Entries |
Document | Title | Date |
20080206046 | Rotor seal segment - A ceramic seal segment for a shroud ring of a rotor of a gas turbine engine, the ceramic seal segment positioned radially adjacent the rotor and characterized by being a hollow section that defines an inlet and an outlet for the passage of coolant therethrough. | 08-28-2008 |
20080240909 | Bearing arrangement for a turbine rotor of a drill string turbine - Bearing Arrangement for a Turbine Rotor of a Drill String Turbine The invention is directed to a bearing arrangement for a turbine rotor ( | 10-02-2008 |
20080267770 | SEAL - A turbofan gas turbine engine ( | 10-30-2008 |
20080298956 | Shroud configuration having sloped seal - A stator shroud segment is provided that includes an outer shroud having a leading edge groove and a trailing edge groove; and a plurality of inner shrouds each having a leading edge hook and a trailing edge hook, the leading and trailing hooks of each of the inner shrouds being respectively engaged with the leading and trailing edge grooves of the outer shroud so as to axially and radially lock the inner shrouds to the outer shrouds. At least one of the trailing edge hook of the inner shroud and the trailing edge groove of the outer shroud includes a sloped surface disposed at an angle to an axial direction of the rotor and to a radial direction of the rotor and facing the other of the inner and outer shrouds whereby a radial inward force on the inner shroud is transformed into a force in axial and radial directions to force the inner shroud to tightly seal a radial gap between the inner and outer shrouds. | 12-04-2008 |
20090010754 | Bearing-Like Structure to Control Deflections of a Rotating Component - A bearing like surface on a stationary component reduces deflection of an adjacent rotating component. The stationary component is generally parallel to and offset from a rotational component. The rotational component rotates about a central axis. Protrusions located on the stationary component are in contact with the rotational component to prevent deflection of the rotational component while reducing the friction between the rotational and stationary component. The protrusions have a generally flat surface that may be used to affix the protrusions to the stationary component. An arced surface of the protrusions is in contact with the rotating component. The number, size and the shape of the protrusions are determined by the requirements of the application. | 01-08-2009 |
20090047122 | Fan outlet guide vane shroud insert repair - A method of repairing a turbine engine component that contains a series of lined apertures. The component is removed from the engine, and then at least one of the aperture liners is also removed. The area adjacent the aperture is machined to remove a portion of the parent material of the component. An insert which replaces the material removed by machining is secured adjacent the aperture. The liner about the aperture is then replaced. | 02-19-2009 |
20090053045 | Turbine Shroud for Gas Turbine Assemblies and Processes for Forming the Shroud - A gas turbine assembly includes a shroud that includes a plurality of interconnected shroud segments, wherein each one of the shroud segments comprises an arcuate base formed of a first metal material. The arcuate base is made up of an annular member having an axial component and a pair of upstanding ribs having flanges, wherein the arcuate base further comprises a high temperature capable material layer disposed on a surface of the arcuate base so as to define an inner diameter of the shroud segment (i.e., the hot gas path side or environmental side). | 02-26-2009 |
20090053046 | METHOD, SYSTEM AND APPARATUS FOR TURBINE DIFFUSER SEALING - A turbine diffuser is disclosed. The turbine diffuser includes a diffuser segment having a forward end and an aft end with a flange disposed at the aft end of the diffuser segment. The diffuser segment is joinable to an adjacent diffuser segment via the flange, which includes a seal retainer that is securedly connectable in a radial direction with a seal. | 02-26-2009 |
20090053047 | Turbine bucket tip shroud edge profile - A turbine bucket includes a bucket airfoil having a tip shroud with a leading edge comprising two scalloped faces and a trailing edge comprising a third scalloped face defining leading and trailing edge profiles substantially in accordance with Cartesian coordinate values of X and Y as points 1-41 set forth in Table I. The X and Y values are distances in inches which, when respective points are connected by smooth, continuing arcs define the leading and trailing edge tip shroud scalloped profiles. The tip shroud further has first and second, upper and lower, Z form edge profiles substantially in accordance with Cartesian coordinate values of X and Y as points 42-59 and 60-77, respectively of Table II. | 02-26-2009 |
20090053048 | STEAM TURBINE - A steam turbine has a stationary section, a turbine rotor, nozzle diaphragms, a steam passage section, a nozzle box and a sealing. The stationary section includes a casing. The turbine rotor includes moving blade stages. Each of the moving blade stages has turbine moving blades. Each of the nozzle diaphragms has turbine nozzles. The moving blade portions and the turbine nozzle portions constitute the steam passage. The nozzle box is held by the stationary section and arranged at an upstream side of the steam passage coaxially with the turbine rotor. The sealing divides a space between the turbine rotor and the casing into a first space provided at an inner side and a second space provided at an outer side of the nozzle box. | 02-26-2009 |
20090060724 | METHODS AND APPARATUS FOR FABRICATING GAS TURBINE ENGINES - Methods and apparatus of fabricating a gas turbine engine component are provided. The method includes selecting a surface of a component to apply a wear-resistant material, applying a formed wear pad fabricated from a wear-resistant alloy and a braze material, and vacuum brazing the component and applied wear pad wherein the wear-resistant alloy is bonded to the component surface using the braze material. | 03-05-2009 |
20090067994 | Blade outer air seal - A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. At least one cover plate is secured to the body to define at least one cavity. The cover plate has a plurality of feed holes. A plurality of outlet holes extend through the base portion to the ID face. At least one of the base portion and cover plate comprises a protruding portion protruding into the cavity to form a partial restriction separating forward and aft cavity portions. | 03-12-2009 |
20090067996 | BLADE BEARING RING ASSEMBLY OF A TURBOCHARGER WITH A VARIABLE TURBINE GEOMETRY - The invention relates to a turbocharger with a variable turbine geometry. Said turbocharger comprises a blade bearing ring assembly ( | 03-12-2009 |
20090087306 | BLADE OUTER AIR SEALS, CORES, AND MANUFACTURE METHODS - A blade outer air seal (BOAS) casting core has first and second end portions and a plurality of legs. Of these legs, first legs each have: a proximal end joining the first end portion; a main body portion; and a free distal portion. Second legs each have: a proximal end joining the second end portion; a main body portion; and a free distal portion. | 04-02-2009 |
20090104025 | Gas Turbine Engines and Related Systems Involving Blade Outer Air Seals - Gas turbine engines and related systems involving blade outer air seals are provided. In this regard, a representative blade outer air seal assembly for a gas turbine engine includes: an annular arrangement of outer air seal segments defining an inner diameter surface; intersegment gaps located between the outer air seal segments, each of the gaps being located between a corresponding adjacent pair of the segments; and recesses spaced about the inner diameter surface, each of the recesses communicating with a corresponding one of the gaps. | 04-23-2009 |
20090104026 | CONTROL OF CLEARANCE AT BLADE TIPS IN A HIGH-PRESSURE TURBINE OF A TURBINE ENGINE - Turbine stage in a turbine engine, including a wheel with blades rotating inside a sealing ring ( | 04-23-2009 |
20090110545 | Systems and Methods for Controlling Seal Clearance In A Turbine Engine - In one embodiment, a method for controlling seal clearance in a turbine engine includes positioning a seal ring within a turbine engine, the seal ring having an inner annular surface and an outer annular surface, the inner annular surface and the outer annular surface both being circular but non-concentric, rotating the seal ring within the engine until the seal ring is placed in an aligned orientation at which a center of a circle that defines the inner annular surface coincides with a centerline of the engine, and securing the seal ring while in the aligned orientation. | 04-30-2009 |
20090116956 | MANUFACTURABLE AND INSPECTABLE COOLING MICROCIRCUITS FOR BLADE-OUTER-AIR-SEALS - A method for manufacturing a cooling microcircuit in a blade-outer-air-seal is provided. The method broadly comprises the steps of forming a first section of the blade-outer-air-seal having a first exposed internal wall, forming a second section of the blade-outer-air-seal having a second exposed internal wall, and forming at least one cooling microcircuit on at least one of the first and second exposed internal walls. | 05-07-2009 |
20090129917 | SEALING A ROTOR RING IN A TURBINE STAGE - A turbine stage in a turbomachine, the stage comprising a wheel mounted in a ring carried by a turbine casing, and a nozzle situated upstream from the wheel and including an annular fastener rim for fastening to the turbine casing, sealing being provided between the outer rim of the nozzle and the upstream end of the ring by a radial annular sheet bearing axially at its inner and outer peripheries against a downstream face of the outer rim of the nozzle, with its middle annular portion being axially spaced apart from the outer rim of the nozzle and bearing axially against the upstream end of the ring. | 05-21-2009 |
20090142187 | SEALS IN STEAM TURBINE - A seal structure for a steam turbine is provided, which is capable of suppressing transfer of heat generated by a friction between a rotating portion and a fixed portion to the rotating portion and of suppressing an increase in the temperature of the rotating portion. A labyrinth seal device serves to suppress the amount of steam leaking from a clearance present between each stator blade (fixed portion) of the steam turbine and a rotor (rotating portion). The seal structure for the steam turbine is formed to ensure that permeable spacers made of a permeable metal are provided on the rotor and a seal stationary body and face respective seal fins provided in the labyrinth seal device. | 06-04-2009 |
20090148276 | SEAL ASSEMBLY FOR A FAN ROTOR OF A TIP TURBINE ENGINE - A seal assembly ( | 06-11-2009 |
20090148277 | Gas Turbine Engines and Related Systems Involving Blade Outer Air Seals - Gas turbine engines and related systems involving blade outer air seals are provided. In this regard, a representative blade outer air seal assembly for a gas turbine engine includes: an annular arrangement of outer air seal segments, each of the segments having ends, the segments being positioned in an end-to-end orientation such that each adjacent pair of the segments forms an intersegment gap therebetween, each intersegment gap being defined, at least partially, by a first recess and a first protrusion, the first protrusion being sized and shaped to be received by the first recess, one of the first recess and the first protrusion being located on an end of a first segment of an adjacent pair of the segments, another of the first recess and the first protrusion being located on an end of a second segment of the adjacent pair of the segments. | 06-11-2009 |
20090169368 | BLADE OUTER AIR SEAL - A turbine engine blade outer air seal segment has a body having a base portion. The base portion has a transversely concave ID face, a forward end, an aft end, and first and second circumferential edges. The body has at least one mounting hook. The body comprises a metallic member and a ceramic member. The ceramic member and metallic member are joined along the base portion with the ceramic member inboard of the metallic member. | 07-02-2009 |
20090191049 | TURBOJET COMPRESSOR - The invention relates to a turbojet compressor comprising a shroud and a plurality of blades, each fixed via its root to the shroud. Level with each blade root, the shroud presents a suction-side ramp and a pressure-side ramp extending from the trailing edge of the blade to beyond its leading edge. The pressure-side and suction-side ramps join together upstream from the leading edge of the blade to form a projection presenting a profile that is twisted about the axis of the shroud so as to force the gas stream flowing in each flow passage to go round the blade root essentially on the suction-side thereof, and the suction-side ramp presents a profile that is inclined relative to the outside surface of the shroud so as to deflect the gas stream flowing in the corresponding flow passage from the suction-side surface of the blade towards the pressure-side surface of the adjacent blade. | 07-30-2009 |
20090246006 | Mechanically Affixed Turbine Shroud Plug - A sealing interface for a component in a turbine machine, wherein a plug is mechanically affixed within an entrance passage of an aperture. The plug is secured in place within the entrance passage through deformation of an inner end of the plug to cause the plug to mechanically engage a groove formed adjacent the entrance passage. | 10-01-2009 |
