| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 415173300 | Resilient, flexible, or resiliently biased | 34 |
| 20090110546 | Feather Seals and Gas Turbine Engine Systems Involving Such Seals - Feather seals and gas turbine engine systems involving such seals are provided. In this regard, a representative feather seal for a gas turbine engine includes: an elongate body portion; and a locating tab extending longitudinally along the body portion and extending outwardly therefrom. | 04-30-2009 |
| 20090208330 | SEALING ASSEMBLY FOR A TURBINE ENGINE - A sealing assembly for a turbine engine has a brush configured to provide an air seal between an outer air seal segment and a blade. A support is provided for the brush and is configured for attachment to the outer air seal segment. The support is a flexible planar carrier having a first side and a second side. The brush extends from the first side while the second side is for attachment to the outer air seal segment. The flexible planar carrier has a stiffness less than a stiffness of the outer air seal segment. | 08-20-2009 |
| 20090252602 | TURBINE BLADE TIP GAP REDUCTION SYSTEM - A turbine blade sealing system for reducing a gap between a tip of a turbine blade and a stationary shroud of a turbine engine. The sealing system includes a plurality of flexible seal strips extending from a pressure side of a turbine blade generally orthogonal to the turbine blade. During operation of the turbine engine, the flexible seal strips flex radially outward extending towards the stationary shroud of the turbine engine, thereby reducing the leakage of air past the turbine blades and increasing the efficiency of the turbine engine. | 10-08-2009 |
| 20090269189 | FAN BLADE - A fan blade for the fan of a gas turbine engine has a radially outer tip portion which, in use, is adjacent to a fan case of the engine. The tip portion includes a movable sealing element for sealing a gap between the tip portion and the fan case. The sealing element movably adapts to changes in the spacing of the gap to maintain a seal between the tip portion and the fan case. | 10-29-2009 |
| 20090297341 | FLUIDIC SEALING FOR TURBOMACHINERY - Disclosed is a seal for turbomachinery including a seal face locatable between a first turbomachinery component and a second turbomachinery component. At least one fluid channel extends through the seal. The at least one fluid channel is capable of injecting fluid flow between the first turbomachinery component and the second turbomachinery component at the seal face thereby disrupting a leakage flow between the first turbomachinery component and the second turbomachinery component. Further disclosed is a turbomachine utilizing the seal. | 12-03-2009 |
| 20100034645 | Rotor path arrangements - Within such machines as gas turbine engines it is desirable to provide close association between rotating assemblies and a rotor path arrangement to reduce leakage. However, such arrangements of rotor assemblies and rotor path arrangements are subject to thermal cycling and differentials between the respective parts can lead to rub associations. In order to allow closer thermal responses between the respective rotor path arrangement and rotor assembly, a flexible assembly ( | 02-11-2010 |
| 20100092279 | SEALING MEANS BETWEEN ROTOR AND HOUSING IN A WATER TURBINE - A reaction water turbine including: a rotor having an axis of rotation and an radially outer surface; a housing surrounding the rotor and having a bearing support proximate to the radially outer surface of the rotor; and a seal mounted to the bearing support on the housing, the seal includes a brush seal extending to and bearing against the radially outer surface of the rotor. | 04-15-2010 |
| 20100111678 | TURBINE RING ASSEMBLY FOR GAS TURBINE - A turbine ring assembly for a gas turbine, the assembly comprising a complete ring ( | 05-06-2010 |
| 20110002776 | Actuatable Seal for Aerofoil Blade Tip - The present invention relates to an actuatable seal ( | 01-06-2011 |
| 20110135454 | LEAF SEAL ASSEMBLY INCLUDING POLYMER MEMBER AND ROTARY MACHINE CONTAINING SUCH SEAL ASSEMBLY - A seal assembly which, among other applications, may be used for sealing fluid leakage between low temperature multistage compressors and pumps, steam turbine rotors and turbine stator bodies. In accordance with the invention a seal assembly is provided that comprises a leaf seal including a plurality of staggered leaf seal members; and a polymer member disposed on a high pressure side of the leaf seal, wherein the polymer member is in compliant contact with the leaf seal. | 06-09-2011 |
