Class / Patent application number | Description | Number of patent applications / Date published |
415173400 | Erodable or permanently deformable | 73 |
20080219835 | ABRADABLE COMPONENT FOR A GAS TURBINE ENGINE - A gas turbine engine component includes an airfoil having a radial outward end and a radial inward end. A seal member is positioned adjacent to the radial inward end of the airfoil. A tip of the radial inward end of the airfoil is coated with an abradable material. The seal member is coated with an abrasive material. | 09-11-2008 |
20080260522 | GAS TURBINE ENGINE WITH INTEGRATED ABRADABLE SEAL AND MOUNT PLATE - An abradable sealing land for a gas turbine engine includes a mount plate and an open cell portion which is to be abraded. Both portions are formed integrally from a single piece of material. | 10-23-2008 |
20080260523 | GAS TURBINE ENGINE WITH INTEGRATED ABRADABLE SEAL - An abradable land assembly for a gas turbine engine includes a mount portion and an open cell portion which is to be abraded. Both portions are formed integrally from a single piece of material. | 10-23-2008 |
20080273967 | Ring seal for a turbine engine - A turbine engine ring seal for sealing gaps between turbine engine outer seal segments and turbine blade tips. The turbine engine ring segment may have an inner radial surface that defines a portion of a gap gas flow path where the inner radial surface may be formed of an abradable ceramic coating and includes a plurality of gas flow protrusions that are oriented transverse to the gap gas flow path. The gas flow protrusions may induce vortices in the gas flow in the gap gas flow path. Additionally, the gas flow protrusions may be series of peaks and depressions between two adjacent peaks, where the depressions have an approximate semicircular shape. The distance between two adjacent peaks may be equal or greater than a width of the depression and the height of a single peak may be six percent or greater than the distance between two adjacent peaks. | 11-06-2008 |
20080279678 | Abradable CMC stacked laminate ring segment for a gas turbine - A pattern of depressions ( | 11-13-2008 |
20080292452 | Housing for a Supercharger Assembly - A housing for a supercharger assembly is provided having an inner wall at least partially defining a rotor cavity. A layer is formed from a sacrificial polymeric material and is provided on at least a portion of the inner wall. The layer is operable to provide approximately zero running clearance and improve scuff resistance between the first and second rotors and the inner wall. The sacrificial polymeric material is applied to the inner wall by insert molding to form the layer. A method of forming the housing is also provided. | 11-27-2008 |
20090022583 | Turbine blade with a cover plate and a protective layer applied to the cover plate - The invention relates to a turbine blade with a cover plate shaped onto the pan of the blade. The aim of the invention is to provide a turbine blade of this type that, while having a high level of efficiency, is designed for a particularly reliable and safe operation in a turbine, particularly of a steam turbine. To this end, the invention provides that a protective layer made on an alternative material is applied to the surface of the cover plate facing away from the pan of the blade. The friction behavior with regard to a turbine component, particularly a sealing strip, which is opposite the protective layer, can be specifically influenced whereby enabling favorable emergency running properties to be provided in the event of rubbing. | 01-22-2009 |
20090097970 | Systems and Methods Involving Abradable Air Seals - Systems and methods involving air seals are provided. In this regard, a representative air seal for a gas turbine engine comprises a layer of ceramic exhibiting patterned surface features, wherein a substrate supporting the layer of ceramic lacks the patterned surface features. | 04-16-2009 |
20090110547 | Method for producing a contoured gap, and turbo-engine comprising contoured gap - A method for producing a contoured gap between a rotor and a stator of a turbo-engine is provided. A first turbo-engine drives a second turbo-engine by means of a common shaft, the shaft being mounted in a bearing housing by means of a bearing. The aim of the invention is to enable the contoured gap to be created in a simple and reliable manner. To this end, the contoured gap is formed between a contoured surface of the rotor and a contoured surface of an engine housing associated with the rotor, by grinding the contoured surfaces against each other, using the axial play of the bearing. | 04-30-2009 |
20090110548 | ABRADABLE RIM SEAL FOR LOW PRESSURE TURBINE STAGE - An abradable rim seal arrangement for a turbine stage of a gas turbine engine, which includes an abradable rim seat attached to a leading edge of an annular inner duct of a turbine exhaust case, causing a trailing edge platform of each rotor blade to overlap the abradable rim seal, and allowing rubbing with the trailing edge platform during engine operation. | 04-30-2009 |