20090269188 | SHROUD SEGMENT ARRANGEMENT FOR GAS TURBINE ENGINES - The gas turbine engine shroud comprises a plurality of circumferentially-disposed and concentric shroud segments. Each shroud segment has an arc-shaped platform with opposite ends, each end comprising an inter-segment seal slot, at least one slot extending substantially across each corresponding end and having a lengthwise-variable depth. | 10-29-2009 |
20090274552 | TURBO MACHINE AND GAS TURBINE - A gas turbine ( | 11-05-2009 |
20090285675 | Systems and Methods for Modifying Modal Vibration Associated with a Turbine - Shroud assemblies and methods for modifying modal vibrations associated with a turbine are described. A shroud assembly includes an inner shroud and an outer shroud. The inner shroud includes a body with a first end portion, a second end portion opposite to the first end portion, an upper surface and a lower surface, wherein the lower surface is adjacent to a plurality of rotating turbine blades. The inner shroud further includes at least two rails formed on the upper surface and extending between the first end portion and the second end portion, wherein an impingement cooling area is defined between the at least two rails. Additionally, the inner shroud includes at least one cross-member formed on the upper surface in a direction transverse to the at least two rails. | 11-19-2009 |
20090304498 | MULTISTAGE TURBOMACHINE COMPRESSOR - A multistage compressor for a turbomachine, in particular an airplane turboprop or turbojet, the compressor comprising a double-walled casing having an inner wall made up of shrouds surrounding respective annular rows of moving blades and annular rows of straightening stator vanes, said shrouds being connected to the outer wall of the casing by independent suspension means enabling the radial clearances between the outer ends of the moving blades and the shrouds of the inner wall of the casing to be adjusted independently from one compression stage to another. | 12-10-2009 |
20100008768 | PUMP - A pump, in particular a centrifugal pump, includes at least one flow-leading part with an at least regional surface layer ( | 01-14-2010 |
20100034644 | HYBRID SEAL ASSEMBLY FOR A FAN-TURBINE ROTOR OF A TIP TURBINE ENGINE - The hybrid seal assembly includes a seal for use with rotating surfaces which may suffer significant deflections such as for sealing between flanges and mating surfaces typical of annular seal face surface of a diffuser section of a tip turbine engine. | 02-11-2010 |
20100047060 | Plasma Enhanced Compressor - A gas turbine engine is disclosed, comprising a compressor having a circumferential row of blades, a casing surrounding the tips of the blades, located radially apart from the tips of the blades and at least one plasma generator located on the casing. The plasma generator comprises a first electrode and a second electrode separated by a dielectric material. The gas turbine engine further comprises an engine control system which controls the operation of the plasma generator such that the stable operating range of the compressor is increased. | 02-25-2010 |
20100047061 | GRID CERAMIC MATRIX COMPOSITE STRUCTURE FOR GAS TURBINE SHROUD RING SEGMENT - A ceramic matrix composite (CMC) component such as a ring seal segment ( | 02-25-2010 |
20100054924 | Brush seal and turbine using the same - A brush seal in which an increase in steady-state wear is prevented and the influence of turbulence is eliminated is provided. The invention includes a brush seal including brush seal bristles formed of a plurality of wires and mounted to a seal box in such a manner that one end thereof is in contact with a downstream cylindrical portion; and a downstream support plate mounted next to the brush seal bristles in a direction in which combustion gas flows, for restricting the motion of the brush seal bristles. The brush seal seals the combustion gas flowing between the seal box and the downstream cylindrical portion. The brush seal includes restraint bristles mounted opposite to the downstream support plate and next to the brush seal bristles in the direction in which the combustion gas flows. The restraint bristles have a degree of elasticity such that the downstream cylindrical portion is not damaged even if coming into contact with the downstream cylindrical portion and such that the contact deformation of the brush seal bristles is not hindered. | 03-04-2010 |
20100061842 | STEAM TURBINE ROTATING BLADE FOR A LOW PRESSURE SECTION OF A STEAM TURBINE ENGINE - A steam turbine rotating blade for a low pressure section of a steam turbine engine is disclosed. The steam turbine rotating blade includes an airfoil portion. A root section is attached to one end of the airfoil portion. A dovetail section projects from the root section, wherein the dovetail section includes a straight axial entry dovetail. A tip section is attached to the airfoil portion at an end opposite from the root section. A cover is integrally formed as part of the tip section. The cover has a first portion that overhangs a pressure side of the airfoil portion and a second portion that overhangs a suction side of the airfoil portion. The cover is positioned at an angle relative to the tip section, wherein the angle ranges from about 15 degrees to about 35 degrees. | 03-11-2010 |
20100068041 | SHROUD FOR A TURBOMACHINE - A turbomachine includes a casing defining a hot gas path, and a shroud member attached to the casing. The shroud member is spaced from the casing to define a gap. The shroud member includes a first end having a first hook member provided with a first sealing surface and a second end including a second hook member provided with a second sealing surface. At least one of the first and second sealing surfaces includes a plurality of labyrinth seal elements that reduce air leakage through the gap into the hot gas path. | 03-18-2010 |
20100104426 | TURBINE ENGINE RING SEAL - Aspects of the invention relate to a ring seal for a turbine engine. The ring seal can be made up of a plurality of circumferentially abutted ring seal segments. Each ring seal segment can comprise a plurality of individual channels. The channels can be generally U-shaped in cross-section with a forward span, and aft span and an extension connecting therebetween. The channels can be positioned such that the aft span of one channel can substantially abut the forward span of another channel. The plurality of separate channels can be detachably coupled to each other by, for example, a plurality of pins. The ring seal segment according to aspects of the invention can facilitate numerous advantageous characteristics including greater material selection, selective cooling, improved serviceability, and reduced blade tip leakage. Moreover, the configuration is well suited to handle the operational loads of the turbine. | 04-29-2010 |
20100104427 | PRESSURE ACTIVATED FLOW PATH SEAL FOR A STEAM TURBINE - A pressure activated flow path seal for a steam turbine is disclosed. In one embodiment a gap closure component is located about a rotary component and the stationary component of the steam turbine. A pressure differential activates the gap closure component to seal or reduce the radial clearance of a steam leakage path between the rotary component and the stationary component. | 04-29-2010 |
20100104428 | Molecular drag pumping mechanism - A vacuum pump comprises a drive shaft and a Siegbahn pumping mechanism. The Siegbahn pumping mechanism comprises a rotor element located on the drive shaft and an annular stator element located about the drive shaft and proximate the rotor element, the stator element comprising a plurality of walls extending towards the rotor element and defining a plurality of spiral channels. The stator element comprises a plurality of sections, with means such as a resilient member being located about the sections to urge the sections together, and thereby inhibit gas leakage between the sections of the stator element. The resilient member can also form a seal between the stator sections and a casing located about the pumping mechanism. | 04-29-2010 |
20100135775 | TURBOMACHINE, ESPECIALLY STEAM TURBINE - A turbomachine includes a turbine stage having a plurality of blades including a first and a second blade disposed adjacent to each other, each blade having a radial longitudinal axis and a blade tip and configured to twist around the radial longitudinal axis in an operating state in a twist direction, wherein the first and the second blades are pretwisted in a direction of twist in a non-operating state, and wherein a connecting element interconnects the first and the second blades to each other in a circumferential direction in a region of the respective blade tip so as to maintain the pretwisting. | 06-03-2010 |
20100143101 | COMPLIANT FOIL SEAL FOR ROTARY MACHINES - A compliant foil seal comprises a bottom foil configured to be located circumferentially around at least a portion of a rotor, and one or more upper foils configured to cooperate with a stator to position the bottom foil to compliantly face the rotor and be located between the stator and the rotor. A compliant foil seal assembly and a rotary machine are also presented. | 06-10-2010 |
20100143102 | COMPLIANT PLATE SEAL WITH SELF-CORRECTING BEHAVIOR - A self-correcting seal assembly comprises a plurality of compliant plates coupled circumferentially to a stationary component, at least one slot in the compliant plates extending from the stationary component towards a rotor; and a resistance member coupled to a stationary component. The resistance member comprising at least one annular ring extending from the stationary component towards a rotor and through the slot. The seal assembly is configured to create passive feedback on hydrostatic forces in response to a tip-clearance between the rotor and tips of the compliant plates. | 06-10-2010 |
20100150703 | STACKED LAMINATE BOLTED RING SEGMENT - A ceramic ring segment for a turbine engine that may be used as a replacement for one or more metal components. The ceramic ring segment may be formed from a plurality of ceramic plates, such as ceramic matrix composite plates, that are joined together using a strengthening mechanism to reinforce the ceramic plates while permitting the resulting ceramic article to be used as a replacement for components for turbine systems that are typically metal, thereby taking advantage of the properties provided by ceramic materials. The strengthening mechanism may include a bolt or a plurality of bolts designed to prevent delamination of the ceramic plates when in use by keeping the ceramic plates in compression. | 06-17-2010 |
20100158674 | ADAPTIVE COMPLIANT PLATE SEAL ASSEMBLIES AND METHODS - A steam turbine comprises a steam turbine casing, a rotor, and at least one compliant plate seal assembly situated between the casing and the rotor. The compliant plate seal assembly comprises a supporting member being stationary with respect to the casing, a plurality of plate members movably mounted to the supporting member and extending towards the rotor, each plate member being inclined with respect to a rotation direction of the rotor, and an actuator for selectively exerting a pressure to retract the plate members in a direction away from the rotor. | 06-24-2010 |
20100196147 | VANE FRAME FOR A TURBOMACHINE AND METHOD OF MINIMIZING WEIGHT THEREOF - A vane frame for a turbomachine and a method for minimizing the weight of a vane frame. The vane frame includes an inner shroud made up of a plurality of inner shroud segments, an outer shroud circumscribing the inner shroud and made up of a plurality of outer shroud segments, and guide vanes structurally interconnecting the inner and outer shrouds. The guide vanes include a plurality of first guide vanes between and connecting first pairs of the inner and outer shroud segments, and a plurality of second guide vanes between and connecting second pairs of the inner and outer shroud segments. The first and second guide vanes are formed of different first and second materials, respectively, with the first material having lower strength, modulus, and/or density than the second material. The structural interconnection between the inner and outer shrouds is dominated by the second guide vanes. | 08-05-2010 |
20100202875 | COMPRESSOR-SIDE SHAFT SEAL OF AN EXHAUST-GAS TURBOCHARGER - The piston ring sealing points of a sealing apparatus between the rotor and the housing of a continuous-flow machine each have a piston ring, a cylindrical contact surface, which is directed radially inward, on the housing, as well as an axial stop on the rotor. In this case, the piston ring of the outer piston ring sealing point has a larger external radius and a smaller internal radius than the piston ring of the inner piston ring sealing point. At the same time, the outer piston ring sealing point has a smaller internal radius than the inner piston ring sealing point. Because of the V-shaped arrangement concept, there is no need for a steel ring, shrunk onto the rotor, between the piston ring sealing points. | 08-12-2010 |
20100226760 | TURBINE ENGINE SEALING ARRANGEMENT - An example turbine engine sealing arrangement includes a blade array rotatable about an axis. The blade array has a plurality of blades extending radially from the axis. A control ring is circumferentially disposed about the blade array. A plurality of tiles are secured relative to the control ring and configured to establish an axially extending seal with one of the blades. | 09-09-2010 |
20100232938 | Gas Turbine Having Seal Assembly with Coverplate and Seal - A gas turbine and a seal assembly for a machine having a rotating shaft, a wheel coupled to the rotating shaft, the wheel including a bucket coupled to the wheel comprising a coverplate that is fastened to the wheel and the bucket and a seal positioned between the coverplate and the wheel and the bucket. | 09-16-2010 |
