| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 415174500 | Labyrinth seal | 28 |
| 20090003996 | Labyrinth Seal in a Stationary Gas Turbine - The invention relates to a segmented inner ring for holding guide blades. According to the invention, a lateral wall opposing the front side of the inner ring and pertaining to a shaft shoulder formed on the rotor shaft extends radially, and respectively one half of a labyrinth seal is formed on the front side of the inner ring and on the shaft shoulder. The aim of the invention is to apply an arrangement of stacked labyrinth seals, known from aeroplane turbines, to a stationary gas turbine having a separation plane. To this end, a method is used to mount an inner ring of a gas turbine. The invention also relates to a stationary gas turbine comprising a segmented inner ring. | 01-01-2009 |
| 20090047124 | Gas Turbine Engine Systems Involving Hydrostatic Face Seals with Anti-Fouling Provisioning - Gas turbine engine systems involving hydrostatic face seals with anti-fouling provisioning are provided. In this regard, a representative turbine assembly for a gas turbine engine comprises: a turbine having a hydrostatic seal; the hydrostatic seal having a seal face, a seal runner, a carrier, and a biasing member; the seal face and the seal runner defining a high-pressure side and a lower-pressure side of the seal; the carrier being operative to position the seal face relative to the seal runner; and the biasing member being located on the lower-pressure side of the seal and being operative to bias the carrier such that interaction of the biasing member and gas pressure across the seal causes the carrier to position the seal face relative to the seal runner. | 02-19-2009 |
| 20090097971 | TURBINE STATOR FOR AIRCRAFT TURBINE ENGINE INCLUDING A VIBRATION DAMPING DEVICE - This invention relates to a turbine stator ( | 04-16-2009 |
| 20090196743 | Turbocharger - A sealing structure includes a labyrinth seal provided between a housing and an outer periphery of an end portion of a turbine shaft on a turbine wheel side, and a piston ring seal disposed on a side toward a center of the turbine shaft in an axial direction thereof from a position on the turbine shaft at which the labyrinth seal is provided, and a ring groove is formed along a circumferential direction of the housing in a middle portion of the labyrinth seal to reverse a flow direction of exhaust gas entering from the exhaust passage. | 08-06-2009 |
| 20090280004 | Labyrinth seal for a motor-fan unit - A labyrinth seal for a bypass discharge-type motor-fan unit includes a motor unit from which extends a rotating shaft that passes through an aperture in an end plate to drive a fan unit. Disposed within the aperture is a labyrinth seal configured to prevent liquid entrained in a working airflow from entering the motor unit. The rotating shaft also includes a vacuum bore, such that the negative pressure generated by the operation of the fan unit draws any liquid out of an evacuation zone maintained between the motor unit and the end plate. As such, the components of the motor unit are protected from being exposed to the liquid, thereby extending the operating life motor-fan unit. | 11-12-2009 |
| 20100124490 | ROTATING MEMBER AND METHOD FOR COATING THE SAME - A pulsed discharge is generated between tip ends of a rotating member such as a blade and a discharge electrode including a hard material such as cBN in dielectric liquid or gas by a power supply for discharge to melt the discharge electrode, and a part of the discharge electrode is attached to the tip end of the rotating member to form an abrasive coating film including the hard materials such as cBN. | 05-20-2010 |
| 20100166544 | TURBOMACHINERY - Disclosed herein is a turbomachinery including a labyrinth seal easy to fabricate and adapted to prevent unstable vibration of a rotor. A turbomachinery according to this invention includes a labyrinth seal | 07-01-2010 |
| 20110020114 | Seal Assembly - A seal assembly disposed between a rotor and a stator especially of a turbo-machinery is provided with a close clearance gap there between. The clearance gap is bordered by a rotor surface at the side of the rotor and by a stator surface at the side of the stator. The rotor surface or the stator surface or both are provided with openings which open into at least one chamber arranged at the side of the openings turned away from the clearance gap. | 01-27-2011 |
| 20110052376 | INTER-STAGE SEAL RING - The present application describes a turbine section. The turbine section may include a pair of rotors, a seal ring positioned between the pair of rotors, and a first weld at a first end of the seal ring and a second weld at a second end of the seal ring. | 03-03-2011 |
| 20110070074 | GAS TURBINE WITH A SHROUD AND LABYRINTH-TYPE SEALING ARRANGEMENT - A gas turbine with a shroud and labyrinth-type sealing arrangement has a casing | 03-24-2011 |
| 20110236189 | Rotor Oscillation Preventing Structure and Steam Turbine Using the Same - Whirl flow of leakage flow is reduced to reduce the occurrence potential of steam whirl. | 09-29-2011 |