20090148278 | ABRADABLE COATING SYSTEM - This invention relates to an abradable coating system for use in axial turbine engines. When coated onto a turbine ring seal segment the coating system may allow formation of an individualized seal between turbine blade disks and the surrounding ring seal without causing excessive wear to the blade tips. The abradable coating system includes columns of an abradable material. Thus, interference between the blades and the abradable coating system causes the individual columns to break off at the base. This abrasion mechanism may reduce blade wear and spalling of the coating system when compared to conventional coatings. | 06-11-2009 |
20100074730 | GAS TURBINE SEALING APPARATUS - A gas turbine comprises forward and aft rows of rotatable blades coupled to a disc/rotor assembly, a row of stationary vanes positioned between the forward and aft rows of rotatable blades, and rotatable sealing apparatus. Each of the stationary vanes comprises an inner diameter platform having first sealing structure. The rotatable sealing apparatus comprises seal housing apparatus coupled to the disc/rotor assembly and has second sealing structure adapted to engage with the first sealing structure. | 03-25-2010 |
20100074731 | Gas Turbine Sealing Apparatus - A gas turbine includes forward and aft rows of rotatable blades, a row of stationary vanes between the forward and aft rows of rotatable blades, an annular intermediate disc, and a seal housing apparatus. The forward and aft rows of rotatable blades are coupled to respective first and second portions of a disc/rotor assembly. The annular intermediate disc is coupled to the disc/rotor assembly so as to be rotatable with the disc/rotor assembly during operation of the gas turbine. The annular intermediate disc includes a forward side coupled to the first portion of the disc/rotor assembly and an aft side coupled to the second portion of the disc/rotor assembly. The seal housing apparatus is coupled to the annular intermediate disc so as to be rotatable with the annular intermediate disc and the disc/rotor assembly during operation of the gas turbine. | 03-25-2010 |
20100074732 | Gas Turbine Sealing Apparatus - A sealing apparatus in a gas turbine. The sealing apparatus includes a seal housing apparatus coupled to a disc/rotor assembly so as to be rotatable therewith during operation of the gas turbine. The seal housing apparatus comprises a base member, a first leg portion, a second leg portion, and spanning structure. The base member extends generally axially between forward and aft rows of rotatable blades and is positioned adjacent to a row of stationary vanes. The first leg portion extends radially inwardly from the base member and is coupled to the disc/rotor assembly. The second leg portion is axially spaced from the first leg portion, extends radially inwardly from the base member, and is coupled to the disc/rotor assembly. The spanning structure extends between and is rigidly coupled to each of the base member, the first leg portion, and the second leg portion. | 03-25-2010 |
20100143103 | Seal and a method of manufacturing a seal | 06-10-2010 |
20100158675 | TURBOMACHINE ROTOR HAVING BLADES OF COMPOSITE MATERIAL PROVIDED WITH METAL LABYRINTH TEETH - The invention provides a turbine machine rotor having blades of composite material, the rotor comprising an assembly disk, a plurality of composite material blades mounted on the assembly disk via their roots and each provided at its free end with a platform, and a metal shroud positioned on the blade platforms concentrically around the assembly disk and including labyrinth teeth that project radially outwards in order to abrade an abradable material carried by a casing surrounding the rotor, the casing being held stationary both axially and circumferentially relative to the blade platforms and being suitable for moving radially outwards in operation relative to the blade platforms. | 06-24-2010 |
20100232943 | BURIED CASING TREATMENT STRIP FOR A GAS TURBINE ENGINE - A multiple of circumferential grooves within said arcuate engine casing and an abradable material located radial inboard of the multiple of circumferential grooves. | 09-16-2010 |
20110085893 | COUNTOURED HONEYCOMB SEAL FOR A TURBOMACHINE - A turbomachine includes a housing having an inner surface, a compressor, a turbine and a rotary member including a plurality of blade members configured as part of one of the compressor and the turbine. Each of the plurality of blade members includes a base portion and a tip portion. The turbomachine also includes a honeycomb seal member mounted to the inner surface of the housing adjacent the rotary member. The honeycomb seal member includes a contoured surface having formed therein a deformation zone. The deformation zone includes an inlet zone and an outlet zone. The inlet zone is spaced a first distance from the tip portion of each of the plurality of blade members and the outlet zone is spaced a second distance from the tip portion of each of the plurality of blade members. The second distance being substantially equal to or less than the first distance. | 04-14-2011 |
20110103940 | ABRADABLE COATING SYSTEM - An abradable coating system ( | 05-05-2011 |
20110164963 | COATING 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 |