20100232939 | Machine Seal Assembly - A machine and a seal assembly for a machine having a rotating shaft, a wheel coupled to the rotating shaft, the wheel including a bucket coupled to the wheel comprising a seal that extends along a side of the bucket and the wheel, covering an interface there between. | 09-16-2010 |
20100232940 | TURBINE ENGINE SHROUD RING - In one embodiment, a system includes a turbine engine that includes a rotor including multiple blades. The turbine engine also includes a shroud disposed about the blades. The shroud includes multiple segments engaged with one another via mating teeth. The mating teeth are oriented in an axial direction along a longitudinal axis of the turbine engine. | 09-16-2010 |
20100232941 | TURBINE SHROUD SUPPORT COUPLING ASSEMBLY - A coupling assembly for a turbine shroud is provided. The coupling assembly comprises a rotatable positioning block having a first surface, and a biasing spring having a second surface, the second surface generally facing the first surface, and the biasing spring adapted to exert a force toward the positioning block when compressed. | 09-16-2010 |
20100247297 | ACTIVE TIP CLEARANCE CONTROL ARRANGEMENT FOR GAS TURBINE ENGINE - An active tip clearance control (ATCC) apparatus of an aircraft gas turbine engine is situated within a pressurized core case of the engine. First and second portions of bypass air flow passing through the respective compressed core compartment and the ATCC apparatus, are isolated from one another in order to improve both the ATCC performance and bypass air duct performance. | 09-30-2010 |
20100247298 | TURBINE SHROUD - A turbine shroud ( | 09-30-2010 |
20100266391 | MECHANICAL ATTACHMENT OF CERAMIC OR METALLIC FOAM MATERIALS - A thermal barrier includes a thermal barrier member having at least one material selected from a metal foam or a ceramic foam. The thermal barrier member includes an attachment section for securing the thermal barrier member with a corresponding attachment section of a support. | 10-21-2010 |
20100272559 | Chamfer rail pockets for turbine vane shrouds - A shroud rail for retaining a feather seal in a vane shroud of a gas turbine engine comprises a slot for, receiving the feather seal, and a chamfer rail pocket for lightening the shroud rail. The slot traverses the vane shroud and includes a slot base extending from a leading edge to a trailing edge of the shroud rail, and a slot wall extending generally perpendicularly from the slot base. The chamfer rail pocket comprises a pocket wall extending along the slot wall, and a chamfer wall extending from the pocket wall at an angle oblique to the slot base. | 10-28-2010 |
20100284795 | Plasma Clearance Controlled Compressor - A plasma leakage flow control system for a compressor is disclosed, comprising a circumferential row of compressor blades, an annular casing surrounding the tips of the blades, located radially apart from the tips of the blades and at least one annular plasma generator located on the annular casing. The annular plasma generator comprises an inner electrode and an outer electrode separated by a dielectric material. A gas turbine engine having a plasma leakage flow control system further comprises an engine control system which controls the operation of the annular plasma generator such that the blade tip leakage flow can be changed. | 11-11-2010 |
20100284796 | PUMP - In a pump, a main shaft ( | 11-11-2010 |
20100290897 | Tip Shrouded Turbine Blade - A turbine blade is provided comprising: an airfoil including upper and lower ends; a root coupled to the airfoil lower end; a shroud coupled to the airfoil upper end; and at least one sealing rail extending radially outwardly from an upper surface of the shroud and extending generally along a circumferential length of the shroud. The sealing rail may comprise a mid-section, opposing end sections and at least one intermediate section located between the mid-section and one of the opposing end sections. An axial thickness of the rail may vary. | 11-18-2010 |
20110038718 | Fluid Flow Machine - A fluid flow machine has a stator, a rotor which is supported so as to be rotatable relative to the stator, and a brush seal which seals a gap formed between the stator and rotor in a radial direction to prevent the passage of fluid. The brush seal has a brush holder and a plurality of sealing bristles, each of which has a first end that is fastened to the brush holder and a second end that contacts a sealing surface. The sealing surface is rotationally displaceable relative to the second ends of the respective sealing bristles. The sealing surface is formed by a circumferential surface of an intermediate sleeve which is arranged between the stator and rotor and which radially divides the gap. | 02-17-2011 |
20110044800 | Compressor Blade and Production and Use of a Compressor Blade - The invention relates to a compressor blade of a compressor which, along a main axis, comprises a blade base, a platform area and an adjacent blade profile having a profile tip. The blade profile is configured by a convex wall at the suction end and a concave wall at the pressure end opposite the wall at the suction end. These surfaces extend, with respect to a flow medium, from a leading edge to a trailing edge, a profile center line extending in the center between the two. A front face is arranged on the profile tip at an angle to the main axis, a sealing lip at least partially extending from the leading edge to the trailing edge and the blade profile including the sealing lip having a blade profile height extending in the direction of the main axis. In order to allow for an inexpensive compressor blade having improved aerodynamic properties and a modified sealing lip while having the same sealing properties, the height of the sealing lip is less than 2 percent of the height of the blade profile. | 02-24-2011 |
20110044801 | BLADE OUTER AIR SEAL COOLING - A blade outer air seal (BOAS) segment has a plurality of cooling passages axially extending through a platform of the BOAS segment. The passages each have an inlet defined in a radially outer surface and an exit defined on a leading edge of the platform. At least one of the passages positioned close to respective circumferential sides of the platform extends linearly from one of the inlets and is skewed away from the axial direction to cool a corner area of the platform. | 02-24-2011 |
20110044802 | BLADE OUTER AIR SEAL SUPPORT COOLING AIR DISTRIBUTION SYSTEM - A blade outer air seal (BOAS) of a gas turbine engine has a segmented support ring to support a segmented turbine shroud. The support ring has a cooling air distribution system which includes a plurality of inlet cavities extending axially and inwardly to communicate with an inner cooling air passage within the respective support segments. The inlet cavities each are formed with two recesses defined in respective adjacent two support segments. | 02-24-2011 |
20110044803 | BLADE OUTER AIR SEAL ANTI-ROTATION - A blade outer air seal (BOAS) assembly includes a static turbine shroud formed by BOAS segments and a support ring formed by BOAS support segments. Each BOAS support segment supports one or more BOAS segments. The BOAS assembly further includes an anti-rotation apparatus for restricting relative circumferential movement between the turbine shroud and the support ring. The anti-rotation apparatus includes a stopper provided at least in one of the BOAS support segments and a cast anti-rotation tab integrated with at least one of the BOAS segments supported on that at least one BOAS support segment. The stopper and cast anti-rotation tab circumferentially abut each other. | 02-24-2011 |
20110044804 | BLADE OUTER AIR SEAL SUPPORT - A blade outer air seal (BOAS) support segment for supporting at least one BOAS segment of a static turbine shroud of a gas turbine engine, includes a radially and outwardly extending front leg for engagement with an outer case of the engine. The BOAS support segment further includes a pair of radially elongated rear prongs circumferentially spaced apart from each other and radially outwardly abutting the outer case. | 02-24-2011 |
20110081237 | SEALING FOR VANE SEGMENTS - A seal housing is provided to substantially cover at least one duct wall of vane array duct of a gas turbine engine, and one example arrangement is employed in a mid-turbine frame. The arrangement provides improved sealing of the vane array duct through the provision of a plurality of cavities extending along the duct wall. The arrangement may also include insulation tubes to assist in sealing around load transfer spokes passing through the vane array. | 04-07-2011 |
20110110770 | HYDROELECTRIC TURBINE HAVING A MAGNETIC BEARING - The present invention provides an open centred hydroelectric turbine having an annular stator and a rotor mounted for rotation within the stator, the turbine comprising a magnetic bearing which is adapted, by having opposing sets of rotor and stator magnets which are offset at a top and bottom of the stator, to provide both axial and radial support to the rotor. | 05-12-2011 |
20110129335 | Rotor Assembly for a Reheat Steam Turbine - A caseless rotor assembly is provided. The caseless rotor assembly includes a rotor shaft, a high pressure portion with a high pressure rotor blade, a low pressure portion with a low pressure rotor blade, and a common wall between the high pressure portion and the low pressure portion. The common wall extends radially from the rotor shaft. The common wall itself includes a shaft end oriented towards the rotor shaft and an outer end on the other side of the common wall, oriented radially outwards. Additionally, the common wall surrounds circularly the rotor shaft. | 06-02-2011 |
20110150636 | IN-SITU TURBINE BLADE TIP REPAIR - The tip portion of a blade of a gas turbine is repaired in-situ in the gas turbine without removing the blade from the turbine rotor disk. To facilitate the in-situ repair of the tip portion of the turbine blades, one or more access holes may be provided in the turbine shroud or blade outer air seal circumscribing the plurality of turbine blades extending radially outward from the turbine rotor dick. | 06-23-2011 |
20110164961 | 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 |
20110171010 | Sealing System Between a Shroud Segment and a Rotor Blade Tip and Manufacturing Method for Such a Segment - An arrangement including a turbine blade is provided. The turbine blade includes at least a root, an airfoil and a tip which is mounted to a rotor by means of the root. The rotor extends along a machine axis. The arrangement also includes a circumferential casing segment which includes a surface. The surface faces tips of the blades, wherein the surface is structured. A method to produce a casing segment is also provided. In order to increase efficiency without limiting the operational range of the turbine, the surface is provided at least partially with an at least partially ceramic coating. The method includes machining a first structure into the surface and providing the surface with a ceramic coating. | 07-14-2011 |
20110182719 | METHOD AND APPARTUS FOR LABYRINTH SEAL PACKING RINGS - A seal assembly for a turbomachine may include at least one arcuate plate coupled to an interior surface of a stationary housing; a circumferentially-segmented packing ring disposed intermediate to a rotor and the plate; a plurality of arcuate teeth disposed intermediate to the ring and the rotor, wherein a clearance of each tooth decreases progressively going from an upstream side of the turbomachinery to a downstream side; wherein the progressive decrease in the clearances of the teeth creates a passive feedback, such that as a tip clearance decreases, outward radial forces cause the packing ring to move away from the rotor and as the tip clearance increases, inward radial forces cause the packing ring to move toward the rotor; and a biasing member disposed intermediate to the arcuate plate and the ring and coupled to both. | 07-28-2011 |
20110236188 | BLADE OUTER SEAL FOR A GAS TURBINE ENGINE - A blade outer air seal for a gas turbine engine is provided. The blade outer air seal includes a body having an outer radial surface, an inner radial surface, and a plurality of cooling air apertures. The body extends between a forward edge and an aft edge. The inner radial surface includes at least one first seal section, at least one second seal section, and a riser extending radially between the first seal section and the second seal section. Each of the plurality of cooling air apertures extends between the outer radial surface and the riser, and each cooling air aperture has an exit configured to direct cooling air substantially parallel to the second seal section of the inner radial surface. | 09-29-2011 |
20110243714 | SEALING STRUCTURE ON A SHROUD OF A TURBINE BLADE - A device on a shroud which is provided on a turbine rotor blade tip has a cutting structure designed like a line of ribs, locally projecting over the shroud radially to the rotational axis around which the turbine rotor blade is rotatably arranged. The sealing structure has a longitudinal extent (S) oriented in the direction of rotation (U) of the turbine rotor blade, tapers with increasing radial distance from the shroud, and terminates with a flat end face (St) which radially faces away from the turbine rotor blade, and can be divided into five interrelated surfaces. | 10-06-2011 |
