| Entries |
| Document | Title | Date |
|---|
| 20080199312 | GUIDE VANE ARRANGEMENT OF A TURBOMACHINE - A guide vane arrangement of a turbomachine includes a casing, at least one guide vane carrier connected to the casing and having a first carrying portion and a second carrying portion spaced apart axially from the first carrying portion, a plurality of guide vanes connected to the guide vane carrier and arranged next to each other in a circumferential direction, and at least one securing element connected to the guide vane carrier and configured to provide an axial fixing of at least one of the guide vanes. Each guide vane has a platform including a first locking portion and a second locking portion spaced apart axially from the first locking portion, wherein each of the first and second locking portions and the respective first and second carrying portion are adapted to provide an axially pluggable and a radially positive fastening between the guide vane carrier and the respective guide vane. | 08-21-2008 |
| 20080213091 | Steam Turbine - A steam turbine ( | 09-04-2008 |
| 20080260529 | Turbine Nozzle Support Device and Steam Turbine - A steam turbine includes a turbine casing, a turbine rotor disposed in the turbine casing, a plurality of turbine stages, a cylinder substantially coaxial with the turbine casing, and a fixing partition plate having an outer edge fixed to the turbine casing and an inner edge fixed to an outer circumferential portion of the cylinder. In a turbine nozzle support holder of such the steam turbine, the turbine stages each includes turbine movable blades disposed circumferentially around the turbine rotor and turbine nozzles paired with the turbine movable blades and disposed upstream of the turbine movable blades. The turbine nozzles of the turbine stages are arranged inside the cylinder in an axial direction and are engaged with and fixed to the cylinder. The fixing partition plate is disposed downstream of the center of the cylinder in the axial direction to separate an upstream atmosphere and a downstream atmosphere. | 10-23-2008 |
| 20090004000 | DAMPING DEVICE FOR TURBOMACHINE STATOR - The present invention relates to a turbomachine stator forming a stator vane ring or upstream guide vane element comprising a plurality of vanes placed radially between a first inner ring and a second outer ring, the two rings being concentric, the second ring having a cylindrical outer surface portion. The stator is characterized in that, on said outer surface portion, at least one vibration-damping laminate is attached, the laminate comprising at least one layer of viscoelastic material in contact with said surface portion and one counterlayer of rigid material. | 01-01-2009 |
| 20090041580 | Stator joining strip and method of linking adjacent stators - A compressor having a plurality of vane units each having at least one airfoil projecting from the base. Each base has a groove, so that when the vane units are disposed circumferentially adjacent, the grooves of the respective vane units are circumferentially aligned. A metal strip is disposed in the groove of a plurality of adjacent vane units to link the vane units forming a more rigid ring of vanes that are less susceptible to vane motion, e.g., caused by pressure fluctuations within the compressor of a gas turbine. | 02-12-2009 |
| 20090047126 | Integrated compressor vane casing - A low leakage, integral fixed vane system for a gas turbine engine compression system which can accommodate the latest 3-D aerodynamic airfoil geometries and provide endwall ovalization control. A unitized construction wherein the vanes are integral with the case wall in the compression system. | 02-19-2009 |
| 20090053056 | Turbine Vane Securing Mechanism - A turbine vane attachment system configured to eliminate movement of a turbine vane relative to a turbine vane carrier. The turbine vane attachment system may include a base attached to a turbine airfoil. The base may be configured to contact a wedge support along a plane that is generally nonparallel and nonorthogonal with a longitudinal axis of the airfoil. A bolt may connect the base with the wedge support. The bolt may change a distance between a channel in the base and an outer bearing surface. The turbine vane may be positioned in a vane carrier such that tongues extending from the vane carrier are positioned in the channels. As the bolt is advanced, the wedge support is moved laterally along the support surface of the base and the channels engage the tongues, thereby preventing movement of the turbine vane. | 02-26-2009 |
| 20090081037 | MEMBER FOR LOCKING RING SECTORS ONTO A TURBOMACHINE CASING, COMPRISING MEANS ALLOWING IT TO BE GRASPED - The present invention relates to a locking member ( | 03-26-2009 |