20110182720 | GAS TURBINE SHROUD WITH CERAMIC ABRADABLE COATINGS - There is provided a gas turbine shroud including a ceramic abradable coating used as a gap adjusting component that can reduce a fluid leakage from a gap and increase turbine efficiency. A gas turbine ceramic abradable coating includes a bond layer, a thermal barrier ceramic layer, and a porous ceramic abradable layer (hardness may be RC15Y: 80±3). A slit groove is provided in the porous ceramic abradable layer by machining. A width of a rectangular section of the ceramic abradable layer divided by the slit groove may be set to a range of 2 to 7 mm. | 07-28-2011 |
20110243715 | ABRADABLE TURBINE AIR SEAL - An abradable seal for a gas turbine engine includes a metal alloy and a plurality of pores in the metal alloy. The plurality of pores have a diameter of approximately 1 to 10 microns. | 10-06-2011 |
20110243716 | BLADE OUTER AIR SEAL WITH IMPROVED EFFICIENCY - An air seal for use with rotating parts in a gas turbine engine has a matrix of agglomerated fine hBN (hexagonal boron nitride) powder, the particles of which having a first dimension, and of a fine metallic alloy powder, the particles of which having a second dimension. An hBN (hexagonal boron nitride) powder, the particles of which have a third dimension that is greater than the first dimension, is mixed with the matrix. | 10-06-2011 |
20110286839 | FAN CASE WITH RUB ELEMENTS - A turbofan engine comprising an annular inner wall surrounding tips of the fan blades, a layer of insulating material surrounding the inner wall, and an outer casing including an annular outer wall surrounding the insulating material and concentric to the inner wall and at least two annular rub elements extending radially inwardly from the outer wall through only part of a radial thickness of the layer of insulating material, at least two of the rub elements being in axial alignment with the blade tips at every point around a circumference of the fan, each rub element having a radially inner end spaced apart from the inner wall and made of a material harder than that of the blades, and a containment fabric layer wrapped around a support structure of the outer wall. | 11-24-2011 |
20110299977 | PATCH RING SEGMENT FOR A TURBOMACHINE COMPRESSOR - A turbomachine includes a compressor provided with a casing having an inner surface defining a flow path. At least one blade is rotatable within the flow path. The at least one blade includes a tip portion that is spaced from the inner surface. At least one patch ring segment is mounted to the inner surface of the casing. The at least one patch ring segment includes a body having a first end that extends to a second end through a surface portion. A first wall member extends from the first end and a second wall member extends from the second end. The first and second wall members include in-turned sections that define a C-shaped cross-section of the at least one patch ring segment. | 12-08-2011 |
20120063888 | ABRADABLE COATING WITH SAFETY FUSE - An abradable coating for interaction with tips of airfoils (such as vanes or blades of a compressor of a gas turbine engine) includes a metal bond coat thermal, a ceramic layer, and an abradable layer. The ceramic layer on the metal bond coat provides insulation and acts as a fuse that is adapted to spall off upon high rub interaction. The abradable coating on the ceramic layer contacts the tips of the airfoils during operation of the compressor. The abradable coating is sufficiently abradable to roundup the coating by contact with the airfoil tips. | 03-15-2012 |
20120099970 | FRIABLE CERAMIC ROTOR SHAFT ABRASIVE COATING - An abrasive coating on a rotor shaft interacts with cantilevered vanes to form an abradable air seal in a turbine engine. The abrasive coating includes a metal bond coat, and an abrasive layer containing a plurality of abrasive CBN grit particles in a ceramic matrix. | 04-26-2012 |
20120107103 | GAS TURBINE SHROUD WITH CERAMIC ABRADABLE LAYER - A gas turbine shroud includes a ceramic abradable coating superior in abradable property and durability. The gas turbine ceramic abradable coating of the present invention is configured by an abradable metal layer and a porous ceramic abradable layer (hardness RC15Y: 80±3), the porous ceramic abradable layer is provided with slit grooves by machining work, and a slit groove width is 0.5 to 5 mm. Thereby, the abradable property, and durability against a thermal cycle and high-temperature oxidation are improved. | 05-03-2012 |
20120134786 | COMPRESSOR BLADE WITH FLEXIBLE TIP ELEMENTS AND PROCESS THEREFOR - A compressor blade and process for inhibiting rub encounters between a blade tip of the blade and an interior surface of a case that surrounds the rotating hardware within a compressor section of a turbomachine. The compressor blade includes a cap that defines the blade tip at a radially outermost end of the blade, and a plurality of flexible elements extending from a surface of the cap that defines the blade tip. The flexible elements extend from the surface in a span-wise direction of the blade, and are operable to become rigid due to centrifugal stiffening at compressor operating speeds and, optionally, cut a groove the interior surface of the case. | 05-31-2012 |