20110293410 | LOW-DUCTILITY TURBINE SHROUD AND MOUNTING APPARATUS - A turbine shroud apparatus for a gas turbine engine includes an arcuate turbine shroud segment of low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces. At least a portion of each of the forward and aft walls is oriented at an acute angle to the outer wall. Radially inner ends of the forward and aft walls are substantially closer together than radially outer ends thereof. | 12-01-2011 |
20110299976 | COMPOSITE GAS TURBINE ENGINE COMPONENT - A gas turbine engine component is disclosed having a composite construction. In one embodiment the gas turbine engine component is a blade that includes a shroud. A fiber ply of the composite construction extends from an airfoil part of the blade to the shroud. The shroud can include multiple plies that can be stitched together. In one form a sealing knife is formed and coupled to the shroud. The sealing knife can be coupled to the shroud by stitching. Filler material can be used in the composite construction of the gas turbine engine component. | 12-08-2011 |
20110318171 | TURBINE SHROUD SEALING APPARATUS - A turbine shroud sealing apparatus for a gas turbine engine includes: (a) an arcuate shroud segment comprising a low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces of the segment; and (b) a first seal assembly received in at least one slot formed in the first end face, the first seal assembly comprising one or more spline seals which protrude from the first end face and which are arranged to define a continuous sealing surface around the perimeter of the first end face. | 12-29-2011 |
20120003078 | TURBINE SHROUD - A turbine blade assembly is disclosed. The turbine blade assembly includes a turbine blade and an outer shroud section at the radially outer end of the turbine blade. The turbine blade intersects or joins the shroud section. For increased stiffness, the shroud section has a reinforcing rib extending along its outer face and extending substantially in the direction of the principal axis of inertia. | 01-05-2012 |
20120027573 | SEAL TEETH FOR SEAL ASSEMBLY - In an embodiment, a seal assembly for a rotating element is disclosed. The seal assembly includes: a plurality of arcuate packing rings configured to form an annulus proximately surrounding the rotating element; and a plurality of radially and circumferentially extending seal teeth coupled to each of the plurality of arcuate packing rings, wherein at least one of the plurality of seal teeth includes a plurality of axially extending protrusions. | 02-02-2012 |
20120070272 | METHOD FOR PRODUCING METAL ELEMENTS, IN PARTICULAR SEALING ELEMENTS - A method for producing metallic elements, and more particularly sealing elements, wherein a sheet metal strip or a foil strip having a predefinable length, width, and thickness is generated and the sheet metal strip or foil strip is formed to obtain a tube, the mutually opposing end regions or parts, or the entire contact surface of the sheet metal strip or foil strip, are connected to each other non-positively or positively or by bonding, or combinations thereof, and the entire length of the tube, or portions thereof, is subjected to a mechanical shape-forming process so that predefinable contours are introduced into the outer or inner circumferential surface of the tube in defined locations by a means, and the tube is divided into an appropriate number of individual elements, and in particular sealing elements, especially sealing rings for turbochargers. | 03-22-2012 |
20120076642 | SEALING ASSEMBLY FOR USE IN TURBOMACHINES AND METHOD OF ASSEMBLING SAME - A method of assembling a sealing assembly for a turbomachine is provided. The method includes positioning at least one sealing element that includes a substantially tortuous flow path defined therein within at least one channel defined in a rotatable element of the turbomachine. The sealing element is extended circumferentially about the rotatable element such that the sealing element extends into a cavity defined between the rotatable element and a stationary element. This facilitates substantially reducing flow leakage from an upstream region of the cavity to a downstream region of the cavity. | 03-29-2012 |
20120082540 | LOW-DUCTILITY OPEN CHANNEL TURBINE SHROUD - A turbine shroud apparatus for a gas turbine engine includes: a plurality of arcuate shroud segments arranged as an annular shroud, each of the shroud segments comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein an open channel is formed through the outer wall of each shroud segment; an annular stationary structure surrounding the shroud segments; and a hanger received in the open channel of each shroud segment and mechanically coupled to the stationary structure, each of the hangers passing through the respective open channel and including an enlarged portion having greater cross-sectional area than the open channel, the enlarged portion engaging the outer wall of the respective shroud segment, so as to retain the shroud segment radially relative to the stationary structure. | 04-05-2012 |
20120121393 | TURBINE - The turbine is provided with a blade ( | 05-17-2012 |
20120121394 | TURBINE AND TURBINE ROTOR BLADE - An object is to provide a turbine and a turbine rotor blade in which it is possible to ensure the strength of the turbine rotor blade and to improve the performance thereof. The turbine includes: rotor blades that rotate about a rotational axis in a main flow channel of a casing; stator vanes that are disposed in the casing; a tip shroud that is disposed at a radially-outward end of each of the rotor blades and whose length in the direction along the rotational axis is reduced as the distance from the rotor blade increases; and a cavity portion that is formed at a position in the casing facing the rotor blades and in which the tip shroud is accommodated. An inclination angle of the inner periphery of the tip shroud is larger than an average inclination angle that is an inclination angle of the inner periphery of the casing, averaged from the trailing edge of the stator vanes disposed at the upstream side of a main flow to the cavity portion disposed at the downstream side of the main flow. | 05-17-2012 |
20120148389 | SEALS IN STEAM TURBINE - A seal structure for a steam turbine is provided, which is capable of suppressing transfer of heat generated by a friction between a rotating portion and a fixed portion to the rotating portion and of suppressing an increase in the temperature of the rotating portion. A labyrinth seal device serves to suppress the amount of steam leaking from a clearance present between each stator blade (fixed portion) of the steam turbine and a rotor (rotating portion). The seal structure for the steam turbine is formed to ensure that permeable spacers made of a permeable metal are provided on the rotor and a seal stationary body and face respective seal fins provided in the labyrinth seal device. | 06-14-2012 |
20120163960 | GAS TURBINE ENGINE AND VARIABLE CAMBER VANE SYSTEM - One embodiment of the present invention is a unique variable camber vane system for a gas turbine engine. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and variable camber vane systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 06-28-2012 |
20120171023 | MOUNTING APPARATUS FOR LOW-DUCTILITY TURBINE SHROUD - A turbine shroud apparatus for a gas turbine engine having a central axis includes: an arcuate shroud segment comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces and collectively defining a shroud cavity; an annular stationary structure surrounding the shroud segment; and a load spreader received in the shroud cavity of the shroud segment and mechanically coupled to the stationary structure. The load spreader includes: a laterally-extending plate with opposed inner and outer faces; and a boss which protrudes radially from the outer face and extends through a mounting hole in the outer wall of one of the shroud segments. A fastener engages the boss and the stationary structure, so as to clamp the boss against the stationary structure in a radial direction. | 07-05-2012 |
20120195742 | TURBINE BUCKET FOR USE IN GAS TURBINE ENGINES AND METHODS FOR FABRICATING THE SAME - A turbine bucket for use with a turbine engine. The turbine bucket includes a dovetail that is coupled to a rotor assembly that is positioned within a turbine casing. A platform extends from the dovetail. An airfoil extends from the platform. The airfoil includes a root end and a tip end. The tip end extends outwardly from the root end towards the turbine casing. A tip shroud extends from the tip end. The tip shroud includes a shroud plate. A first shroud rail extending a first radial distance from the shroud plate towards the turbine casing. A second shroud rail extends a second radial distance from the shroud plate towards the turbine casing that is different than the first radial distance. | 08-02-2012 |
20120219404 | TURBINE SHROUD AND A METHOD FOR MANUFACTURING THE TURBINE SHROUD - A turbine shroud includes a body having a plurality of sides. A first inward facing groove is defined by a first side of the body, and a first seal covers the first inward facing groove to define a first fluid passage in the first inward facing groove along the first side of the body. A first inlet port through the first seal fluid communication through the first seal into the first fluid passage. A method for forming a turbine shroud includes forming an inner surface and forming an outer surface opposed to the inner surface, wherein the outer surface is configured for exposure to a hot gas path. The method further includes defining a first slot in the inner surface and extending a first seal across the first slot to define a first fluid passage in the first slot along the inner surface. | 08-30-2012 |
20120243975 | COMPRESSOR AIRFOIL WITH TIP DIHEDRAL - An airfoil for a compressor is described. The airfoil has a root, an airfoil tip, a leading edge, a trailing edge, airfoil pressure and suction sides extending between the leading edge and the trailing edge. The airfoil has an inner span region and an outer span region and the trailing edge has a dihedral profile such that the trailing edge dihedral angle decreases in at least a portion of the inner span region and the outer span region. | 09-27-2012 |
20120243976 | TURBINE SHELL WITH PIN SUPPORT - A turbine is provided and includes a turbine shell including shrouds at multiple stages thereof, and constraining elements, disposed at least at first through fourth substantially regularly spaced perimetrical locations around the turbine shell, which are configured to concentrically constrain the shrouds of the turbine shell. | 09-27-2012 |
20120288360 | TURBINE - A turbine ( | 11-15-2012 |
20120301279 | HOUSING SYSTEM FOR AN AXIAL TURBOMACHINE - The English-language Abstract from the international application is to be retained and is therefore not duplicated in the specification. | 11-29-2012 |
20120308367 | SEAL ASSEMBLY FOR GAS TURBINE ENGINE - A seal assembly for a gas turbine engine includes a seal body and a biasing support member. The seal body includes a generally annular shape that defines an outer diameter surface. The biasing support member is circumferentially disposed about the outer diameter surface of the ceramic matrix composite seal body and includes an array of spring fingers that circumferentially overlap about the biasing support member. The array of spring fingers contacts the seal body and centers the seal body relative to the centerline axis of the gas turbine engine. | 12-06-2012 |
20130034428 | SEGMENTED SEAL ASSEMBLY - Systems and devices for sealing portions of a rotary machine are disclosed. In one embodiment, a seal assembly element includes: a head flange; an axial neck connected to the head flange, wherein the axial neck includes a mating flange extending circumferentially from a distal end of the seal assembly element, the mating flange configured to form a multidirectional seal with a recessed portion of a complementary seal assembly element; and a set of axial seal teeth connected to the axial neck. | 02-07-2013 |
20130058764 | STEPPED, CONICAL HONEYCOMB SEAL CARRIER - A seal carrier for a seal used between rotating and non-rotating components includes an arcuate sheet metal seal carrier body formed to include a stepped, conical configuration wherein an inner diameter at a forward end is larger than the diameter at an aft end, with plural stepped sections defined by alternating radial and axial portions between the forward end and the aft end. Each axial portion is adapted to carry a seal element, preferably a honeycomb seal. Mounting flanges are provided at the forward end and the aft end of the arcuate sheet metal seal carrier body to enable attachment to the non-rotating component. | 03-07-2013 |
20130058765 | ROTARY MACHINE SEAL ASSEMBLY WITH BUTT GAP SEAL ELEMENTS - Systems and devices for substantially fluidly isolating portions of a rotary machine are disclosed. In one embodiment, a seal assembly for a rotary machine includes: a complementary set of seal segments configured relative one another so as to form a substantially continuous body with butt gaps between the seal segments, the segments including: a head flange; and an axial neck connected to the head flange, wherein the axial neck extends radially inboard and includes an axial slot formed substantially there through; and at least one butt gap seal element, wherein the at least one butt gap seal element includes an axial flange and a radial flange, the axial flange disposed within the axial slots of adjacent seal segments; and the radial flange extending radially inboard from the axial slots to a proximity of the rotary machine substantially forming a barrier to axial flow through the butt gap. | 03-07-2013 |
