| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 415173500 | Labyrinth seal | 19 |
| 20090148279 | GAS TURBINE BELLY BAND SEAL ANTI-ROTATION STRUCTURE - A seal strip assembly for use in a turbomachine having a plurality of stages including rotationally driven disks, and arms on opposed portions of adjoining disks to define paired arms with a space therebetween. The seal strip assembly includes a seal strip positioned in the space between the paired arms and having opposing edges for locating in slots formed in opposed faces of the paired arms. An anti-rotation block is provided, where a portion of the anti-rotation block is removably located in opposed openings formed in the paired arms and is engaged with the seal strip to resist movement of the seal strip relative to the paired arms. A detachable engagement member is detachably fastened to the anti-rotation block for maintaining the anti-rotation block in engagement with the seal strip. | 06-11-2009 |
| 20100034646 | CENTRIFUGAL COMPRESSOR - The present invention provides a centrifugal compressor that inhibits possible leakage while reducing a destabilizing fluid force generated in a seal to prevent the possible instable vibration of a rotor. The centrifugal compressor includes a casing, a rotor rotatably installed in the casing and having an impeller, and seals provided in the clearance between the casing and the rotor to prevent a fluid from leaking through the clearance from a high pressure side to a low pressure side. The rotor rotates to compress gas. For example, the balance piston seal is composed of a damper seal with a plurality of holes and a labyrinth seal with an annular parallel groove; the damper seal and the labyrinth seal are continuously provided. The damper seal is disposed on the high pressure side in a leakage flow direction. The labyrinth seal is disposed on the low pressure side in the leakage flow direction. | 02-11-2010 |
| 20100074733 | Ingestion Resistant Seal Assembly - A seal assembly limits gas leakage from a hot gas path to one or more disc cavities in a gas turbine engine. The seal assembly includes a seal apparatus associated with a blade structure including a row of airfoils. The seal apparatus includes an annular inner shroud associated with adjacent stationary components, a wing member, and a first wing flange. The wing member extends axially from the blade structure toward the annular inner shroud. The first wing flange extends radially outwardly from the wing member toward the annular inner shroud. A plurality of regions including one or more recirculation zones are defined between the blade structure and the annular inner shroud that recirculate working gas therein back toward the hot gas path. | 03-25-2010 |
| 20110171011 | BLADE OUTER AIR SEAL FORMED OF STACKED PANELS - A blade outer air seal for a gas turbine engine has a plurality of stacked panels extending for at least a part circumferential extent, and extending from a radially outer location to a radially inner location. The plurality of stacked panels are mounted together. A turbine section is also claimed. | 07-14-2011 |
| 20120063889 | FLUID MACHINE - A fluid machine of an embodiment includes a sealing portion formed of an annular minute gap between a runner band of a runner configuring a rotating portion and a sealing liner which is a stationary portion and arranged in opposition to the runner band. A groove having a quadrangular cross-sectional shape is formed circumferentially on a surface of the sealing liner configuring the sealing portion. In a cross section perpendicular to a groove forming direction of the groove, an angle θ, formed between a side WU of the groove on the most upstream side with respect to the flowing direction of the leakage flow and a side W | 03-15-2012 |
| 20130011245 | AXIAL SHAFT SEAL FOR A TURBOMACHINE - A turbomachine has a housing having a passage extending along an axis and an annular axially directed housing face extending radially from the passage. A shaft extending axially in the passage has an outer shaft surface radially spaced from an inner surface of the passage and forming therewith an annular axially extending gap. A radial impeller fixed to the shaft outside the housing has an axially directed and radially extending impeller face axially spaced from and confronting the radial housing face and forming therewith a radially extending gap opening into the axially extending gap. An impeller housing forms a flow space with the impeller outside the housing. The radial gap opens into the flow space. A plurality of spaced seals engaged in the radial gap between the radial faces of the housing and impeller fluidically separates the axial gap from the flow space. | 01-10-2013 |