20120177484 | Elliptical Sealing System - The present application provides an elliptical sealing system for use with a rotor and a stator housing of a rotary machine. The elliptical sealing system may include a number of sealing segments with an abradable coating thereon. The sealing segments with the abradable coating thereon may have a substantially elliptical shape. A number of biasing members may be in communication with the sealing segments and the stator housing. | 07-12-2012 |
20120189434 | COATING WITH ABRADABILITY PROPORTIONAL TO INTERACTION RATE - A seal in a gas turbine engine component between an airfoil with a radial outward end and a seal member adjacent it coated with an abrasive layer having a ceramic component in a matrix of a metal alloy with hexagonal BN. The ceramic component is selected from silica, quartz, alumina, zirconia and mixtures thereof and the metal is selected from nickel, cobalt, copper and iron. The ceramic ranges from about 1% to about 10% and the amount of nickel, cobalt, copper or iron will range from about 30% to about 60% by volume, and the balance is hBN. | 07-26-2012 |
20130017070 | TURBINE SEAL, TURBINE, AND PROCESS OF FABRICATING A TURBINE SEALAANM GOLLER; George AlbertAACI GreenvilleAAST SCAACO USAAGP GOLLER; George Albert Greenville SC USAANM CAVANAUGH; Dennis WilliamAACI SimpsonvilleAAST SCAACO USAAGP CAVANAUGH; Dennis William Simpsonville SC USAANM LAYLOCK; MatthewAACI GreenvilleAAST SCAACO USAAGP LAYLOCK; Matthew Greenville SC US - Provided is a turbine seal, a turbine, and a process of fabricating a turbine seal. The turbine seal includes a metallic foam positioned along a hot gas path of a turbine. The turbine includes a blade configured to rotate along a predetermined path in response to a hot gas and a metallic foam turbine seal positioned to be contacted by the hot gas. The process of fabricating the turbine seal includes providing a blade configured to rotate along a predetermined path in response to a hot gas and positioning a metallic foam turbine seal to be contacted by the hot gas. | 01-17-2013 |
20130071234 | ABRADABLE PANEL AND METHOD OF FORMING THE SAME - An abradable panel for a fan track liner assembly comprises an abradable layer comprising a syntactic material. The abradable panel is arranged to be attached to a fan track liner so as to provide an abradable gas-washed surface. The abradable panel may further comprise a carrier tray to which the abradable layer is attached. There is also disclosed a method of manufacturing an abradable panel. | 03-21-2013 |
20130078085 | BLADE AIR SEAL WITH INTEGRAL BARRIER - An air seal for use with rotating parts includes a thermal barrier coating layer adhered to a substrate. An abradable layer is adhered to the thermal barrier coating layer. The abradable layer comprises a matrix of agglomerated hexagonal boron nitride and a metallic alloy. Another hexagonal boron nitride is interspersed with the matrix. | 03-28-2013 |
20130089412 | TURBOMACHINE ROTOR HAVING PATTERNED COATING - A turbomachine rotor includes: a rotor body having an outer surface; and a patterned abrasive or abradable coating formed over the outer surface of the rotor body, the patterned abrasive or abradable coating for directing a flow of a working fluid across the turbomachine rotor. | 04-11-2013 |
20130142628 | ABRADABLE SEAL WITH AXIAL OFFSET - A sealing system for a centrifugal compressor includes a stator having a seal, a seal disposed in the seal housing and having an abradable portion along an inner circumference, a rotor having a plurality of rotor teeth configured to rotate within the inner circumference of the seal and configured to create rub grooves within the abradable portion, and a first spring disposed between the stator and the seal and configured to facilitate axial movement of the seal relative to the seal housing. | 06-06-2013 |
20130142629 | Preforms and Related Methods for Repairing Abradable Seals of Gas Turbine Engines - A preform, for repairing an abradable seal component of a gas turbine engine, includes a multilayer stack that has a first layer and a second layer. The first layer is operative to bond the multilayer stack to a structural substrate of an abradable seal. The first layer includes structural material that corresponds to a material of the structural substrate and braze material that is compatible with the structural material. The second layer includes an abradable material. The multilayer stack is operative to bond to the structural substrate of the abradable seal component during a brazing process such that the second layer forms a replacement abradable layer of the abradable seal component. | 06-06-2013 |
20130195633 | GAS TURBINE ROTARY BLADE WITH TIP INSERT - A rotary blade is provided that includes a root, an airfoil, and a tip insert. The airfoil is attached to the root, and has a suction side surface, a pressure side surface, a leading edge, a trailing edge, a tip, and a slot disposed within the tip. The slot extends in a chordwise direction between the leading edge and trailing edge. The tip insert has a base end and a rub end. The base end of the tip insert is disposed within the slot. The rub end of the tip insert extends radially outward from the airfoil tip. | 08-01-2013 |
