| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 415174400 | Erodable or permanently deformable | 22 |
| 20090081028 | Developments relating to a rotor arrangement - A rotor arrangement comprising a rotor-section and a circumferential moveable seal around the rotor-section, the arrangement being such that, for a given rotation rate, the rotor-section is subject to an associated radial growth and a corresponding related axial displacement, relative to the seal, wherein the rotor-section is provided with an axially-varying profile for off-setting said radial growth of the rotor-section, adjacent the circumferential seal, at said given rotation rate. | 03-26-2009 |
| 20100143106 | Fluid Pump - A fluid pump comprising a pump body, a low pressure impeller, a high pressure impeller, impeller seal means separating the inlet side of the low pressure impeller from its pressure side, a pump priming system, and a pump priming conduit provided through the low pressure impeller radially inboard of the impeller seal means. The high pressure impeller is preferably provided within a cavity, defined by an impeller recess and a cover plate. A wear ring is preferably provided between the low pressure impeller and the inboard end of the cover plate. The pump priming conduit preferably comprises: first and second axial bores through the pump body; a radial bore and two axial holes through the cover plate; an axial hole through the rear wear ring; a cavity between the wear ring and the low pressure impeller; and axial holes through the low pressure impeller, connecting the cavity to the suction side of the low pressure impeller. | 06-10-2010 |
| 20100158676 | COMPOSITE COMPONENT - A composite component such as a fan rear seal comprises a hub and a body of composite material which is moulded over the outer periphery of the hub. The body is formed from a preform of fibre reinforcement impregnated with a resin, in a compression moulding process. The body has an annular projection provided with a sealing surface. The sealing surface may comprise circumferential fins, or may be a surface of, for example, an abradable seal insert moulded into the composite material of the body. | 06-24-2010 |
| 20100266392 | ABRASIVE THERMAL COATING - A protective coating for a surface exposed to hot gas flow comprises a thermal layer, a conducting layer and an abrasive layer. The thermal layer comprises stabilized zirconia, and overlies the surface. The conducting layer overlies the thermal layer. The abrasive layer comprises abrasive particles bonded in a metal matrix that is electroplated onto the conducting layer. | 10-21-2010 |
| 20100284797 | ABRADABLE SEALS - In one embodiment, an abradable seal includes a soft material that may be worn away and a hard material that may provide mechanical strength for the abradable seal. The soft material and the hard material may include different compositions of a base material. | 11-11-2010 |
| 20110070073 | REPAIR OF INDUSTRIAL GAS TURBINE NOZZLE DIAPHRAGM PACKING - A technique for refurbishing nozzle diaphragm sections of a gas turbine replaces an eroded section of the nozzle diaphragm with a replacement part designed to engage a slot machined in the nozzle diaphragm. The replacement part is formed of a material with capable of sustained exposure to higher temperature than the original eroded section, and with a similar coefficient of expansion as the material used for manufacture the original nozzle diaphragm. The combination of the nozzle diaphragm and the replacement part conform to the original manufacturer's dimensional specifications for the nozzle diaphragm. | 03-24-2011 |
| 20110268561 | TURBINE ENGINE ROTOR WHEEL WITH BLADES MADE OF A COMPOSITE MATERIAL PROVIDED WITH A SPRING RING - A turbomachine rotor wheel including blades made of composite material; an annular mounting plate; a plurality of composite material blades mounted on the mounting plate, each blade also including a top platform at its tip carrying radial labyrinth teeth; an orientation disk fastened coaxially around the mounting plate and including at its outer periphery a plurality of axial slots that are open at one end, each slot presenting a cross-section that matches the cross-section of a blade root so as to hold it angularly in position by co-operation of shapes; and a variable-diameter spring ring housed in part in an axial notch formed in each blade root and projecting axially relative thereto, the spring ring to come into radial abutment against an inside surface of the orientation disk during radial outward movement of the blades relative to the mounting plate. | 11-03-2011 |