| 20130058766 | Systems, Methods, and Apparatus for a Labyrinth Seal - Certain embodiments of the invention may include systems, methods and apparatus for providing a labyrinth seal. In an example embodiment, a method is provided for sealing a flow path between a stationary element and a rotating element of a turbomachine. The method can include disposing at least one fixture on an inner surface of a stationary element associated with the turbomachine; disposing a packing ring linked via a spring element to the fixture wherein the packing ring comprises at least one bore; and disposing, according to a predetermined profile, a plurality of interdigitated packing ring teeth and rotor teeth intermediate to the packing ring and the rotating element; wherein the bore, packing ring teeth, and rotor teeth, cooperate to counter a moment associated with one or more axial forces. | 03-07-2013 |
| 20130084168 | CLEARANCE FLOW CONTROL ASSEMBLY HAVING RAIL MEMBER - A flow control assembly is provided, including a member and a wall. The member has a surface, a flow diverting member and a rail member. The rail member is situated upstream of the flow diverting member. The flow diverting member and the rail member each project from the surface of the member. The flow diverting member has a distal end. The wall is disposed in relation to the member to create a clearance gap between the distal end of the flow diverting member and the wall. A fluid path is created between the member and the wall, and flows from an upstream section and through the clearance gap. A first chamber and a second chamber are defined by the wall and located upstream of the clearance gap. | 04-04-2013 |
| 20130236298 | SEALING ASSEMBLY FOR USE IN A ROTARY MACHINE AND METHODS FOR ASSEMBLING A ROTARY MACHINE - A sealing assembly for use with a rotary machine is described herein. The sealing assembly includes a stator shroud coupled to the casing. The stator shroud includes an inner surface that at least partially defines the cavity within the casing. At least one stator labyrinth tooth extends outwardly from the stator shroud inner surface towards a rotor assembly positioned within the casing. At least one protective member is coupled to the stator shroud upstream from the at least one stator labyrinth tooth to facilitate reducing a flow of combustion gas across the at least one stator labyrinth tooth. | 09-12-2013 |
| 20130272855 | TURBINE - A turbine includes a blade, a structure installed at a tip section side of the blade via a gap and configured to relatively rotate with respect to the blade, a step section formed at the tip section of the blade, having at least one step surface, and protruding toward a portion opposite to the tip section of the structure, a seal fin formed at the portion opposite to the tip section of the structure, extending toward the step section, and configured to form a micro gap between the step section and the seal fin, and a cutout section formed at the step surface to be connected to an upper surface of the step section. The cutout section guides a separation vortex separated from a main stream of a fluid passing through the gap toward the seal fin on the upper surface of the step section. | 10-17-2013 |
| 20140064939 | HIGH-RELIABLITY TURBINE METAL SEALING MATERIAL - A metal sealing material used in a sealing device which can reduce a gap between a stator and a rotor of a turbine. The metal sealing material used in a sealing device for a stator and a rotor of a turbine includes a surface layer and a lower layer composed of a porous metal layer, wherein the porosity of the surface layer is smaller than the porosity of the lower layer; the porosity of the surface layer is 60 to 65% and the porosity of the lower layer is 67 to 75% or less; and the porous metal layer has a thickness of 0.3 to 3.0 mm and may include, as a main component, an MCrAlY alloy where M is either one of Ni and Co or both thereof, and h-BN as a solid lubricant. | 03-06-2014 |
| 20140133971 | 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. | 05-15-2014 |
| 20140169954 | CENTRIFUGAL IMPELLER AND TURBOMACHINE - A centrifugal turbomachine comprising a casing, a rotor assembly comprising at least one centrifugal impeller for a fluid flowing from an inlet side to an outlet side of the impeller, and an eye seal extending between an impeller eye of the centrifugal impeller and the casing for preventing the fluid from leaking between the casing and the centrifugal impeller, wherein the eye seal comprises at least a first portion toward the inlet side and a last portion toward the outlet side of the impeller, the last portion being smaller in diameter than the first portion. | 06-19-2014 |