| 20090110552 | COMPRESSOR STATOR VANE REPAIR WITH PIN - A vane unit system having a plurality of vane units having at least one airfoil projecting from a base is modified by placing a hole in the base and receiving a pin which extends between adjacent bases of vane units. A series of modified bases form a ring of rigid vanes that are less susceptible to vane motion caused by pressure fluctuations within the compressor of a gas turbine. A blade assembly tool having a shape to fit within the slot in a casing that receives the vane units allows for the installation of vane units with pins locking to shims or adjacent vanes without the necessity of having to remove the rotor from the casing. Preferably, the pins are coiled straps resiliently engaging at least one but preferably both holes in two adjacent vanes. | 04-30-2009 |
| 20090148283 | NOZZLE RING ADHESIVE BONDED BLADING FOR AIRCRAFT ENGINE COMPRESSOR - A compressor nozzle ring for an aircraft includes an inner shroud, an outer shroud and a multiplicity of blades extending from the inner shroud to the outer shroud. Each blade passes through the inner shroud and is attached to it with sealing cement containing an organic polymer adhesive. The adhesive is polyimide based. | 06-11-2009 |
| 20090155069 | AXIAL LOADING ELEMENT FOR TURBINE VANE - A vane assembly for a gas turbine engine comprising an axial loading element disposed between a mounting element of the vane ring and a cooperating portion of the supporting structure, such as to generate a load force therebetween in an axial direction. The axial load force limits unwanted relative movement between the vane ring and the supporting structure during operation of the gas turbine engine. | 06-18-2009 |
| 20090185899 | HP SEGMENT VANES - A stator vane segment, for constructing a circumferential array of like segments in a gas turbine engine, each segment in the array being separated by an axially extending joint from an adjacent segment and being releasably mounted to an outer engine casing. Each stator vane segment has: a number of vane airfoils spanning radially between an inner platform and an outer platform, and the outer platform includes: a casing mounting fastener on an outer surface and mating lateral joint edges extending between forward and aft edges. | 07-23-2009 |
| 20090208332 | LPC exit guide vane and assembly - A vane for a gas turbine engine includes an airfoil portion, a platform, and a first flange. The airfoil portion has first and second ends spaced apart in a first direction, and the first end of the airfoil portion defines an unshrouded tip. The platform is integrally formed at the second end of the airfoil, and is configured to define a flowpath boundary segment. The first flange extends from the platform away from the airfoil portion. The first flange defines a first circumferential extension and an adjacent second circumferential extension, each defining forward and aft faces. The first and second circumferential extensions are offset in a second direction such that the forward face of the first circumferential extension is substantially aligned with the aft face of the second circumferential extension in the second direction. | 08-20-2009 |
| 20090246014 | METHOD AND SYSTEM FOR SUPPORTING STATOR COMPONENTS - A method and system of supporting removable static components in a turbine engine stator assembly is described. The method comprises the steps of engaging a stator hanger located at a first location on a first static component with a post located on a first static structure whereby the post supports at least a part of the weight of the first static component, engaging a stator stopper located at a second location on the first static component that is located circumferentially apart from the first location with the stator hanger that is located on a second static component, and engaging a hook located at a third location on the first static component with a second static structure whereby the second static structure supports at least a part of the weight of the first static component. | 10-01-2009 |
| 20090304503 | STATOR BLADE SEGMENT OF A THERMAL TURBOMACHINE, ASSOCIATED PRODUCTION METHOD AND ALSO THERMAL TURBOMACHINE - The invention relates to a guide blade segment of a thermal turbomachine, in particular a gas turbine, comprising a number of profiled blades which are arranged on a platform. A plurality of securing elements for securing the guide blade segment to an associated guide blade support are arranged on the side of the platform which is oriented away from the blade. The aim of the invention is to provide a guide blade segment which can be produced in a simple and economical manner avoiding casting problem areas enabling the guide blade segment to be attached in a particularly reliable and secure manner to the associated guide blade support. According to the invention, at least one section of at least one of the securing elements is a separately produced component which is rigidly connected to the platform or to an additional section of the securing element. | 12-10-2009 |