| 20110164962 | Turbine blade with tip brush seal - A turbine rotor blade with a brush seal formed between the blade tip and an outer shroud to form a seal for a blade outer air seal. The brush seal includes fibers made from a high temperature resistant material that has long wear life such as fibers of alumina-boria-silicate in order to withstand the temperature environment of a turbine rotor blade and to provide long life due to rubbing of the brush fibers on the relatively rotating brush seal surface. | 07-07-2011 |
| 20110311353 | SEAL ASSEMBLY FOR USE WITH TURBINE NOZZLES - A method for assembling a turbine nozzle assembly with respect to a combustor of a gas turbine engine is provided. The method includes coupling a radial outer retaining ring to an aft end of the combustor. A plurality of turbine nozzles is provided. Each turbine nozzle includes an inner band, a radially opposing outer band, and at least one vane extending between the inner band and the outer band. The outer band of each turbine nozzle is coupled to the outer retaining ring to define the turbine nozzle assembly. An inner retaining ring is positioned about an axis of the gas turbine engine and coupled to the inner band of each turbine nozzle. | 12-22-2011 |
| 20120093633 | TURBOMACHINE SEAL ASSEMBLY - A turbomachine seal assembly includes a plurality of sealing strips configured and disposed to inhibit a flow of fluid from passing through a channel defined by a first member and a second member. At least one of the plurality of sealing strips includes a paddle element that is configured and disposed to create a fluid recirculation zone at the channel. The fluid recirculation zone further inhibits the flow of fluid through the channel. | 04-19-2012 |
| 20120093634 | BONDED TURBINE BUCKET TIP SHROUD AND RELATED METHOD - A turbine bucket includes an airfoil portion and a tip shroud at a radially outer end of the airfoil portion. The tip shroud includes a first radially inner tip shroud component formed integrally with the airfoil portion and composed of a first metal material, and a second radially outer structural tip shroud component composed of a second metal material bonded to the first radially inner tip shroud component. | 04-19-2012 |
| 20120107102 | ANNULUS FILLER - An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and for bridging the gap between two adjacent blades attached to the rotor disc. The annulus filler has a body portion defining an airflow surface for air being drawn through the engine. The annulus filler further has a front attachment formation connecting a forward end of the body portion to the rotor disc and which allows rotational movement of the body portion thereabout. The annulus filler further has a rear attachment formation connecting a rearward end of the body portion to the rotor disc. The rear attachment formation comprises a spring element which extends between the body portion and the rotor disc. The spring element expands under operational centrifugal loading such that the rearward end of the body portion moves radially outwardly with the body portion rotating about the front attachment formation. | 05-03-2012 |
| 20120177483 | SYSTEM FOR ADJUSTING BRUSH SEAL SEGMENTS IN TURBOMACHINE - A system includes a brush seal segment. The brush seal segment includes a movable support including a head, an extension, and a seal surface, wherein the head is configured to mount in a chamber. The brush seal segment also includes a brush coupled to the movable support along the seal surface, wherein the seal surface consists essentially of the brush. The brush seal segment also includes a biasing element coupled to the movable support, wherein the biasing element is configured to bias the movable support from a first position to a second position to increase a brush clearance in a space between the brush and a rotor, and the movable support is configured to move from the second position to the first position to decrease the brush clearance in response to a fluid flow from the space to the chamber. | 07-12-2012 |
| 20120219405 | SEALING ARRANGEMENT FOR A THERMAL MACHINE - A sealing arrangement for sealing a gap ( | 08-30-2012 |
| 20120243977 | SEALING DEVICE FOR ROTATING TURBINE BLADES - A seal for reducing a fluid flow around tips of rotating blades of a turbine includes a plurality of diaphragms disposed in succession and providing an outer support for a radial arrangement of static blades disposed alternatingly with the rotating blades in an axial direction. An outer seal has axial and radial supports. The radial support includes a ring held in position by a key and a circumferential extension of the ring. The key and the circumferential extension have a clearance so as to allow a relative radial movement between the ring and a part of a casing or the plurality of diaphragms and providing a pressure sealing face and support in the axial direction. | 09-27-2012 |