20130216362 | SEAL STRUCTURE AND ROTATING MACHINE EQUIPPED THEREWITH - Provided is a seal structure, which includes fins configured to protrude from an outer circumferential surface of a rotor in a circumferential direction, and stator blades having an abradable coating formed on an inner circumferential surface of an inner shroud so as to face the fins. The inner circumferential surface of the inner shroud is formed in an uneven shape, and the abradable coating is formed along the uneven shape. | 08-22-2013 |
20130266427 | SEALING SYSTEM FOR A TURBOMACHINE - A sealing system for a turbomachine, in particular, for a gas turbine, having an annular space between a flow-restricting wall and at least one series of rotor blades including a plurality of rotor blades. The sealing system comprises at least one first sealing fin disposed on an end of the rotor blade facing the wall, at least one second abradable lining disposed following the first sealing fin in the flow direction on the end of the rotor blade facing the wall, at least one first abradable lining disposed on the inside of the wall and opposite the first sealing fin, and at least one second sealing fin disposed in the flow direction following the first abradable lining on the inside of the wall and opposite the second abradable lining. The invention furthermore relates to a gas turbine comprising at least one sealing system. | 10-10-2013 |
20130280049 | BLADE HAVING POROUS, ABRADABLE ELEMENT - A blade includes an airfoil having a base and a free, tip end. The tip end includes at least one porous, abradable element. | 10-24-2013 |
20130323034 | ROTARY MACHINE - In a compressor ( | 12-05-2013 |
20140093360 | ALUMINUM BASED ABRADABLE MATERIAL WITH REDUCED METAL TRANSFER TO BLADES - A turbomachine has a seal which mates to a plurality of airfoils. The seal is formed from an abradable aluminum based material having a plurality of hard phase particles embedded therein and having a melting point higher than a melting point of the melting point of the abradable coating matrix alloy. | 04-03-2014 |
20140140826 | Segmented Composite Inner Ferrule and Segment of Diffuser of Axial Compressor - An axial compressor includes a rotor, a stator, and a blade attached to the stator at a base section and linked to a ferrule at a section opposing the base section, the ferrule being supported solely by the blade. The rotor is configured to rotate within the stator and the ferrule is configured to extend around a periphery of the rotor. | 05-22-2014 |
20140205445 | Gas Turbine - A gas turbine includes a disk wheel forming a rotor; a rotor blade including a shank mounted on the outer circumference of the disk wheel and a rotor blade profile portion; a stator blade including a stator blade profile portion and an inner circumferential end wall provided on the inner circumferential side of the stator blade profile portion; and a seal fin provided on the shank of the rotor blade so as to face an inside-diameter surface of the inner circumferential end wall of the stator blade. An abradable coating is applied to such a portion of the inside-diameter surface of the inner circumferential end wall of the stator blade that faces the seal fin. | 07-24-2014 |
20140271148 | ENGINE CASING ASSEMBLY - A gas turbine engine casing assembly has a first casing element which is located radially outward of one or more rotating aerofoil elements of the gas turbine engine. The first casing element is radially enclosed by a track element, a septum layer, a second casing element and a fan case. The track element is formed from an abrasion resistant material in order to prevent abrasion of the septum layer during excoriation of the first casing element. | 09-18-2014 |
20140294571 | SEAL SEGMENT - A seal segment is provided for a shroud ring of a rotor of a gas turbine engine. The seal segment is positioned, in use, radially adjacent the rotor. The seal segment includes a body portion having front and rear sides which each contain a respective slot that extends in the circumferential direction so that a respective hook formation is insertable into each slot for attaching the seal segment to the engine casing. The body portion is formed from continuous fibre reinforced ceramic matrix composite, reinforcing fibres of the composite wrapping around each slot so that, at the base of the slot, the reinforcing fibres are parallel to the surface of the body portion. | 10-02-2014 |
20140334920 | Turbomachine Stator Internal Shell with Abradable Material - The present application relates to a compression stage of a low-pressure compressor of an axial turbomachine, such as a turboprop. The stage includes a rotor with, on its outer surface, two lip seals, each forming a radial annular rib; and a stator which includes an annular row of stator blades extending substantially radially; and an inner shell whose radial cross section includes a central part connected to the inner tips of the blades, a lateral part extending from each side of the central part to one of the two lip seals, respectively, thus forming a rotor with the annular cavity. The shell and the rotor are configured so that the radial section of the annular cavity has a length L1 and a height H, the length L1 being greater than the height H, which initiates rotational movement of the air contained therein. The speed of the air reduces its pressure, which limits downstream to upstream leaks. | 11-13-2014 |