20130078084 | AIRFOIL AIR SEAL ASSEMBLY - An air seal assembly for a gas turbine engine the air seal comprises a first assembly and a second assembly. One of the first assembly and the second assembly is rotatable relative to the other of the first assembly and the second assembly. The second assembly is aligned annularly with the first assembly and includes a circumferential surface with an abradable coating disposed annularly adjacent to the first and second airfoil tips. The first assembly includes at least one first airfoil with a first tip having an abrasive coating, and at least one second airfoil with a second tip absent the abrasive coating, the at least one first airfoil co-aligned axially and intermingled with a respective at least one second airfoil around a periphery of the first assembly. | 03-28-2013 |
20130084166 | SEGMENTED COMPONENT - A component, in particular for a gas turbine, is disclosed. The component has at least two component segments which are arranged relative to one another leaving a gap and are sealed against each other by a sealing device. The sealing device includes at least one brush seal. Also disclosed is a gas turbine, in particular an aircraft engine, having such a component. | 04-04-2013 |
20130084167 | WEAR-RESISTANT COATING AND USE THEREOF - A rotor blade | 04-04-2013 |
20130094944 | BUCKET ASSEMBLY FOR TURBINE SYSTEM - A bucket assembly is disclosed. The bucket assembly includes an airfoil having a generally aerodynamic contour and defining a tip, and a lower body portion extending generally radially inward from the airfoil. The bucket assembly further includes a tip shroud disposed on the tip of the airfoil and comprising a main body and a rail. The rail includes an exterior surface. The exterior surface defines a microchannel. The bucket assembly further includes a cover layer configured on the exterior surface. | 04-18-2013 |
20130094945 | SEAL STRUCTURE, TURBINE MACHINE HAVING THE SAME, AND POWER GENERATING PLANT EQUIPPED WITH THE SAME - A seal structure includes shrouds that are provided at tips of a plurality of blades on which a main flow of fluid impinges and that come into contact with adjacent shrouds to form a cylindrical shape; a sealing part connected to a structure body facing the shrouds; and a space that is defined by downstream sides of the shrouds, a downstream side of the sealing part, and a wall on a downstream side of the structure body, and that communicates with the main flow of fluid that has impinged on the blades. An end of the wall on the downstream side of the structure body is formed so as to be disposed a predetermined distance away from a shroud extension and away from a sealing-part extension and so as to be located on the opposite side of the shroud extension with respect to the sealing-part extension. | 04-18-2013 |
20130094946 | TURBINE SHROUD THERMAL DISTORTION CONTROL - A shroud for a gas turbine engine includes a leading portion having a leading edge and a first set of circumferentially spaced slots at the leading edge that break up the leading portion into circumferentially spaced segments separated by the first set of slots, and a trailing portion adjacent to the leading portion. The trailing portion has a trailing edge. | 04-18-2013 |
20130108416 | GAS TURBINE ENGINE COMPONENT HAVING WAVY COOLING CHANNELS WITH PEDESTALS | 05-02-2013 |
20130108417 | FIBER PREFORM FOR A TURBINE RING SECTOR, AND ITS METHOD OF FABRICATION | 05-02-2013 |
20130136582 | SHROUD SEGMENT PRODUCING METHOD AND SHROUD SEGMENT - Disclosed herein is a production method of a shroud segment that includes a forming process of molding a cylindrical fiber fabric ( | 05-30-2013 |
20130164119 | SEAL STRUCTURE AND CENTRIFUGAL COMPRESSOR - Provided is a seal structure ( | 06-27-2013 |
20130170962 | Forward Step Honeycomb Seal for Turbine Shroud - The present application provides a stage of a gas turbine engine. The stage may include a bucket, a shroud facing the bucket, and a forward step honeycomb seal on the shroud. The forward step honeycomb seal may include a forward step portion and one or more linear portions. | 07-04-2013 |
20130170963 | HYBRID BLADE OUTER AIR SEAL FOR GAS TURBINE ENGINE - A Blade Outer Air Seal (BOAS) includes a body manufactured of a metal alloy, the body includes a face opposite a forward interface and an aft interface, the face includes a cavity. A non-metallic insert within the cavity such that the insert is flush with the face. | 07-04-2013 |
20130189085 | TURBOMACHINE SEAL ARRANGEMENT - The present invention relates to a seal arrangement for a turbomachine, in particular a gas turbine, having a plurality of rows, arranged in succession in the axial direction (A), of shells ( | 07-25-2013 |
20130189086 | SEAL ASSEMBLY, METHOD AND TURBOMACHINE - A sealing arrangement for a turbomachine for sealing a radial gap between a rotor and a stator, with a plurality of sealing segments each comprising a honeycomb element and a base body for holding the honeycomb element, and with at least one support for arranging the sealing segments on a rotor section or stator section, wherein the base bodies can be arranged on the at least one support by a radial movement and by a plastic deformation of at least one body section, a generative method for the integral production of the sealing segments, and a turbomachine are disclosed. | 07-25-2013 |
20130202419 | METHOD FOR FASTENING A BRUSH SEALING ELEMENT IN A GROOVE OF A HOUSING SEGMENT - A sealing system and method is disclosed. The sealing system includes a brush sealing element and an accommodating element with an accommodating chamber. The brush sealing element is disposed in the accommodating chamber and a bendable strap is disposed on the accommodating element. The method includes fastening the brush sealing element in the accommodating chamber of the accommodating element. The accommodating element is arranged in a groove of a housing segment and a position of the accommodating element is secured on the housing element by bending the strap of the accommodating element to engage with a side wall of the housing segment. | 08-08-2013 |
20130266426 | SEALING SYSTEM FOR A TURBOMACHINE - Disclosed is a sealing system for a turbomachine, in particular for a gas turbine, the sealing system being formed in an annular space between a flow-limiting wall of the turbomachine and at least one rotor blade tip of a rotor blade or an outer shroud arranged on the rotor blade tip, and comprising at least one sealing point. The sealing point comprises at least one run-in coating arranged on the rotor blade tip or on the outer shroud in the direction of the flow-limiting wall of the turbomachine. The invention furthermore encompasses a gas turbine comprising the sealing system. | 10-10-2013 |
20130280048 | SEAL FOR A TURBINE SYSTEM - A seal for a turbine system includes a rotor, a bowl region and a stator assembly having a tip strip disposed proximate the rotor. Also included is a packing head disposed proximate the tip strip. Further included is a flex seal having a first end portion fixedly secured to at least one of the tip strip and the packing head, with a second end portion slidably engaged with at least one of the tip strip and the packing head. | 10-24-2013 |
20130309073 | DETACHABLE FAN BLADE PLATFORM AND METHOD OF REPAIRING SAME - A fan section for a gas turbine engine includes a hub. A fan blade is secured to the hub. A platform is removably secured to the hub and is arranged adjacent to the fan blade. The platform has a body with lateral sides that each include a channel. A seal is removably received in each of the channels, with one of the seals abutting the fan blade. A method of repairing the fan blade platform includes the steps of removing a nose cone to provide access to a hub, detaching a platform from the hub, and pulling the seal from a groove in the platform. | 11-21-2013 |
20130323031 | TURBINE DAMPER - A damper for a turbine rotor assembly of a gas turbine engine is disclosed. The damper includes a width dimension, a height dimension, and a length dimension and a forward plate. The damper further includes an aft plate that is larger than the forward plate along the width and height dimension and having a lower portion including two legs extending in the height dimension. The damper also includes a longitudinal structure extending in the length dimension and connecting the forward plate and the aft plate. | 12-05-2013 |
20130323032 | BLADE OUTER AIR SEAL FOR A GAS TURBINE ENGINE - A blade outer air seal (BOAS) segment according to an exemplary embodiment of the present disclosure can include a seal body having a radially inner face and a radially outer face that circumferentially extend between a first mate face and a second mate face and axially extend between a leading edge face and a trailing edge face. At least one of the first mate face, the second mate face, the radially outer face and the radially inner face can include an inner wall having a ledge and an undercut passage radially inward from the ledge that extends uninterrupted along a length of the ledge. | 12-05-2013 |
20130323033 | BLADE OUTER AIR SEAL WITH CORED PASSAGES - A blade outer air seal for a gas turbine engine includes a wall, a forward hook, and an aft hook. The wall extends between the forward hook and the aft hook, which are adapted to mount the blade outer air seal to a casing of the gas turbine engine. The wall includes a cored passage extending along at least a portion of the wall. The cored passage extends radially and axially through a portion of the aft hook to communicate with one or more apertures along a trailing edge of the aft hook. | 12-05-2013 |
20140017072 | BLADE OUTER AIR SEAL WITH COOLING FEATURES - A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. At least one cooling fin is disposed on the radially outer face between the leading edge portion and the trailing edge portion. | 01-16-2014 |
20140030071 | BLADE OUTER AIR SEAL FOR A GAS TURBINE ENGINE - A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. The BOAS includes a trough disposed on the radially inner face and an abradable seal received within the trough. The trough is open to expose a leading edge of the abradable seal to a core flow path of the gas turbine engine. | 01-30-2014 |
20140030072 | SEAL SEGMENT - A seal segment is positioned, in use, radially adjacent the rotor. The seal segment has first and second circumferentially spaced passageways each of which extends in the fore and aft direction. In use, a first support bar is contained within the first passageway, and a second support bar is contained within the second passageway. The first and second support bars being mountable to complementary formations provided by the casing of the engine. The first passageway is configured such that the seal segment is fixed relative to the first support bar in the radial and circumferential directions. The second passageway is configured such that the seal segment is fixed relative to the second support bar in the radial direction but allows relative movement of the seal segment and the second support bar in the circumferential direction to accommodate differential thermal expansion of the seal segment and the casing. | 01-30-2014 |
20140044528 | BLADE OUTER AIR SEAL HAVING ANTI-ROTATION FEATURE - A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. At least one of the leading edge portion and the trailing edge portion includes a solid wall and a perforated wall. At least a portion of the perforated wall is spaced from the solid wall such that a passage extends between the solid wall and the perforated wall. | 02-13-2014 |
20140044529 | SEALING OF THE FLOW CHANNEL OF A TURBOMACHINE - A turbomachine having a flow channel and a housing radially surrounding the flow channel, a plurality of stationary and moving blades being situated in the flow channel, stationary blades being situated adjacent to the moving blades in the axial direction, and the stationary blades having at least one stationary blade hook which engages with at least one housing hook for the purpose of connecting the stationary blades to the housing. A sealing and lining element is situated in the radial direction between the moving blades adjacent to the stationary blades and the housing, and has a sealing structure interacting with blade tips of the moving blades. A heat protection element is provided in the area between the sealing and lining element and the housing, and a sealing element being situated on the heat protection element for the purpose of sealing contact with the housing hook. | 02-13-2014 |
20140105731 | AXIAL SEAL IN A CASING STRUCTURE FOR A FLUID FLOW MACHINE - A casing structure for a fluid flow machine, in particular for a gas turbine or an aircraft engine, including an outer casing wall and an inner casing wall, which annularly surround a flow channel of the fluid flow machine and are spaced apart in a radial direction with respect to the flow channel. At least one cavity is formed between the inner and outer casing walls. The cavity is axially divided into at least two regions which are separated from each other by an axial seal in such a way that different pressure conditions are created according to the axial position of these regions, which different pressure conditions correspond to the pressure conditions in the flow channel. A corresponding fluid flow machine such as, for example, an aircraft engine. | 04-17-2014 |