| 20120251303 | ROTATING BRUSH SEAL - A brush seal for use between a rotating component and a stationary component in a turbomachine is disclosed. The brush seal according to embodiments of this invention include a set of bristles having a fixed end and a free end, wherein the fixed end is attached to the rotating component, and wherein the set of bristles are angled axially with respect to the rotating component. | 10-04-2012 |
| 20120263580 | FLEXIBLE SEAL FOR TURBINE ENGINE - A turbine includes a turbine seal. The turbine seal includes a first straight portion extending along a first axis. The turbine seal also includes a second straight portion extending along the first axis. The first and second straight portions of the turbine seal intersect to form a V-shaped cross section with an opening extending along the first axis. The first and second straight portions of the turbine seal are also configured to resiliantly move towards and away from each other and the first and second straight portions of the turbine seal are configured to pre-load the turbine seal along a gap between first and second bucket segments of the turbine. | 10-18-2012 |
| 20140064938 | RUB TOLERANT FAN CASE - A case apparatus for a gas turbine engine includes an annular case having an interior surface with annular recess formed therein; and an annular bumper disposed in the recess, the bumper comprising a frangible material and having a low-friction contact surface, wherein the bumper is configured to permit elastic radial deflection in response to applied forces below a predetermined threshold. | 03-06-2014 |
| 20140079538 | REPLACEABLE SEALS FOR TURBINE ENGINE COMPONENTS AND METHODS FOR INSTALLING THE SAME - An assembly and method are provided for sealing a compressor in a gas turbine engine. The method comprises forming an annular groove in a compressor casing such that the groove extends circumferentially about a rotor that is housed within the casing. The compressor casing is then coupled to the rotor such that the compressor casing extends circumferentially about the rotor. A plurality of arcuate seal segments are then inserted into the annular groove without removing the rotor from the compressor casing such that the plurality of seal segments extend circumferentially about the rotor to facilitate sealing a gap that is defined between the rotor and the compressor casing. | 03-20-2014 |
| 20140255167 | CONSUMABLE ASSEMBLY TOOL FOR A GAS TURBINE ENGINE - A method of assembling a gas turbine engine includes locating a consumable assembly tool within the engine | 09-11-2014 |
| 20140321993 | ELLIPTICAL SEALING SYSTEM - Some embodiments of the invention are directed to an elliptical sealing system for use with a rotor and a stator housing of a rotary machine. The elliptical sealing system includes a plurality of sealing segments; and an abradable coating having a uniform thickness disposed on each of the plurality of sealing segments, such that the plurality of sealing segments with the abradable coating disposed thereon has a substantially elliptical shape under all conditions when the rotor rotates and the rotor remains stationary. A rotary machine having the elliptical sealing system is also disclosed. | 10-30-2014 |
| 20140348644 | ARRANGEMENT OF A SEGMENTED RETRACTABLE SEAL IN A STATOR OF A TURBINE - A segmented retractable seal is provided in a stator of a turbine by which a rotor seal is arranged radially and axially movably in a groove formed in the stator of the turbine and is connected with a mechanism which retracts it away from the rotor of the turbine in a radial direction. The groove formed in the stator of the turbine contains an outer partial groove formed on the inner surface of the stator and an inner partial groove formed in the body of the stator and connected with it, its width being smaller than or equal to that of the outer partial groove. A head of the seal is arranged in the inner partial groove, and a comb of the seal is arranged in the outer partial groove. The head of the seal and the comb of the seal are connected by a neck of the seal. | 11-27-2014 |