| 20120087781 | LAYER SYSTEM FOR ROTOR/STATOR SEAL OF A TURBOMACHINE AND METHOD FOR PRODUCING THIS TYPE OF LAYER SYSTEM - The present invention creates a layer system for the rotor/stator seal of a turbomachine, in particular a compressor, which is disposed between components of the turbomachine and can be run in with a movement of the components relative to one another, in such a way that at least one of the components is run into the layer system, having: a first adhesive layer disposed on at least one of the components; a protective layer disposed on the first adhesive layer; a second adhesive layer disposed on the protective layer; and a running-in layer, which is formed softer than the protective layer and which is disposed on the second adhesive layer. The present invention further provides a method for producing a layer system for the rotor/stator seal of a turbomachine, as well as a turbomachine. | 04-12-2012 |
| 20120099972 | ROUGH DENSE CERAMIC SEALING SURFACE IN TURBOMACHINES - An abrasive coating is formed on a rotor shaft that rotates with respect to cantilevered vanes. The coating is formed by thermal spray techniques and comprises a ceramic layer on a metal bond coat. The coating surface is roughened by crush grinding or by grit blasting to increase the abradability of the surface. | 04-26-2012 |
| 20120099973 | LOW DENSITY ABRADABLE COATING WITH FINE POROSITY - A low density abradable coating for use as a seal material is formed by depositing a metal bond coat followed by depositing a low density, porous, abradable metal seal layer on the bond coat. The seal layer is formed by co-depositing metallic sponge particles and metal precursor particles. The metal precursor particles decompose during heat treatment leaving fine pores distributed throughout the microstructure. | 04-26-2012 |
| 20120156012 | Flow machine for a fluid having a radial sealing gap and a stationary wear ring - A flow machine | 06-21-2012 |
| 20120275908 | TURBOMACHINE SHROUD - A ceramic shroud seal has a roughed inner surface for contacting a rotating turbomachine component. | 11-01-2012 |
| 20130004301 | SPALL RESISTANT ABRADABLE TURBINE AIR SEAL - An abrasive coating for a rotor shaft, the abrasive coating having a metal bond coat layer on the rotor shaft and an abrasive layer over the bond layer for contact with vanes during operation of the rotor shaft. The abrasive coating includes a matrix containing a low strength filler having an increased concentration radially outward from the bond layer to the outer surface of the abrasive layer. The matrix may be ceramic or metal. | 01-03-2013 |
| 20130017071 | FOAM STRUCTURE, A PROCESS OF FABRICATING A FOAM STRUCTURE AND A TURBINE INCLUDING A FOAM STRUCTUREAANM GOLLER; George AlbertAACI GreenvilleAAST SCAACO USAAGP GOLLER; George Albert Greenville SC USAANM CAVANAUGH; Dennis WilliamAACI SimpsonvilleAAST SCAACO USAAGP CAVANAUGH; Dennis William Simpsonville SC US - Disclosed is a foam structure, a process of fabricating the foam structure, and a turbine including the foam structure. The foam structure includes a cast metallic foam having pores and a gel positioned within at least a portion of the pores. The process of fabricating the foam structure includes providing the cast metallic and infusing the cast metal foam with the gel. The turbine includes a rotating portion and a turbine seal including the foam structure. | 01-17-2013 |
| 20130017072 | PATTERN-ABRADABLE/ABRASIVE COATINGS FOR STEAM TURBINE STATIONARY COMPONENT SURFACESAANM ALI; SulfickerAACI BangaloreAACO INAAGP ALI; Sulficker Bangalore INAANM MURALIDHARAN; VasanthAACI BangaloreAACO INAAGP MURALIDHARAN; Vasanth Bangalore IN - A pattern-abradable seal assembly is provided for a stationary steam turbine component. The seal assembly, in use, is oriented in opposition to at least one seal tooth on a rotatable turbine component so as to inhibit leakage flow across the seal assembly in one direction, the seal assembly may include an annular seal carrier having at least one axially-oriented surface; a pattern-abradable/abrasive seal coating or insert at least partially covering the at least one axially-oriented surface, the pattern-abradable/abrasive seal coating having a pattern formed thereon adapted to face and be at least partially penetrated by the at least one seal tooth. A plurality of anti-swirl elements project radially beyond the pattern and are arranged to provide at least an axial component of flow across the abradable seal assembly. The coating or insert may also be used on other stationary turbine component surfaces to direct flow in a predetermined direction. | 01-17-2013 |