20140119899 | BELLY BAND SEAL WITH UNDERLAPPING ENDS - A sealing band for use in a turbomachine having a plurality of stages, each stage comprising a rotatable disk and blades carried thereby. At least one pair of adjacent rotatable disks define an annular gap therebetween and have respective opposing sealing band receiving slots aligned with the annular gap. The sealing band includes a plurality of seal strips located in series adjacent to one another, and adjacent seal strips include opposing end faces located in facing relationship adjacent to one another. An underlap portion is affixed adjacent to an end of at least one seal strip and extends past the end face of an adjacent seal strip, along a radially facing side of the adjacent seal strip. | 05-01-2014 |
20140119900 | GAS TURBINE INCLUDING BELLY BAND SEAL ANTI-ROTATION DEVICE - A sealing band located in opposing seal band receiving slots of adjacent turbine disks to seal an annular gap therebetween. An anti-rotation body including a base portion is located between edges of the sealing band within the annular gap, and a pin portion extends axially from the base portion for engagement with a cut-out portion of at least one of the disks. A pair of spaced projections extend from the base portion and into through openings in the sealing band at a location within the annular gap. The projections define an attachment structure attaching the anti-rotation body to the sealing band. | 05-01-2014 |
20140119901 | Axial Flow Turbine - An axial flow turbine that can enhance an effect of reducing a mixing loss is disclosed. The axial flow turbine includes a plurality of stator blades provided on the inner circumferential side of a diaphragm outer ring; a plurality of rotor blades provided on the outer circumferential side of a rotor; a shroud provided on the outer circumferential side of the plurality of rotor blades; an annular groove portion formed in the diaphragm outer ring and housing the shroud therein; a clearance passage defined between the groove portion and the shroud, into which a portion of working fluid flows from the downstream side of the stator blades in a main passage; seal fins provided in the clearance passage; a circulation flow generating chamber defined on the downstream side of the clearance passage; and a plurality of shielding plates secured to the diaphragm outer ring. | 05-01-2014 |
20140119902 | SEAL CARRIER ATTACHMENT FOR A TURBOMACHINE - A housing structure for a turbomachine having a stationary blade ring annularly surrounding a flow channel, and having a seal carrier ring which also annularly surrounds the flow channel, the stationary blade ring and the seal carrier ring being connected to each other, and either the stationary blade ring or the seal carrier ring having a one-sidedly open receptacle in the radial direction in relation to the flow channel and a radially projecting engagement area which corresponds to the connected seal carrier ring or stationary blade ring and which is held in a form-fitting manner in the axial direction and in the radial direction in the direction of the closed side of the receptacle but is freely movable with respect to the connected receptacle and the seal carrier ring or stationary blade ring having this receptacle in the radially opposite direction in the direction of the receptacle opening. | 05-01-2014 |
20140127006 | BLADE OUTER AIR SEAL - A blade outer air seal for a gas turbine engine includes a first side surface, a second side surface, and a wall. The wall extends between the first side surface and the second side surface and has one or more holes formed therein. The holes are spaced from the first side surface and/or the second side surface and have areas between about 0.005% and 0.450% of a surface area of the blade outer air seal. | 05-08-2014 |
20140140825 | BLADE OUTER AIR SEAL HAVING INWARD POINTING EXTENSION - A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion and a seal land that extends from the seal body and includes an inward pointing extension that extends radially inwardly from the radially inner face. | 05-22-2014 |
20140154061 | TURBINE - Provided is a turbine. One of a tip portion of a blade and a portion of a partition plate outer ring corresponding to the tip portion of the blade is provided with a step part having a step face that protrudes toward the other, and the other is provided with seal fins) extending out with respect to the step part and forming minute clearance between the step part and the other. The step part facing the seal fins is configured to protrude so that a cavity forming a main vortex and counter vortex being formed by the main vortex are formed on an upstream side of the seal fins. The cavity is formed so that an axial width dimension and a radial height dimension satisfy Formula expressed by 0.45≦D/W≦2.67. | 06-05-2014 |
20140161596 | TURBINE SHROUD ENGAGEMENT ARRANGEMENT AND METHOD - According to one aspect of the invention a turbine shroud engagement arrangement includes an outer shroud and an inner shroud operably connectable to the outer shroud. The outer shroud has at least one of a channel formed in and a protruding member extending from an inner radial surface thereof. The inner shroud has at least one of a protruding member extending from an outer radial surface thereof that is complementary to the at least one channel of the outer shroud or a channel formed in the outer radial surface that is complementary to the at least one protruding member of the outer shroud. The turbine shroud engagement arrangement is primarily axially slidably engagable and configured to radially support the inner shroud relative to the outer shroud. | 06-12-2014 |
20140169953 | DRUM SEAL - A gas turbine engine comprising at least one drum pack having two or more annular discs | 06-19-2014 |
20140178183 | ROTATION MECHANISM AND INTERNAL UNIT OF ROTATION MECHANISM - A rotation mechanism includes: a casing which is configured to be vertically split into two portions and includes an upper half portion on the upper side and a lower half portion on the lower side; an internal unit which is disposed in the casing and has a configuration in which a rotor which rotates around an axis thereof, a bearing portion which rotatably supports the rotor, and an annular seal portion which seals a gap surrounding a circumferential surface of the rotor so as to enable the rotor to rotate are integrated; an axial movement restricting portion which includes a fitting concave portion provided on one of the casing and the internal unit and a fitting convex portion provided on the other thereof to be fitted into the fitting concave portion as a pair and restricts relative movement between the casing and the internal unit in a direction of axis; and a tapered surface which is formed on each of the fitting concave portion and the fitting convex portion so that a width thereof in the direction of axis increases toward an inner circumferential side in a radial direction. | 06-26-2014 |
20140186163 | BLADE OUTER AIR SEAL HAVING SHIPLAP STRUCTURE - A blade outer air seal (BOAS) for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion and a shiplap structure that at least partially overlaps at least a portion of at least one of the leading edge portion and the trailing edge portion. | 07-03-2014 |
20140205444 | TURBOMACHINE HAVING SWIRL-INHIBITING SEAL - Various embodiments include a turbomachine including a swirl-inhibiting seal. In various particular embodiments, a turbomachine includes: a rotor section having sets of axially disposed blades; a diaphragm section at least partially surrounding the rotor section, the diaphragm section including a set of nozzles positioned between adjacent sets of axially disposed blades, wherein the set of nozzles includes at least one nozzle having: a base section coupled to the diaphragm section; a blade coupled to the base section; and a radial tip section coupled to a radial end of the blade, the radial tip section including an axially extending flange having a slot extending therethrough for controlling fluid flow within the turbomachine. | 07-24-2014 |
20140219787 | ANNULAR SEALS FOR NON-CONTACT SEALING OF FLUIDS IN TURBOMACHINERY - According to an aspect of the disclosure, an annular seal generally includes a hollow member having two ends and an inner surface. The hollow member has a number of depressions formed in and extending around its inner surface. Each of the depressions having a depth that is a function of its distance from one of the two ends. | 08-07-2014 |
20140248139 | TURBOMACHINE BUCKET HAVING FLOW INTERRUPTER AND RELATED TURBOMACHINE - Various embodiments include a turbomachine bucket having a flow interrupter, as well as related turbomachines. Various embodiments include a turbomachine bucket having: a base section sized to couple with a turbomachine rotor, the base section having a leading edge and a trailing edge opposing the leading edge; a blade section coupled to the base section and aligned to extend radially from the base section; a shroud coupled to the blade section and aligned to extend radially from the blade section; and a flow interrupter coupled to the leading edge of the base section. | 09-04-2014 |
20140271142 | Turbine Shroud with Spline Seal - A turbine shroud assembly comprises a honeycomb rub strip, a metallic backsheet disposed along an upper edge of said honeycomb seal structure, a shroud frame having a first rail and a second rail disposed at lateral edges of said metallic backsheet, a first support and a second support connected to the first rail and the second rail, a spline extending axially in the first rail and the second rail along laterally outer surfaces of the first rail and the second rail and, a spline seal having a first edge and a second opposite edge, the first edge disposed in each of the spline grooves and the second opposite edge being capable of positioning in an adjacent shroud assembly. | 09-18-2014 |
20140271143 | Fan Spacer Having Unitary Over Molded Feature - A fan spacer for placement between a pair of adjacent blades in a fan assembly and a related method of making. The fan spacer has a spacer body including an airflow surface shaped to direct air between the pair of adjacent blades in which the airflow surface is shaped on opposing sides to correspond to the pair of adjacent blades. An over molded feature is molded onto the airflow surface of the spacer body in which the over molded feature both includes an erosion coating on the airflow surface and, on the two opposing sides, seals configured to seal against the pair of adjacent blades on the opposing sides of the airflow surface. | 09-18-2014 |
20140271144 | TURBINE SHROUD - A turbine shroud for a gas turbine engine includes an annular metallic carrier, a blade track, and a cross-key connection formed between the annular metallic carrier and the ceramic blade track. The cross-key connection is formed between the annular metallic carrier and inserts included in the blade track. The inserts are bonded to an annular runner also included in the blade track by a braze layer. | 09-18-2014 |
20140271145 | TURBINE BLADE TRACK ASSEMBLY - A gas turbine engine is disclosed with a turbine section having at least one turbine rotor with a plurality of turbine blades, a plurality of blade tracks positioned circumferentially around the turbine blades, at least one dovetail shaped connecting member extending radially outward from each blade track, and a hanger connected to a structural member of the gas turbine engine and configured to releasably couple with the at least one dovetail shaped connecting member of a corresponding blade track. | 09-18-2014 |
20140271146 | ANTI-ROTATION LUG AND SPLITLINE JUMPER - The present invention relates to a system and method for joining adjacent sections of a compressor diaphragm. A splitline jumper is positioned within a recessed portion of a seal ring segment of the adjacent compressor diaphragms. The splitline jumper is sized and oriented so as to prevent axial movement of the compressor diaphragms relative to each other and also to prevent rotational movement of the seal ring relative to the diaphragm. | 09-18-2014 |
20140286761 | CENTRIFUGAL COMPRESSOR - Disclosed is a centrifugal compressor capable of minimizing leakage of fluid while realizing high aerodynamic performance in the process of compressing the fluid. The centrifugal compressor includes an impeller having blades, a housing formed with an inlet and an outlet, a sealing unit disposed adjacent to one of the inlet and the outlet, and a partial shroud disposed adjacent to the sealing unit and formed at one of the inlet and the outlet to partially surround outer peripheral portions of outer ends of the blades. | 09-25-2014 |
20140294570 | TURBOMACHINE - Disclosed are a turbomachine having at least one radial gap seal which has at least two opposite ceramic coatings which are constructed in each case from a ceramic powder, the particle size of which is smaller than 1.0 μm, and a turbomachine having at least one radial gap seal, wherein the coatings are built up from powder-based individual layers, the outer layer of which has a higher ceramic fraction than a base layer close to the rotor or stator section respectively, wherein the particle size of the powder material is smaller than 1.0 μm. | 10-02-2014 |
20140341721 | SHROUD ARRANGEMENT FOR A GAS TURBINE ENGINE - Described is a shroud arrangement for a gas turbine engine, comprising: a seal segment for bounding a hot gas flow path within the gas turbine engine, the seal segment being attached to a casing of the engine via at least one fore attachment and at least one aft attachment, the fore and aft attachment restricting radial movement of the seal segment relative to the engine casing; and, an axial restrictor which prevents axial movement of the seal segment relative to the engine casing, the axis being the principal rotational axis of the engine, wherein the fore and aft retention features are slidably engaged with a carrier segment or engine casing from a common direction. Also described is a gas turbine engine having the shroud arrangement. | 11-20-2014 |