20140341722 | UNLOCKABLE DEVICE FOR AXIALLY ARRESTING A SEALING RING WITH WHICH AN AIRCRAFT TURBOMACHINE MODULE ROTOR WHEEL MAKES CONTACT - A device for axially arresting a sealing ring made of an abradable material in contact with a periphery of an aircraft turbomachine module rotor, the device having a first reference central axis, and including: a support including a support opening defining a circular track centered on a second axis at a distance from the axis; and an axial stop part including an extraction passage centered on a third axis at a distance from the axis, and defining a complementary circular track around its periphery, cooperating with the track to allow the part to rotate about the axis, between an axial stop position for the sealing ring, and a position to extract the ring through the extraction passage. | 11-20-2014 |
20140356142 | Gas Turbine with Honeycomb Seal - Provided is a gas turbine that can solve a problem in which a seal fin of a turbine blade is abraded by a brazed place of a honeycomb seal. | 12-04-2014 |
20150044035 | HIGH POROSITY ABRADABLE COATING - An abradable coating for a gas turbine engine includes a bond coat, an intermediate layer, and a porous layer. The bond coat includes a metal coating and a thickness from 0.152 millimeters to 0.229 millimeters. The intermediate layer includes a ceramic material and a thickness from 0.051 millimeters to 0.381 millimeters. The porous layer includes a porous ceramic material. The porous layer also includes a porosity greater than thirty-five percent of a volume of the porous layer. The porous layer further includes a thickness from 0.127 millimeters to 1.524 millimeters. | 02-12-2015 |
20150093237 | CERAMIC MATRIX COMPOSITE COMPONENT, TURBINE SYSTEM AND FABRICATION PROCESS - A ceramic matrix composite component, turbine system and fabrication process are disclosed. The ceramic matrix composite (CMC) component includes a CMC material, an environmental barrier coating (EBC) on the CMC material, and a hard wear coating applied over the EBC. The turbine system includes a rotatable CMC component having a hard wear coating, and a stationary turbine component, the stationary turbine component having an abradable coating arranged and disposed to be cut by the silicon carbide material. The fabrication process includes positioning the rotatable CMC a pre-determined distance from the stationary turbine component and rotating the rotatable CMC component. The hard wear coating on the rotatable CMC component cuts the abradable coating on the stationary turbine component. | 04-02-2015 |
20150118031 | SYSTEM AND A METHOD OF INSTALLING A TIP SHROUD RING IN TURBINE DISKS - The various embodiments of the present invention provide a method for installing a tip shroud on a turbine disk in a steam turbine. A tip shroud in the form of a ring is installed on the outer periphery of the turbine disk to prevent a leakage of the driving fluid. The method comprises the steps of mounting turbine disk on to a rotor shaft, tapering the outer diameter of the turbine disk and the inner diameter of the tip shroud, aligning and mounting the tapered surface of the turbine disk with the tapered surface of the tip shroud and fastening the tip shroud on the turbine disk with the help of fasteners. The bolted tip shroud is finally machined to reduce the outer peripheral diameter to appropriate dimensions. | 04-30-2015 |
20150139787 | TURBINE ENGINE STATOR WALL COVERED IN AN ABRADABLE COATING - An annular turbine engine stator portion including a structural support provided in succession with a bonding underlayer and with an abradable coating formed by a resin filled with microbeads, the bonding underlayer for fastening the abradable coating to the structural support being formed by fiber reinforcement made of long fibers having a peripheral portion of the reinforcement that is secured to the structural support and having a central portion thereof that is impregnated with the resin filled with microbeads while the abradable coating is being fastened to the structural support. | 05-21-2015 |
20150308281 | LOW PERMEABILITY HIGH PRESSURE COMPRESSOR ABRADABLE SEAL FOR BARE Ni AIRFOILS HAVING CONTINUOUS METAL MATRIX - An air seal in a gas turbine engine comprising a substrate. A bond coating layer is adhered to the substrate. An abradable layer is adhered to the bond coating layer. The abradable layer comprises a metal matrix discontinuously filled with a soft ceramic material. | 10-29-2015 |
20150322809 | Blade Rub Material - One aspect of the disclosure involves a nib material comprising a polymeric matrix and carbon nanotubes in the matrix. In one or more embodiments of any of the foregoing embodiments, the matrix comprises a silicone. In one or more embodiments of any of the foregoing embodiments, the rub material is at least 1.0 mm thick. In one or more embodiments of any of the foregoing embodiments, the silicone is selected from the group consisting of dimethyl- and fluoro-silicone rubbers and their copolymers. In one or more embodiments of any of the foregoing embodiments, the carbon nanotubes at least locally have a concentration of 1-20% by weight. | 11-12-2015 |