| 20100008774 | VARIABLE GEOMETRY TURBOCHARGER LOWER VANE RING RETAINING SYSTEM - A vane ring assembly which includes a lower vane ring ( | 01-14-2010 |
| 20100028146 | METHOD AND APPARATUS FOR ASSEMBLING GAS TURBINE ENGINES - A method of operating a gas turbine engine includes forming at least one stator ring passage within at least a portion of a radially inner surface of a casing. The method also includes providing at least one stator ring segment that is sized to be inserted into the at least one stator ring passage. The method further includes forming at least one radial passage within at least a portion of the at least one stator ring segment such that at least a portion of the at least one radial passage is adjacent to at least one substantially axial stator blade passage. | 02-04-2010 |
| 20100028147 | DIFFUSER/GUIDE VANE ASSEMBLY FOR A TURBOMACHINE - Diffuser/guide vane assembly ( | 02-04-2010 |
| 20100040464 | SELF-PRIMING VANE PUMP - A self-priming vane pump includes a cylindrical rotor disposed in a cavity in a housing including inlet and outlet ports. The rotor defines a plurality of axially extending slots which each receive one of a like plurality of vanes. A garter spring or similar resilient annulus is disposed within the rotor and provides a radially outwardly directed force on the vanes which maintains their contact with the cavity walls during pump start-up and rapidly self-primes the pump. The spring or annulus rests against a shoulder within the hollow rotor and is retained therein by a pressed in collar. | 02-18-2010 |
| 20100068049 | FEATURES TO PROPERLY ORIENT INLET GUIDE VANES - Several physical features on an inlet guide vane (IGV) ensure proper orientation of the IGV within a compressor during assembly. A gear with several teeth removed results in a flat surface on the gear which inhibits the gear from rotating on the rack of the compressor inlet casing. An orientation pin is located in the internal bore of the gear. The cylindrical IGV spindle has a portion formed as a flat surface and the orientation pin engages this flat surface. These features are applicable to both a one-piece IGV where the jackshaft is integrated with the IGV stem and a two-piece IGV in which the jackshaft is separate from the IGV stem. A feature applicable to a two-piece IGV is a shaped boss on the IGV stem that allows the jackshaft to be located on the IGV stem in only one orientation. | 03-18-2010 |
| 20100068050 | GAS TURBINE VANE ATTACHMENT - Base hooks of a vane includes an approximate two times thicker radial geometry, with dimensioning and tolerancing that results in a line-line to loose fit on the forward OD hook surface and the aft ID hook surface. Tolerances thus stack up on the opposite, non-critical surfaces of the hooks (the forward ID hook surface and the aft OD hook surface). The base of the vane is curved to match that of the casing. An interface between the vane base and the casing groove includes a metal alloy liner. Also, a wear coating is provided on the vane attachment hooks. The liner protects the casing groove from wear damage, while the hook coating and the liner provide a wear coupling between the vane base and the casing that provides a barrier between the vane bases and the casing to decrease the wear rate. | 03-18-2010 |
| 20100074745 | DUAL STAGE TURBINE SHROUD - A turbine shroud includes a shroud hanger having an arcuate panel from which three inner hooks extend inwardly, and from which two outer hooks extend outwardly therefrom. The two outer hooks effect a statically determinate configuration of the shroud. | 03-25-2010 |
| 20100086401 | Stator vane assembly - A stator vane assembly comprising inner and outer support rings connected by an annular array of stator vanes at locations around the supporting rings, at least one of said stator vanes in said array being a separate, pre-formed stator vane which is slidably connected to one or both of the supporting rings for radial movement relative to the respective support ring thereby to accommodate relative radial expansion of the support rings. | 04-08-2010 |
| 20100098537 | STATOR BLADE RING AND AXIAL FLOW COMPRESSOR USING THE SAME - A stator blade ring is provided with which the possibilities of thermal deformation and a decrease in strength can be reduced, the shape flexibility can be ensured, and the compression performance can be improved. It includes stator blade segments ( | 04-22-2010 |