| 20150037145 | SYSTEMS RELATING TO AXIAL POSITIONING TURBINE CASINGS AND BLADE TIP CLEARANCE IN GAS TURBINE ENGINES - A gas turbine engine that includes: a flowpath defined through one of a compressor and a turbine; an inner casing defining an axially tilted outboard boundary of the flowpath, which, relative to the axial tilt, defines a converging direction in which the flowpath converges and a diverging direction in which the flowpath diverges; a row of rotor blades having outer tips that oppose the outboard boundary across a gap clearance defined therebetween; an outer casing concentrically arranged about the inner casing so to form an annulus therebetween; and a connection assembly that slidably connects the inner casing to the outer casing and includes a biasing means for axially preloading the inner casing in the converging direction. | 02-05-2015 |
| 20150063990 | Turbomachine Axial Compressor Seal with a Brush Seal - The present application relates to an axial turbine engine compressor having a stator with an annular row of stator blades extending radially, an inner ferrule disposed at the inner ends of the stator blades, a downstream brush seal disposed on the inner ferrule which includes a profile of revolution extending substantially axially. The brush seal comprises bristles which extend mainly axially. The compressor also includes a rotor having an annular sealing surface, generally cylindrical or frusto-conical, disposed on the downstream side of the stator blades and which cooperates with the brush seal, so as to provide sealing between the internal ferrule and the rotor. The annular surface surrounds the brush seal, such that the pressure downstream of the brush seal tends to push said seal away from the annular surface. The brush seal wears less in contact with the annular surface. | 03-05-2015 |
| 20150098808 | METHOD AND SYSTEM TO FACILITATE SEALING IN GAS TURBINES - A method and system for sealing between components within a gas turbine is provided. A first recess defined in a first component receives a seal member. A second recess defined in a second component adjacent the first component also receives the seal member. The first and second recesses are located proximate a hot gas path defined through the gas turbine, and define circumferential paths about the turbine axis. The seal member includes a sealing face that extends in a direction substantially parallel to the turbine axis. The seal member also includes a plurality of seal layers, wherein at least one of the seal layers includes at least one stress relief region for facilitating flexing of the first seal member. | 04-09-2015 |
| 20150337674 | SEAL ASSEMBLY FOR ARRANGING BETWEEN A STATOR AND A ROTOR - A seal assembly is provided that extends along an axial centerline. The seal assembly includes a seal support, a seal housing, a plurality of torque pins and a plurality of stopper collars. The seal housing includes a plurality of slots arranged circumferentially around the centerline. The slots extend axially through the seal housing, and one or more of the slots has a lateral slot width. The torque pins are connected to the seal support. Each of the torque pins respectively extends axially through a uniquely associated one of the slots to a distal pin end. Each of the stopper collars is uniquely associated with and connected to a respective one of the torque pins at the pin end. One or more of the stopper collars has a lateral collar width that is less than the slot width. | 11-26-2015 |
| 20160084101 | GAS TURBINE ENGINE BLADE OUTER AIR SEAL ASSEMBLY - A gas turbine engine includes a rotating stage of blades. A circumferential array of blade outer air seal segments are arranged radially outward of the blades. Adjacent blade outer air seal segments provide a circumferential gap. Facing ends of the adjacent blade outer air seal segments include surfaces. A gap seal engages the surfaces and obstructs the circumferential gap. A biasing member is configured to urge the gap seal radially inward toward the surfaces. | 03-24-2016 |
| 20160160671 | METHOD TO PILOT USING FLEXIBLE PROFILE - A fan assembly for use in a gas turbine engine of an aircraft includes a fan disk having a number of fan blades and a windage shield coupled to the fan disk to move therewith. The fan assembly supplies air for use in the engine. The windage shield rotates with the fan disk during operation of the gas turbine engine and directs air supplied by the fan blade. | 06-09-2016 |
| 20160169020 | GAS TURBINE ENGINE NON-ROTATING STRUCTURE WEDGE SEAL | 06-16-2016 |
| 20160169043 | FAN CASING ARRANGEMENT FOR A GAS TURBINE ENGINE | 06-16-2016 |
| 20160376907 | TURBINE SHROUD SEGMENT WITH LOAD DISTRIBUTION SPRINGS - A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine. | 12-29-2016 |