20150354373 | CUTTING BLADE TIPS - A blade includes a blade body extending from a blade root to an opposed blade tip surface along a longitudinal axis. The blade body defines a pressure side and a suction side. The blade body includes a cutting edge defined where the tip surface of the blade body meets the pressure side of the blade body. The cutting edge is configured to abrade a seal section of an engine case. A method for manufacturing a blade includes forming an airfoil with a root and an opposed tip surface along a longitudinal axis, wherein the airfoil defines a pressure side and a suction side. The method also includes forming a cutting edge where the tip surface of the airfoil meets the pressure side of the airfoil. | 12-10-2015 |
20150354392 | ABRADABLE COATINGS - Turbine shroud abradable coatings that balance the apparently contradictory requirements of high flowpath solidity, low blade tip wear, and good durability in service. The shrouds include a shroud substrate, a coating system, and an abradable coating. The coating system overlies at least a portion of an outer surface of the shroud substrate. The coating system includes a bond coat, a thermal barrier coating (TBC), and/or an environmental barrier coating (EBC). The abradable coating overlies at least a portion of the barrier coating. The abradable coating defines a substantially smooth continuous flowpath surface. The abradable coating includes a hybrid microstructure including a relatively dense, high-durability phase corralling relatively porous abradable phases. The second phases are relatively more abradable by the blades of a turbine than the second regions. | 12-10-2015 |
20150377053 | TURBOMACHINE - A turbomachine, particularly an aircraft engine, having a rotor, which is mounted rotatably around its longitudinal axis in a stator, and which has at least one row of rotating blades, which is formed by a plurality of rotating blades, is disclosed, wherein the stator has at least one abradable layer, and wherein each rotating blade has a blade tip that is lowered radially inward, at least in sections, proceeding from a leading edge on the side of the rotating blades in the direction of a trailing edge on the side of the rotating blades, and with a blade tip region that extends downstream from the leading edge runs into the abradable layer during operation of the turbomachine. | 12-31-2015 |
20160053625 | AIRFOILS HAVING POROUS ABRADABLE ELEMENTS - A gas turbine engine includes a plurality of airfoils that are circumferentially arranged to rotate about an engine central axis. Each of the airfoils includes a base and a free tip end. The tip end includes first and second porous abradable elements that are axially spaced apart. The first porous abradable elements of the airfoils circumferentially align with each other, and the second porous abradable elements of the airfoils circumferentially align with each other. | 02-25-2016 |
20160084102 | ABRADABLE SEAL AND METHOD FOR FORMING AN ABRADABLE SEAL - An abradable seal having a metallic substrate and a multi-layered ceramic coating on the metallic substrate. The multi-layered ceramic coating includes a base layer deposited on the metallic substrate, an abradable layer overlaying the first layer, and an abrading layer overlaying the second layer. The abrading layer is formed of an abrading material. A turbine system and a method for forming an abradable seal are also disclosed. | 03-24-2016 |
20160084103 | SHROUDED BONDED TURBINE ROTORS AND METHODS FOR MANUFACTURING THE SAME - Methods are provided for manufacturing a shrouded bonded turbine rotor. A shrouded blade ring is formed. The shrouded blade ring is formed by bonding a unitary shroud ring to an assembled blade ring or assembling a plurality of shrouded turbine blade segments. The shrouded blade ring is bonded to a hub. The shrouded bonded turbine rotors are also provided. The shrouded bonded turbine rotor comprises a shrouded blade ring and a shroud. The shrouded blade ring comprises a plurality of turbine blade segments and a shroud. Each turbine blade segment comprises an airfoil portion including an airfoil having a root and a tip. The shroud covers the tip of each airfoil in the shrouded blade ring. A hub is bonded with the shrouded blade ring. | 03-24-2016 |
20160097295 | SEALING ELEMENT - A sealing element for positioning radially outwardly of aerofoil blades of a gas turbine engine is provided. A radially inner surface region of the sealing element includes a seal structure having one or more inwardly projecting walls formed by additive layer, powder fed, laser weld deposition. The walls form a plurality of curved profile shapes which are arranged in a repeating pattern across the radially inner surface region. None of the walls intersects with any other wall. The curved profile shapes have no radii of curvature less than 0.5 mm. | 04-07-2016 |
20160130960 | Mixed Stator for an Axial Turbine Engine Compressor - The present application relates to a stator for a low-pressure compressor of an axial turbine engine. The stator includes an annular row of stator vanes with connection vanes, and support vanes which are grouped into vaned casings. The casings include internal platforms and external platforms, and are integrally produced by means of additive production based on titanium powder. The stator has a circular internal shroud which is formed by the internal platforms of the vanes of the casings and internal shroud segments which are fixed to the connection vanes. The internal platforms include pairs of contact surfaces in order to interlock the shroud segments therein by moving into abutment and sliding against the contact surfaces. The contact surfaces are perpendicular to the rotation axis and form axial stops. | 05-12-2016 |