| 20100129210 | VANE WITH REDUCED STRESS - An airfoil assembly is described comprising an airfoil, a band coupled to the airfoil for providing at least a portion of support for the airfoil in the airfoil assembly and a slot capable reducing stress in the airfoil wherein the slot is located in the band near a portion of the airfoil. A compression system is described comprising a stator assembly comprising a plurality of arcuate vane sectors arranged circumferentially around a longitudinal axis, each vane sector comprising an airfoil, an arcuate inner band and an arcuate outer band coupled to the airfoil, and a slot capable of reducing stress in the airfoil, the slot being located in the vane sector near a portion of the airfoil. | 05-27-2010 |
| 20100129211 | COMPRESSOR VANE DIAPHRAGM - A compressor diaphragm for a gas turbine engine having improved wear capability, manufacturability, and assembly techniques is disclosed. The diaphragm includes a shiplap-type joint at an outer vane platform for connecting to adjacent vane assemblies and a clamshell-like assembly of a seal box secures and seals regions around the inner vane platform of the compressor diaphragm so as to reduce wear between the seal box and the vane assemblies. The inner platform of the diaphragm segments are fastened to each other through circumferentially-oriented fasteners at the inner diameter platform. | 05-27-2010 |
| 20100135782 | ASSEMBLING METHOD OF STATOR BLADE RING SEGMENT, STATOR BLADE RING SEGMENT, COUPLING MEMBER, WELDING METHOD - The present invention has an object to provide an assembling method of a stator blade ring segment that can prevent the risk of thermal deformation and a reduction in strength, ensure flexibility of shape, and increase compression performance of a compressor. The present invention has another object to provide welding that prevents an object to be welded from rising from a groove or a recess during welding and allows satisfactory welding. A groove | 06-03-2010 |
| 20100150711 | APPARATUS AND METHOD FOR PREVENTING CRACKING OF TURBINE ENGINE CASES - A method for preventing cracking of a turbine engine case includes the steps of disposing at least two rails upon an exterior surface of a turbine engine case; and securing a first rail to a first means for attaching at least one fan exit guide vane to the turbine engine case and securing a second rail to a second means for attaching the at least one fan exit guide vane to the turbine engine case. | 06-17-2010 |
| 20100150712 | HEAT SHIELD SEGMENT FOR A STATOR OF A GAS TURBINE - A gas turbine includes a turbine housing; a rotatable turbine rotor with turbine blades; and at least one heat shield segment for a stator. The heat shield segment is disposed radially between the rotor and the housing and attached to the housing and has a profile with a curved section in at least one region in an axial direction of the gas turbine and a radial outer surface. The heat shield segment includes a rib, a first boss, and a second boss disposed on the radial outer surface. | 06-17-2010 |
| 20100158685 | Guide Vane Architecture - Guide vane stage of a turbine engine comprising a series of fixed blades connecting an inner collar to an outer collar, characterised in that said fixed blades comprise attachment platforms with flat surfaces that co-operate with a plurality of juxtaposed flat facets, said flat facets being located on the inner face of the outer collar in order to ensure attachment with a contact of a flat/flat type between the fixed blades and the outer collar. | 06-24-2010 |
| 20100172755 | METHOD AND APPARATUS FOR INSURING PROPER INSTALLATION OF STATORS IN A COMPRESSOR CASE - Disclosed herein is a compressor case assembly that includes a compressor case section having an assembly track and a set of stator portions that are insertable in the assembly track, the compressor case section and the set of stator portions are configured such that the set of stator portions only assembles to the compressor case section in a single configuration. | 07-08-2010 |
| 20100183435 | Gas Turbine Vane Platform Element - A gas turbine CMC shroud plate ( | 07-22-2010 |
| 20100196155 | Annular vane assembly for a gas turbine engine - An annular vane assembly for a gas turbine engine is provided. The assembly includes a vane segment, the vane segment includes an arcuate rail and a vane that extends radially inwardly from the arcuate rail. The assembly also includes a hollow cylindrical casing, the inside curved surface of which an annular groove is formed that receives the arcuate rail. The arcuate rail is secured in the annular groove using a resilient strip interposed between the rail and the groove. The resilient strip includes a planar main body and sprung wings that extend to either side of the main body. The wings are angled with respect to the plane of the main body. The resilient strip is moveable circumferentially between a first position in which the strip exerts a force radially on the arcuate rail and a second position in which the wings occupy recesses in the assembly. | 08-05-2010 |