| 20110280715 | CURVED LABYRINTH SEALS - In one embodiment, a system includes a rotary machine and a packing seal that is disposed between rotary and stationary components of the rotary machine. The packing seal includes a pair of seal lands spaced axially along the rotary component and a seal tooth disposed at an axial position between the pair of seal lands. At least one seal land of the pair of seal lands or the seal tooth includes a curved flow-facing side and is slanted toward the curved flow-facing side. | 11-17-2011 |
| 20120003080 | METHOD AND APPARATUS FOR LABYRINTH SEAL PACKING RINGS - The present disclosure relates to a seal assembly for a turbomachine that includes at least one arcuate plate, a biasing member, and a packing ring. In addition, the seal assembly includes a plurality of arcuate teeth disposed intermediate to the packing ring and the rotor. The plurality of arcuate teeth includes at least one subset of arcuate teeth. The clearance of at least one of the arcuate teeth is different from the clearances of the rest of the arcuate teeth. The clearances of the arcuate teeth of the at least one subset do not progressively increase going from an upstream to a downstream side of the turbomachinery. | 01-05-2012 |
| 20120027575 | LABYRINTH SEAL - A labyrinth seal is provided for forming a seal between a first and a second component which rotate relative to each other. The seal has an abradable lining mounted to the first component, and a plurality of fins projecting from the second component. The fins are arranged in abutment with the abradable lining to form a labyrinthal path for a flow of air through the seal. The seal further has a bypass passage which extends through the abradable lining. The bypass passage allows air to flow through the seal and bypass the labyrinthal path. | 02-02-2012 |
| 20120195743 | FLEXIBLE SEAL FOR TURBINE ENGINE - A system including: a first turbine segment comprising a first blade coupled to a first shank. The system also includes a second turbine segment including a second blade coupled to a second shank, as well as an elongated flexible seal disposed in a gap between the first and second shanks. The elongated flexible seal includes an opening configured to channel a fluid flow into a hollow region of the elongated flexible seal to induce expansion of the elongated flexible seal in the gap. | 08-02-2012 |
| 20130149118 | LABYRINTH SEALS - A labyrinth seal impedes leakage flow though a gap between confronting static and moving parts in a turbomachine. The seal includes axially spaced and circumferentially extending sealing fins arranged in leakage flow series and projecting across the gap from at least one of the confronting parts into sealing proximity with the opposing confronting part. The fins have at least a distal portion that is curved or inclined in the upstream direction of the leakage flow to deflect the leakage flow in the upstream direction. Successive fins define chambers that accommodate recirculating vortices produced by the deflected leakage flow. | 06-13-2013 |
| 20130170965 | COMPLIANT PLATE SEAL FOR USE WITH ROTATING MACHINES AND METHODS OF ASSEMBLING A ROTATING MACHINE - A sealing assembly for use with a rotating machine is described herein. The rotating machine includes a stator casing that includes a radially inner surface that defines a cavity therein, and a rotor positioned within the cavity and spaced inwardly from the stator inner surface. The sealing assembly includes a support ring coupled to the stator casing, and a plurality of plate members coupled to the support ring and oriented circumferentially about the rotor. A resistance member extends inwardly from the support ring towards the rotor outer surface. The resistance member is coupled to the support ring and extends through each plate member of the plurality of plate members. At least one rotor land is defined circumferentially about the rotor outer surface. Each plate member is oriented adjacent the at least one rotor land. | 07-04-2013 |
| 20130223998 | Turbo Machinery - Turbo machinery includes a rotating body, a stator, and a labyrinth seal disposed in a gap between the rotating body and the stator. The labyrinth seal includes a first seal fin and a second seal fin both of which protrude from a portion of one of the rotating body and the stator toward an opposing portion of the other one of the rotating body and the stator. The first seal fin is disposed on the high-pressure side of the center of the labyrinth seal in the axial direction of the rotating body. The second seal fin is disposed on the low-pressure side of the first seal fin to form a cavity together with the first seal fin. A gap to the portion opposing the first seal fin is smaller than a gap to the portion opposing the second seal fin. | 08-29-2013 |
