled to the rotating shaft, the wheel including a bucket coupled to the wheel comprising a coverplate that is fastened to the wheel and the bucket and a seal positioned between the coverplate and the wheel and the bucket.09-16-2010
20110150636IN-SITU TURBINE BLADE TIP REPAIR - The tip portion of a blade of a gas turbine is repaired in-situ in the gas turbine without removing the blade from the turbine rotor disk. To facilitate the in-situ repair of the tip portion of the turbine blades, one or more access holes may be provided in the turbine shroud or blade outer air seal circumscribing the plurality of turbine blades extending radially outward from the turbine rotor dick.06-23-2011
20080240909Bearing arrangement for a turbine rotor of a drill string turbine - Bearing Arrangement for a Turbine Rotor of a Drill String Turbine The invention is directed to a bearing arrangement for a turbine rotor (10-02-2008
20130170962Forward Step Honeycomb Seal for Turbine Shroud - The present application provides a stage of a gas turbine engine. The stage may include a bucket, a shroud facing the bucket, and a forward step honeycomb seal on the shroud. The forward step honeycomb seal may include a forward step portion and one or more linear portions.07-04-2013
20130170963HYBRID BLADE OUTER AIR SEAL FOR GAS TURBINE ENGINE - A Blade Outer Air Seal (BOAS) includes a body manufactured of a metal alloy, the body includes a face opposite a forward interface and an aft interface, the face includes a cavity. A non-metallic insert within the cavity such that the insert is flush with the face.07-04-2013
20130094945SEAL STRUCTURE, TURBINE MACHINE HAVING THE SAME, AND POWER GENERATING PLANT EQUIPPED WITH THE SAME - A seal structure includes shrouds that are provided at tips of a plurality of blades on which a main flow of fluid impinges and that come into contact with adjacent shrouds to form a cylindrical shape; a sealing part connected to a structure body facing the shrouds; and a space that is defined by downstream sides of the shrouds, a downstream side of the sealing part, and a wall on a downstream side of the structure body, and that communicates with the main flow of fluid that has impinged on the blades. An end of the wall on the downstream side of the structure body is formed so as to be disposed a predetermined distance away from a shroud extension and away from a sealing-part extension and so as to be located on the opposite side of the shroud extension with respect to the sealing-part extension.04-18-2013
20130094946TURBINE SHROUD THERMAL DISTORTION CONTROL - A shroud for a gas turbine engine includes a leading portion having a leading edge and a first set of circumferentially spaced slots at the leading edge that break up the leading portion into circumferentially spaced segments separated by the first set of slots, and a trailing portion adjacent to the leading portion. The trailing portion has a trailing edge.04-18-2013
20130094944BUCKET ASSEMBLY FOR TURBINE SYSTEM - A bucket assembly is disclosed. The bucket assembly includes an airfoil having a generally aerodynamic contour and defining a tip, and a lower body portion extending generally radially inward from the airfoil. The bucket assembly further includes a tip shroud disposed on the tip of the airfoil and comprising a main body and a rail. The rail includes an exterior surface. The exterior surface defines a microchannel. The bucket assembly further includes a cover layer configured on the exterior surface.04-18-2013
20130189086SEAL ASSEMBLY, METHOD AND TURBOMACHINE - A sealing arrangement for a turbomachine for sealing a radial gap between a rotor and a stator, with a plurality of sealing segments each comprising a honeycomb element and a base body for holding the honeycomb element, and with at least one support for arranging the sealing segments on a rotor section or stator section, wherein the base bodies can be arranged on the at least one support by a radial movement and by a plastic deformation of at least one body section, a generative method for the integral production of the sealing segments, and a turbomachine are disclosed.07-25-2013
20130189085TURBOMACHINE SEAL ARRANGEMENT - The present invention relates to a seal arrangement for a turbomachine, in particular a gas turbine, having a plurality of rows, arranged in succession in the axial direction (A), of shells (07-25-2013
20120027573SEAL TEETH FOR SEAL ASSEMBLY - In an embodiment, a seal assembly for a rotating element is disclosed. The seal assembly includes: a plurality of arcuate packing rings configured to form an annulus proximately surrounding the rotating element; and a plurality of radially and circumferentially extending seal teeth coupled to each of the plurality of arcuate packing rings, wherein at least one of the plurality of seal teeth includes a plurality of axially extending protrusions.02-02-2012
20130202419METHOD FOR FASTENING A BRUSH SEALING ELEMENT IN A GROOVE OF A HOUSING SEGMENT - 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.08-08-2013

Patent applications in class Between blade edge and static part

Patent applications in all subclasses Between blade edge and static part