20140363279 | NON-INTEGRAL SEGMENTED ANGEL-WING SEAL - A cover plate adapted to axially overlie root or shank portions of one or more buckets or blades secured to a turbomachine wheel, includes an arcuate cover plate body adapted to be secured to the turbomachine wheel so as to cover a root portion of at least one of the turbine buckets or blades; and at least one arcuate angel-wing seal segment detachably secured to one side of the arcuate cover plate body. | 12-11-2014 |
20150016969 | Turbomachine, Sealing Segment, and Guide Vane Segment - A turbomachine includes a sealing segment ring that is provided between a front guide vane row and a back guide vane row for sealing a radial gap between a casing section and a rotor blade row rotating between the guide vane rows, wherein the sealing segment ring has a plurality of identical sealing segments and at least one of the guide vane rows has a plurality of identical guide vane segments, wherein the sealing segments each have a plurality of engagement sites lying adjacent to one another in the peripheral direction for interaction with securing elements of this guide vane row, wherein the engagement sites and securing elements are distributed uniformly over the periphery and the engagement sites are a multiple of the securing elements, a sealing element, and a guide vane segment. | 01-15-2015 |
20150016970 | BLADE TRACK ASSEMBLY, COMPONENTS, AND METHODS - A blade track assembly is disclosed having a variety of features. The assembly can have annular or segmented components, or a combination of the two. In one form the assembly includes blade tracks having a forward and aft edge that can be received in an opening of respective hangers. The hangers can include anti-movement features to discourage movement of a blade track. A rib can extend between hangers and in one form can be used as part of a seal assembly. Clips can be used to secure the blade track in openings of the respective hangers, as well as to discourage movement of the blade track. | 01-15-2015 |
20150056068 | BELLY BAND SEAL WITH CIRCUMFERENTIAL SPACER - A circumferentially extending sealing band is located within sealing band receiving slots formed in adjacent turbine engine disks. The sealing band includes a plurality of seal strips forming overlap joints defined by overlapping end portions, each formed by a tongue portion extending from a seal face of one seal strip past a seal face of the adjacent seal strip, along a radially inward facing side of the adjacent seal strip. A joint gap is defined within at least one overlap joint between the seal face of the one seal strip and the seal face of the adjacent strip, and a spacer is affixed to the one seal strip and is located at a position within the joint gap between the seal faces to limit circumferential movement of the seal faces toward each other. | 02-26-2015 |
20150071769 | METHOD FOR DISASSEMBLY AND ASSEMBLY OF A ROTOR OF A GAS TURBINE - A method for disassembly of a rotor, in particular the front rotor of a gas turbine with a housing and a channel which diverges in a direction of flow and in which the rotor is arranged, is disclosed. An embodiment of the method includes axially displacing an outer sealing ring that is radially opposite the rotor, and whose minimum inside diameter is smaller than the maximum outside diameter of the rotor, against the direction of flow. Then, the rotor is axially displaced against the direction of flow, in particular out of the housing. A method for assembly of such a rotor, as well as a tool for the same, is also disclosed. | 03-12-2015 |
20150071770 | ANGULAR STATOR SECTOR FOR A TURBOMACHINE COMPRESSOR COMPRISING A BRUSH SEAL - The main object of the invention is an angular stator sector ( | 03-12-2015 |
20150104297 | TURBOCHARGER - A turbocharger has a casing system which houses a centrifugal impeller connected to a turbine by a shaft. The casing system includes an insert casing which forms a duct for feeding air to and through the impeller, and a volute casing which forms a volute for receiving compressed air from the impeller, the insert casing inserting into the volute casing. The casing system further includes a main casing which forms a housing for the shaft and for the shaft-side end of the impeller. The impeller includes a hub which has a radially outer annular rim, and has front and rear faces which converge towards the rim from respectively the inlet side and the shaft side of the hub. The impeller further includes a plurality of circumferentially arranged vanes on the front face of the hub. The impeller further includes a seal formation formed on the rear face at the rim. | 04-16-2015 |
20150104298 | TIP TREATMENT BARS IN A GAS TURBINE ENGINE - There is presented a casing arrangement for a gas turbine engine. The casing arrangement includes a plurality of tip treatment bars extending between a pair of spaced-apart annular supports, with each tip treatment bar being elongate and supported at each end by a respective support such that each end of the bar is received within an opening formed in the respective support. At least the ends of each tip treatment bar are tapered in transverse cross-section so as to have a wedge-shaped profile, and the openings in the supports have a complementary tapered shape for receipt and retention of the bar ends therein. | 04-16-2015 |
20150110610 | SUPERCHARGER ASSEMBLY WITH ROTOR END FACE SEAL AND METHOD OF MANUFACTURING A SUPERCHARGER ASSEMBLY - A supercharger assembly has a rotor housing defining a chamber. A rotor is within the chamber and has an end with an end face. A seal has a seal face adjacent the end face. The seal face and the end face have complex topographies configured to be complementary to define a gap therebetween. The complex topographies can be, but are not limited to, interfitting concentric annular channels. The gap functions as a tortuous flow path to inhibit fluid flow past the end face. A method of manufacturing a supercharger assembly is also provided. | 04-23-2015 |
20150139786 | RUN-IN COATING BASED ON METAL FIBERS - The present invention relates to a run-in coating for a turbomachine, in particular for an aero engine, to be attached to a seal between a rotor and a stator, wherein the run-in coating comprises a metallic scaffold having interstices which are filled with an inorganic-nonmetallic filler material, and wherein the metallic scaffold is formed from an arrangement of metal fibers ( | 05-21-2015 |
20150300190 | ROTATING MACHINE - A steam turbine through which a fluid flows along an axis is equipped with: a tip shroud for turbine blades that are provided on a shaft that extends with the axis as a center; an outer partition plate ring that is provided on a casing so as to face the tip shroud in a radial direction and be capable of rotating relative to the tip shroud around the axis; seal fins that extend radially inward from the outer partition plate ring and that, with the tip shroud, form minute gaps therebetween; and steam introduction surfaces that are formed on downstream sides of the seal fins and are provided so as to face the seal fins within cavities where a main vortex, generated from a leakage flow passing through a minute gap, is generated, and that guide the flow, generated from the main vortex, toward the minute gaps. | 10-22-2015 |
20150330239 | SEAL SUPPORT DISK AND ASSEMBLY - An assembly for a gas turbine engine includes a first module, a second module interconnected with the first module, a first gas turbine component, and a seal assembly. The first gas turbine component includes a body extending generally radially between an inner mounting portion and an outer seal carrier portion. The inner mounting portion is fastened to the first module such that the first gas turbine component forms a boundary between a first annular cavity in the first module, and a second annular cavity in the second module. The seal assembly is mounted to the seal carrier portion of the first gas turbine component, and includes a flow diverter assembly having a flow diverter and a finger seal commonly fastened to a first axial side of the seal carrier portion. | 11-19-2015 |
20150330241 | GAS TURBINE SEAL ASSEMBLY AND SEAL SUPPORT - A gas turbine engine assembly includes a second module connected axially to a first module along a joint, and an annular cavity defined between the first module and the second module. The seal assembly is disposed proximate the cavity, and includes a seal support ring, a first finger seal, and a second finger seal. The support ring has a backing portion secured to a radial wall of to the first module, and a first seal land extending axially into the cavity away from the first module. The first finger seal has a free end adapted to contact an inner side of the first seal land. The second finger seal is adapted to seal a radially outer portion of the annular cavity | 11-19-2015 |
20150330242 | TURBINE ARRANGEMENT WITH IMPROVED SEALING EFFECT AT A SEAL - A turbine arrangement and a gas turbine engine comprising a rim seal is configured with two cavities. The main fluid path, the two cavities, and a disc space are furthermore separated from another, but still in fluid communication with another, via three annular seal passages. A rim seal is configured for an upstream rotor blade and a downstream guide vane. The seal arrangement includes a trailing edge of the inner blade platform, a leading edge of the inner vane platform and a first annular cavity and a second annular cavity. | 11-19-2015 |
20150330245 | FLOW DIVERTER ELEMENT AND ASSEMBLY - An assembly for a gas turbine engine, comprises a fairing assembly extending generally axially through a portion of the gas turbine engine, a first component disposed radially inward of the fairing assembly, a second component disposed axially adjacent to the first component, a flow diverter, and a finger seal. The flow diverter includes a mounting portion securing the flow diverter to the first component, and an arm extending in an axial direction from the mounting portion toward the second component. The finger seal includes a fixed end secured between the flow diverter mounting portion and the first component. | 11-19-2015 |
20150337672 | GROOVED BLADE OUTER AIR SEALS - A blade outer air seal for a turbomachine includes a base portion configured to attach to a turbomachine housing, a thermal coating disposed on the base portion, and at least one groove defined in an external surface of the thermal coating. The groove can be machined. A method of manufacturing a blade outer air seal includes disposing a thermal coating on a base portion, and machining at least one groove into the thermal coating. The method can also include using an automated force sensing and vision sensing equipped robotic system. | 11-26-2015 |
20150337673 | Segmented Clearance Control Ring - A clearance control ring having at least two segments is disclosed. Each of the segments interlock with adjacent segments to form a full hoop clearance control ring. Separate carriers and seals or one-piece carriers and seals may be mounted on the clearance control ring. The segmented structure of the clearance control ring allows for simpler assembly with segmented cases for gas turbine engines than prior art one-piece clearance control rings. The segmented structure also may be used with one-piece pre-assembled and multi-stage rotors. | 11-26-2015 |
20150354388 | TURBINE SHROUD MILLING - An exemplary shroud milling method includes milling a convex side of a shroud, milling a concave side of the shroud, and holding a shroud within a common fixture when milling the convex side and when milling the concave side. | 12-10-2015 |
20150354391 | TURBINE ARRANGEMENT WITH IMPROVED SEALING EFFECT AT A SEAL - A turbine arrangement and a gas turbine engine including a rim seal is configured with two cavities. The main fluid path, the two cavities, and a disc space are furthermore separated from another, but still in fluid communication with another, via three annular seal passages. The turbine arrangement also includes a plurality of cooling fluid injectors arranged underneath a radially inner vane platform. The rim seal is configured for an upstream guide vane and a downstream rotor blade. | 12-10-2015 |
20150369076 | HYBRID PASSIVE AND ACTIVE TIP CLEARANCE SYSTEM - A control ring extends circumferentially about a central axis. A plurality of circumferentially spaced carrier portions have a cavity receiving the control ring. There are circumferential gaps between the carrier portions. A blade outer air seal is mounted on the carrier portions radially inwardly of the control ring. The control ring maintains the carrier portions at a radially outwardly expanded position when heated by an electric heater. | 12-24-2015 |
20160003076 | KNIFE EDGE WITH INCREASED CRACK PROPAGATION LIFE - A knife edge seal includes a pedestal and a knife edge with a tip and a base. The base rests on the pedestal. The base has a first width and the tip has a second width, and the ratio of the first width to the second width is in the range of 5:1 to 15:1. A gas turbine engine and a method of sealing a high pressure area from a low pressure area are also disclosed. | 01-07-2016 |