20160130969 | ADDITIVE PROCESS FOR AN ABRADABLE BLADE TRACK USED IN A GAS TURBINE ENGINE - A gas turbine engine assembly comprising a rotor, a gas path component, and a carrier. The rotor includes a shaft adapted to rotate about an axis and a gas-path component that extends from the shaft for rotation therewith about the axis. The carrier extends around the gas-path component to block gasses from passing over the gas-path component during rotation of the rotor. | 05-12-2016 |
20160138413 | Internal Shroud for a Compressor of an Axial-Flow Turbomachine - The present application relates to a segmented inner shroud of a low-pressure compressor for an axial-flow turbine engine. The shroud includes an axial tubular wall, and a row of apertures formed in the axial wall. Each aperture has opposing edges situated to either side of a stator vane positioned in the aperture for the purpose of its attachment. The axial wall includes a radial flange which passes through the apertures in the circumferential direction of the shroud, so as to form a mechanical link between the opposing edges of the apertures. This mechanical seal permits the opposing edges to be joined together through each aperture, which improves the rigidity and the sealing. The shroud exhibits an E-shaped profile forming a sandwich structure with the annular sealing fins of the rotor, or sealing lips. The present application also relates to a method for the assembly of stator vanes abutting radially against the transverse radial flange. | 05-19-2016 |
20160146034 | ABRADABLE COMPOSITION AND SEAL OF AN AXIAL-FLOW TURBOMACHINE COMPRESSOR CASING - The invention relates to a composition for an abradable seal of a turbomachine, the composition comprising an aluminium base, nickel powder, polyester powder. The invention also relates to an outer casing of a low-pressure compressor of an axial-flow turbomachine with an abradable seal surrounding an annular row of rotor blades. The seal comprises a rounded support covered with a layer of abradable material comprising a metallic phase mainly made of aluminium and with nickel in a lesser proportion. The abradable material additionally comprises from 25% to 55% of additive, such as polyester, methyl methacrylate, hexagonal boron nitride, calcium fluoride. The support is segmented, and forms an organic matrix composite outer casing of the compressor. The invention also proposes a process for producing an abradable seal by plasma spraying an Al—Ni-polyester powder. | 05-26-2016 |
20160160673 | Stiffness Controlled Abradable Seal System and Methods of Making Same - A stiffness controlled abradable seal system for a gas turbine engine includes a cantilevered arm that supports one of a rotating seal surface and a static seal surface, a stiffness of the cantilevered arm controlled to achieve a desired operational temperature at a seal interface, and an optimally matched abradeable seal material with required thermo-physical and friction properties to enable desired wear mechanisms and maximized sealing and durability. | 06-09-2016 |
20160177971 | GAS TURBINE ENGINE | 06-23-2016 |
20160186595 | COMPRESSOR ABRADABLE MATERIAL SEAL WITH TAILORED WEAR RATIO AND DESIRABLE EROSION RESISTANCE - What is described is a wear resistant seal system that is adapted for resisting wear of a rotating part in a gas turbine engine as it rotates against a stationary part in the engine. The system includes an axially rotable member including an abrasive tip having a first tensile strength. The system also includes a stationary structure radially exterior and adjacent to the rotable member and including an abradable material. The abradable material includes a matrix material having a second tensile strength that, at least in a first temperature range, is lower than the first tensile strength and a filler material interspersed with the matrix material. | 06-30-2016 |
20160186768 | DIFFUSER OF ROTATING FLUID MACHINES - A diffuser of a rotating fluid machine that processes a gas with high level of contaminants is provided, the diffuser having an annular surface portion facing rotating vanes of a rotor of the rotating fluid machine, the annular surface portion being at least partially covered with an abradable and anti-encrustation coating including (A) a first lower metal-based coating layer applied on the annular surface portion of the diffuser, and (B) a second upper polymer-based coating layer applied on the first lower metal-based coating layer, wherein the first lower metal-based coating layer comprises 99% by weight of aluminum powder based on the total weight of the first lower-based coating layer and is anchored to the annular surface with a nickel and aluminum (NiAl) binder. | 06-30-2016 |
20160251975 | ALUMINUM ALLOY COATING WITH RARE EARTH AND TRANSITION METAL CORROSION INHIBITORS | 09-01-2016 |
20180023409 | TURBINE SHROUD WITH ABRADABLE LAYER HAVING RIDGES WITH HOLES | 01-25-2018 |