| 20130045091 | ROTATABLE COMPONENT, COATING AND METHOD OF COATING THE ROTATABLE COMPONENT OF AN ENGINE - A rotatable engine component, coating and method of coating the rotatable component includes a substrate, a transitional zone applied to the substrate, and an abradable zone applied to the transitional zone. During operation of an engine in a turbine, the abradable zone is consumed upon contact with a static portion of the engine preventing damage to the rotatable component. | 02-21-2013 |
| 20130058768 | GAS TURBINE ENGINES WITH ABRADABLE TURBINE SEAL ASSEMBLIES - A turbine section of a gas turbine engine includes a housing, a rotor assembly, and a seal assembly. The rotor assembly includes a rotor disk, a rotor platform coupled to the rotor disk, and a rotor blade extending from the rotor platform into the mainstream hot gas flow path. The stator assembly includes a stator platform with a stator vane that extends from the stator platform into the mainstream hot gas flow path. The seal assembly includes a first flow discourager extending in a first direction from the rotor platform, a second flow discourager extending in a second direction from the stator platform, the first flow discourager axially overlapping the second flow discourager such that the second flow discourager is interior to the first flow discourager in a radial direction, a hard coating applied to the first flow discourager, and an abradable coating applied to the second flow discourager. | 03-07-2013 |
| 20130071235 | LIGHT WEIGHT ABRADABLE AIR SEAL - An air seal for use with rotating parts includes an abradable layer adhered to a substrate. The abradable layer comprises a matrix of agglomerated hexagonal boron nitride and an oxide ceramic. Another hexagonal boron nitride is interspersed with the matrix. | 03-21-2013 |
| 20140105732 | LABYRINTH SEAL FOR GAS TURBINE ENGINE TURBINE - A turbine for a gas turbine engine comprising at least one turbine stator and one turbine rotor, said turbine stator comprising at least one inner annular platform, said inner platform comprising a radial wall delimiting at least one cavity between the turbine stator and the turbine rotor, wherein the turbine rotor comprises at least one elongate element positioned substantially axially and defining a sealing baffle in said cavity, and in that the turbine stator comprises at least one element made of abradable material designed to engage with said elongate element of the turbine rotor so as to form a labyrinth seal. | 04-17-2014 |
| 20140154062 | SYSTEM AND METHOD FOR SEALING A GAS PATH IN A TURBINE - A seal for placement in a slot between two turbine components of a gas turbine to seal a gap between the components may include a sealing element sized so as to be capable of placement within the slot and of substantially sealing the gap during operation of the gas turbine. A sacrificial coating may be located on the sealing element. The sacrificial coating may be configured with a size substantially conforming to a size of the slot, the sacrificial coating including a material that is removable from the sealing element via heating to a temperature achieved during operation of the gas turbine. Related gas turbine assemblies and methods of assembly are also disclosed. | 06-05-2014 |
| 20140199163 | ABRADABLE LAYER INCLUDING A LOW THERMAL CONDUCTIVITY COMPOSITION - A system may include a blade track or blade shroud and a gas turbine blade that includes a blade tip. The blade track or blade shroud may include a substrate and an abradable layer formed over the substrate. The abradable layer may include at least one of zirconia or hafnia; ytterbia; samaria; and at least one of lutetia, scandia, ceria, gadolinia, neodymia, or europia. The abradable layer may include a porosity between about 25 vol. % and about 50 vol. %. The blade track or blade shroud and the gas turbine blade may be configured so the blade tip contacts a portion of the abradable layer during rotation of the gas turbine blade, and the abradable layer may be configured to be abraded by the contact by the blade tip. | 07-17-2014 |
| 20140308116 | GAS TURBINE THERMAL SHROUD WITH IMPROVED DURABILITY - Shroud device thermally protecting a gas turbine blade, having a ceramic layer and a metallic layer, the metallic layer being thermally protected by the ceramic layer, the ceramic layer being mechanically joined to the metallic layer by a fixation device having a plurality of protrusions located in the metallic layer designed so as to engage with a plurality of cavities located in the ceramic layer, such that there exists a gap between the cavities and the protrusions at ambient temperature, the gap disappearing at high temperature operation of the gas turbine, the protrusions being then locked into the cavities. | 10-16-2014 |