20160003080 | GAS TURBINE ENGINE SEAL ASSEMBLY - A seal assembly is positioned within a cavity that extends circumferentially about an axial centerline of a gas turbine engine. The cavity includes a cavity wall. The seal assembly includes a seal and a seal protector. The seal extends circumferentially within the cavity. The seal protector extends circumferentially within the cavity. The seal protector is positioned between the seal and the cavity wall. The seal protector includes a locating feature that is operative to contact the seal to aid in axially positioning the seal protector relative to the seal. | 01-07-2016 |
20160003081 | FLEXIBLE FINGER SEAL FOR SEALING A GAP BETWEEN TURBINE ENGINE COMPONENTS - An assembly for a turbine engine includes a turbine engine first component, a turbine engine second component and a flexible seal that is attached to the first component. The flexible seal at least partially seals a gap between the first component and the second component. The flexible seal includes a mount and a finger seal that sealingly engages the second component. The mount includes a boss that sealingly engages the first component. | 01-07-2016 |
20160010482 | Low Leakage Multi-Directional Interface for a Gas Turbine Engine | 01-14-2016 |
20160032746 | ASSEMBLY FOR SEALING A GAP BETWEEN COMPONENTS OF A TURBINE ENGINE - A turbine engine assembly includes a first component, a second component and a third component arranged along an axis. The first component houses at least a portion of the third component. The assembly also includes a seal carrier, a seal land and a seal element, which seals a gap between the seal carrier and the seal land. The seal carrier is connected to the first component, and includes a groove surface and a groove. A first portion of the seal carrier seals a gap between a second portion of the seal carrier and the second component. The seal land is connected to the third component and includes a seal land surface. The seal element extends radially into the groove. The seal element is axially engaged with the groove surface and radially engaged with the seal land surface. | 02-04-2016 |
20160040546 | COMPRESSOR CASING - A gas turbine engine shroud for surrounding one of a rotor and a stator having a plurality of radially extending airfoils is provided. The shroud includes an annular body defining an axial and a radial direction. The body has a radially inner surface and a plurality of indentations is annularly defined therein. Each of the plurality of indentations has a depth of an order of magnitude of a clearance between the one of the rotor and the stator and the inner surface. The plurality of indentations is defined in a region of the inner face defined axially between projections of leading and trailing edges of the airfoils onto the inner surface of the annular body. | 02-11-2016 |
20160040548 | CERAMIC COATING SYSTEM AND METHOD - A gas turbine engine article includes a substrate and a bond coating that covers at least a portion of the substrate with a step formed in at least one of the substrate and the bond coating. A thermally insulating topcoat is disposed on the bond coating. The thermally insulating topcoat includes a first topcoat portion separated by at least one fault that extends through the thermally insulating topcoat from a second topcoat portion. | 02-11-2016 |
20160047265 | ROTATING MACHINE - A rotating machine includes a casing ( | 02-18-2016 |
20160053624 | RADIAL POSITION CONTROL OF CASE SUPPORTED STRUCTURE WITH AXIAL REACTION MEMBER - A radial position control assembly for a gas turbine engine stage includes a case structure. A supported structure is operatively supported by the case structure. A support ring operatively supports the supported structure. The supported structure and the support ring have different coefficients of thermal expansion. A sealing structure is adjacent to the supported structure. The support ring maintains the supported structure relative to the sealing structure at a clearance during thermal transients based upon a circumferential gap between adjacent supported structure and based upon a radial gap between the support ring and the supported structure. A pin supports the supported structure relative to the case structure and is configured to isolate the support ring from loads on the supported structure. | 02-25-2016 |
20160061212 | RADIAL COMPRESSOR STAGE - A radial compressor stage includes: an impeller, rotatable relative to a stator, the impeller having multiple impeller blades on a rotor side; a diffuser positioned in a flow direction downstream of the impeller, the diffuser having multiple guide blades on the stator side; an impeller side gap formed between the impeller and the stator; and an intermediate flow channel extending between the impeller and the diffuser. A gap is formed between an outer edge of a downstream back side of the impeller and an opposite inner edge of the stator, the gap being sealed via a seal such that the seal seals the impeller side gap from the intermediate flow channel. | 03-03-2016 |
20160069217 | PANELS OF A FAN OF A GAS TURBINE - An aircraft gas turbine with a fan disc at which fan blades 31, distributed around the circumference and forming an intermediate space in between each other, are attached, with a sealing disc that is arranged on the back side of the fan disc, and with an inlet cone that is mounted at the front side of the fan disc, as well as with filling elements that are arranged in the intermediate spaces, characterized in that the inlet cone includes strip-shaped lugs which are configured in one piece with the same and which can be inserted into the intermediate spaces, with their free ends being inserted into a ring groove that is formed at the sealing disc, and in that a filling element is arranged on each strip-shaped | 03-10-2016 |
20160084099 | THERMALLY PROTECTED SEAL ASSEMBLY - A seal assembly that may be for turbine engine includes first and second rings with a convoluted seal resiliently compressed there-between. The seal may define a gap for receipt of a thermally resistant shield that may also reduce wear of the seal. The seal may include a hole for the flow of cooling air and the shield may be porous so as not to obstruct the cooling air flow for cooling of the seal. | 03-24-2016 |
20160084168 | Chemistry Based Methods of Manufacture for Maxmet Composite Powders - A method of manufacturing a gas turbine engine air seal comprising forming at least one MAX phase particle. The method includes coating the at least one MAX phase particle with a metallic shell. The method includes applying the at least one MAX phase metallic coated particle to a surface of a substrate of the air seal to form an abradable layer of a MAXMET composite abradable material from the at least on MAX phase metallic coated particle. | 03-24-2016 |
20160090853 | SEAL ASSEMBLY FOR SEALING AN AXIAL GAP BETWEEN COMPONENTS - A seal assembly extends along an axis and seals an axial (and/or radial) gap between a first component and a second component. The seal assembly includes a seal carrier and a seal element. The seal element extends axially (and/or radially) between a first portion and a second portion. The first portion of the seal element is slidingly arranged within a slot in an axial end (or a radial side) of the seal carrier. The second portion of the seal element is configured to axially (and/or radially) engage the second component. | 03-31-2016 |
20160090866 | SHROUD SEGMENT RETAINER - A gas turbine, including: axially adjacent first and second components each having a gas path facing surface within an engine casing, inter-component cavity located between first and second components on the gas path outboard side, an axial-restrictor within the inter component cavity for restricting movement of the first or second component relative to at least one other first and second component or engine casing, wherein the axial-restrictor is radially located in the engine casing or other first and second component and includes a radially facing surface; a retaining element, including a body having circumferential length extending around the gas turbine engine and axial length extending between axially adjacent first and second components when in use; an obstructing portion between the radially facing surface of the axial-restrictor and opposing second radial surface of the other first or second component or engine casing to restrict radial movement of in use axial-restrictor. | 03-31-2016 |
20160097294 | BRUSH SEAL PLATE - A brush seal plate may comprise a flat ring with bristles protruding from an inner diameter of the flat ring. The brush seal plate may have a racetrack slot to allow the flat ring to move in a radial direction relative to a retention pin. The bristles may protrude from the inner diameter of the flat ring at an angle. A slot may be formed through the flat ring, and the slot may be angled. The flat ring may be circumferentially discontinuous. The flat ring may further comprise a retention opening configured to fix the flat ring in place relative to a retention pin. | 04-07-2016 |
20160102572 | TURBINE SHROUD WITH BIASED BLADE TRACK - A turbine shroud for a gas turbine engine is adapted to extend around a bladed turbine wheel and prevent gasses from passing over the blades without interacting with the blades. The turbine shroud includes a carrier, a blade track, and a plurality of biasing members. The biasing members locate the blade track relative to the carrier. | 04-14-2016 |
20160108735 | TANDEM ROTOR BLADES - A gas turbine engine includes a compressor section and a compressor case with a low pressure compressor (LPC) and a high pressure compressor (HPC). The HPC is aft of the LPC. The compressor case defines a centerline axis. The compressor section also includes a rotor disk defined between the compressor case and the centerline axis. A plurality of stages defined radially inward relative to the compressor case. The plurality of stages includes at least one tandem blade stage. The tandem blade stage includes a plurality of blade pairs. Each blade pair is circumferentially spaced apart from the other blade pairs, and is operatively connected to the rotor disk. Each blade pair includes a forward blade and an aft blade. The aft blade is configured to further condition air flow with respect to the forward blade without an intervening stator vane stage shrouded cavity therebetween. | 04-21-2016 |
20160115992 | FLEXURE PIVOT TILTING PAD JOURNAL BEARING ASSEMBLY - A flexure pivot tilting pad ( | 04-28-2016 |
20160123171 | TURBINE SHROUD WITH LOCATING INSERTS - A turbine shroud for a gas turbine engine includes an annular metallic carrier, a blade track, and a cross-key connection formed between the annular metallic carrier and the ceramic blade track. The cross-key connection is formed between the annular metallic carrier and inserts included in the blade track. | 05-05-2016 |
20160138610 | FAN SHROUD ASSEMBLY - Provided is a fan shroud assembly and, more specifically, a fan shroud assembly including a swirling airflow-preventing saw-teeth which is arranged along a predetermined inner circumferential surface of a ventilating part while maintaining a predetermined gap from an end portion of a blade of a fan or an end portion of a fan band of the fan and are formed in a saw-toothed shape, in which both a first area in which the swirling airflow-preventing saw-teeth are formed and a second area from which the swirling airflow-preventing saw-teeth are removed are formed, thereby generating a swirling airflow of ventilated air due to a reduction in pressure fluctuation and thus effectively reducing noise. | 05-19-2016 |
20160146053 | BLADE OUTER AIR SEAL SUPPORT STRUCTURE - A support structure for a gas turbine engine includes an axially extending portion that forms a loop. A radially extending portion extends radially inward from the axially extending portion. A plurality of retention members are attached to at least one of the axially extending portion and the radially extending portion for retaining a blade outer air seal. | 05-26-2016 |
20160158964 | CERAMIC-ENCAPSULATED THERMOPOLYMER PATTERN OR SUPPORT WITH METALLIC PLATING - A method for fabricating a ceramic component is disclosed. The method may comprise: 1) forming a polymer template having a shape that is an inverse of a shape of the ceramic component, 2) placing the polymer template in a mold; 3) injecting the polymer template with a ceramic slurry, 4) firing the ceramic slurry at a temperature to produce a green body, and 5) sintering the green body at an elevated temperature to provide the ceramic component. | 06-09-2016 |
20160160878 | Blade Of A Ventilator Wheel, Ventilator Wheel And Axial Ventilator - The invention relates in particular to a ventilator wheel of an axial ventilator, which includes multiple blades, each having radially outward extending blade forward edges and radial outer edges on the outlet side, wherein a transition from the radial outer edges to the blade forward edges is formed, in each case with a projection extending in the circumferential direction relative to the adjacent, radially outward extending blade forward edges, wherein a seamless transition is formed from the radial outer edge portion ( | 06-09-2016 |
20160169025 | HANGER SYSTEM FOR A TURBINE ENGINE COMPONENT | 06-16-2016 |
20160177970 | BLOWER | 06-23-2016 |
20160194974 | BOAS WITH RADIAL LOAD FEATURE | 07-07-2016 |
20160201467 | BLADE OUTER AIR SEAL WITH COOLING HOLES | 07-14-2016 |
20160201497 | GAS TURBINE AND MOUNTING METHOD | 07-14-2016 |
20160201498 | SEAL COATING | 07-14-2016 |
20160376906 | TURBINE SHROUD SEGMENT WITH BUFFER AIR SEAL SYSTEM - 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 |
20170234147 | CENTRIFUGAL COMPRESSOR ASSEMBLY FOR USE IN A TURBINE ENGINE AND METHOD OF ASSEMBLY | 08-17-2017 |
20180023408 | TURBINE SHROUD WITH FORWARD CASE AND FULL HOOP BLADE TRACK | 01-25-2018 |
20180023415 | AIR COOLED COMPONENT FOR A GAS TURBINE ENGINE | 01-25-2018 |