| 20140356143 | ASSEMBLY FOR A FLUID FLOW MACHINE - A structural assembly for a fluid-flow machine includes: a main flow path boundary and at least one row of relatively rotating blades with a gap existing between blade ends of the at least one row of blades and the main flow path boundary. At least one secondary flow duct has in the main flow path boundary one opening each at ends spaced apart in the flow direction, such that the secondary flow duct is connected to the main flow path via the two openings. The structural assembly has at least two components connected to one another, i.e. at least one support component and at least one connecting component, where the support component at least partially forms the main flow path boundary and where the connecting component forms or surrounds at least one part-section of the secondary flow duct. | 12-04-2014 |
| 20150086342 | Centrifugal pump for delivering liquids in a motor vehicle - In a centrifugal pump for delivering liquids in a motor vehicle, annular webs project into a gap seal between a housing part and a cover disc of a rotor. The webs are arranged on both components of the housing part and of the cover disc and delimit chambers which accelerate, decelerate and divert a flow. In this way, the gap seal has a high throttling action. | 03-26-2015 |
| 20150086343 | HIGH DAMPING LABYRINTH SEAL WITH HELICOIDAL AND HELICOIDAL-CYLINDRICAL MIXED PATTERN - A device for sealing a high pressure region in a turbomachine from a low pressure region; the turbomachine has one or more statoric parts and one or more rotoric parts; the device comprises a labyrinth seal having a first plurality of grooves and a second plurality of grooves; the first plurality of grooves is disposed in a helical pattern and the second plurality of grooves is disposed in a cylindrical pattern; the labyrinth seal is disposed between at least one of the one or more rotoric parts of the turbomachine and at least one of the one or more statoric parts of the turbomachine between the high pressure region and the low pressure region of the turbomachine; the helical pattern has a helix angle less than or equal to 10°, wherein a stabilization effect of the turbomachine is obtained and leakage due to the second plurality of grooves is negligible. | 03-26-2015 |
| 20150118032 | SEAL SYSTEM - A seal system for sealing a seal gap in a turbomachine includes: a rotor component; a stator component, the sealing gap extending between the rotor component and the stator component; first seal strips and second seal strips each projecting into the seal gap and forming at least one seal strip package; first seal strip grooves in the rotor component that receive the first seal strips; second seal strip grooves in the stator component that receive the second seal strips; and a relief groove in the rotor component arranged in front of the seal strip package, and after the seal strip package. Every relief groove is at least two times wider than, and at most six times wider than, the first and second seal strip grooves and at least two times deeper than, and at most six times deeper than, the first and second seal strip grooves. | 04-30-2015 |
| 20150330244 | MULTI-PURPOSE GAS TURBINE SEAL SUPPORT AND ASSEMBLY - A gas turbine engine assembly includes a first module, a second module rotatable about a center line of the gas turbine engine and fluidly coupled with the first module, and a multi-purpose seal support. The multi-purpose seal support includes an aft end secured to the first module, and a forward end disposed proximate the second module. The forward end has a) discourager portion, a seal portion, and a meshing portion. | 11-19-2015 |
| 20160115805 | FLEXIBLE FILM-RIDING SEAL - A seal apparatus for a rotary machine, including a plurality of sealing assembly segments surrounding a rotor element which is mounted for rotation about a longitudinal axis and has an outer surface. Each of the segments includes a shoe with one or more labyrinth teeth facing the outer surface and a shoe plate disposed downstream of the one or more labyrinth seal teeth and configured to generate an aerodynamic force between the shoe plate and the outer surface of the rotor element. The shoe is further configured to be flexible in a radial-axial plane in response to fluid film forces generated by interaction of the sealing assembly segment and the rotor element, and an axially-oriented beam spring connects the shoe to a stationary seal body. | 04-28-2016 |