| 20140072415 | SWIRL INTERRUPTION SEAL TEETH FOR SEAL ASSEMBLY - A seal assembly for sealing between a rotating component and a stationary component in a turbomachine. The seal assembly includes a plurality of radially inwardly projecting, axially spaced teeth extending from the stationary component, wherein at least one of the plurality of teeth has at least one axially extending hole therethrough. Axial flow of an operating fluid through the holes acts as an air-curtain to interrupt swirl flow in a seal cavity, therefore reducing steam force that could act to destabilize rotordynamics. | 03-13-2014 |
| 20140140827 | Full Ring Inner Air-Seal With Locking Nut - A vane assembly has a vane including an inner platform with a mount rail extending radially inwardly toward an engine center axis. An air seal is attached to the inner platform. The air seal has a single-piece ring extending circumferentially about the engine center axis. A ring nut secures the air seal to the inner platform. A biasing member cooperates with the ring nut and air seal to seal fore and aft locations on the vane. | 05-22-2014 |
| 20140271150 | LABYRINTH DISK FOR A TURBOMACHINE - The present invention relates to a labyrinth disk for a turbomachine comprising a hub, a web and a frustoconical peripheral portion, having on one face labyrinth seal teeth and on the other face radial ribs ( | 09-18-2014 |
| 20140356145 | CENTRIFUGAL COMPRESSOR HAVING SEAL SYSTEM - Embodiments of the present disclosure are directed towards a seal assembly including a first seal and a second seal, wherein the first seal and the second seal axially abut one another within a retaining bore of a compressor, and cooperatively form an outer radial contour of the seal assembly that is retained by the retaining bore. | 12-04-2014 |
| 20140369821 | EARTH AND/OR SEALING ASSEMBLY FOR ELECTRIC MOTORS - The present invention relates to a shaft earth and/or sealing assembly for use with housed rotating equipment such as electric motors to earth the shaft and also provide an IP69K-rated seal that is flame and spark resistant. | 12-18-2014 |
| 20150037146 | TURBOCHARGER - To reduce the amount of exhaust gas leaking through the inlet side of the turbine wheel and the back face to the brazed portion and to suppress decrease in strength of the brazed portion due to increase in the temperature of the brazed portion in operation, a turbocharger having a turbine rotor including a turbine wheel and a shaft which are joined to each other with a brazing material comprises: a turbine housing | 02-05-2015 |
| 20150369074 | COMPRESSOR AFT HUB SEALING SYSTEM - An aft hub sealing assembly for a gas turbine engine is disclosed. The aft hub sealing assembly includes an aft hub, a bearing cap, an aft baffle, a first seal, and a second seal. The aft hub includes a body portion and a disk portion aft surface. The bearing cap includes a bearing cap inner portion spaced apart from the body portion. The aft baffle is located adjacent the disk portion. The aft baffle includes a baffle forward surface following a contour of the disk portion aft surface. The first seal is between the bearing cap inner portion and the body portion. The second seal is between the bearing cap inner portion and the body portion. | 12-24-2015 |
| 20160024954 | SWIRL INTERRUPTION SEAL TEETH FOR SEAL ASSEMBLY - A seal assembly for sealing between a rotating component and a stationary component in a turbomachine. The seal assembly includes a plurality of radially inwardly projecting, axially spaced teeth extending from the stationary component, wherein at least one of the plurality of teeth has at least one axially extending hole therethrough. Axial flow of an operating fluid through the holes acts as an air-curtain to interrupt swirl flow in a seal cavity, therefore reducing steam force that could act to destabilize rotordynamics. | 01-28-2016 |
| 20160032752 | ROTATING SEAL CONFIGURATION AND METHOD OF SEALING A ROTATING MEMBER TO A HOUSING - A seal configuration includes a housing and a rotatable member rotationally mounted relative to the housing. The rotatable member has at least one portion defining an outer perimetrical face that is configured to contact the housing during operational conditions that cause a radial dimension of the at least one portion to increase. The at least one portion has opposing axial surfaces with each of the opposing axial surfaces being dimensionally axially nearer to the other of the opposing axial surfaces immediately radially inwardly of the outer perimetrical face than a furthest part of the outer perimetrical face. | 02-04-2016 |
| 20160130967 | MODULAR TURBOCHARGER CLEARANCE SEAL - A turbocharger shaft is sealed with respect to the bore of the bearing housing at the turbine wheel end by one or more shaft seal rings. Conventionally these rings are seated in annular grooves provided in the shaft behind the turbine wheel. Problems can arise with this conventional shaft seal arrangement, particularly where the turbocharged engine has an engine brake valve located downstream of the turbine, and the back pressure in the exhaust line, and thus in the turbine wheel housing, can reach 7 bar. The inventive shaft seal design avoids grooves, and makes it possible to assemble a seal with ring seals with higher wear resistance and thus to maintain the seal's effectiveness over heavy use. | 05-12-2016 |