| 20100209240 | VANE FIXING APPARATUS AND METHOD - A vane fixing apparatus for removably fixing a vane plate ( | 08-19-2010 |
| 20100215490 | Systems, Methods, and Apparatus for Linking Machine Stators - Systems, methods, and apparatus for linking machine stators are provided. A bracket may be utilized to link adjacent stators within a machine, for example, a turbine. The bracket may include a body portion, a first plurality of extensions, and a second plurality of extensions. The body portion may include a first edge operable to align with a base of a first stator and a second edge opposite the first edge and operable to align with a base of a second stator. The first plurality of extensions may extend from the first edge and may be operable to align with at least one corresponding groove on the base of the first stator. The second plurality of extensions may extend from the second edge and may be operable to align with at least one corresponding groove on the base of the second stator. When utilized to link the first stator and the second stator, the bracket may facilitate a reduction of vibrations in the first stator and the second stator. | 08-26-2010 |
| 20100266400 | COLUMNAR AIR MOVING DEVICES, SYSTEMS AND METHOD - A columnar air moving device can comprise separately formed modular stator vanes in a stator vane assembly. The stator vanes can be arranged in a radial pattern, and can direct air in an axial direction. The modular stator vanes, as well as other components of the stator vane assembly, can be replaced, adjusted, and/or removed from the columnar air moving device. | 10-21-2010 |
| 20100284805 | APPARATUS AND METHOD FOR LOCKING A COMPOSITE COMPONENT - An apparatus and method for locking a composite component such as blade or vane of a turbine engine is disclosed herein. The disclosed lock can also be used generally to fix the position of composite structures. The lock includes a first locking member including a first structure operable to at least partially fix the first locking member along an axis of a slot for receiving a blade or a vane. The lock also includes a second locking member including a second structure operable to engage the blade or vane. The first and second locking members are slidably engaged with one another along mating ramped surfaces. | 11-11-2010 |
| 20100322763 | METHOD FOR MANUFACTURING VANES INTEGRATED INTO A RING AND RECTIFIER BY THE METHOD - The present invention relates to a method for manufacturing a turbomachine rectifier comprising an outer ring ( | 12-23-2010 |
| 20110008163 | COMPOSITE ARTICLE AND SUPPORT FRAME ASSEMBLY - A support frame includes a rail engaging a hook of a composite article having plys. The rail included a rail contact surface generally conformal to and contacting a hook contact surface of the hook. The rail and hook contact surfaces being substantially normal to the plys beneath the hook contact surface. One embodiment of the article is a composite nozzle segment including one or more airfoils extending radially between arcuate radially outer and inner band segments having plys curved about a centerline axis and the rail engages a hook of the radially inner band segment. The hook and the rail may be straight or arcuate. The frame includes a central body extending axially aftwardly from the rail to an aft frame flange. A frame pin may be mounted on the frame, engage the inner band segment or one of the airfoils, and may extend into a cavity in the airfoil. | 01-13-2011 |
| 20110014041 | Rotary Drum of an Axial Compressor Having a Composite Web - A rotary drum of an axial compressor having a web made of composite material has an upstream flange for fastening the fan, a segment having a sealing flange upstream, a segment with a groove adapted to receive the bases of the vane of a first row of vanes, a segment with a groove adapted to receive the bases of the vane of a second row of vanes, and a segment with a groove adapted to receive the bases of the vane of a third row of vanes. These segments are made of metallic material mostly for reasons of mechanical resistance to the centrifugal forces. The segments are connected to each other with web segments made of composite material. The ends of the metallic segments have a dovetail-shaped section in a longitudinal plane that is able to ensure a positive connection with the composite material. | 01-20-2011 |
| 20110033290 | STRUT FOR AN INTERMEDIATE TURBINE HOUSING, INTERMEDIATE TURBINE HOUSING, AND METHOD FOR PRODUCING AN INTERMEDIATE TURBINE HOUSING - The present invention relates to a strut for a turbine center frame of a jet engine, in particular a gas turbine, with a first end for disposition on an internal structure of the turbine center frame and a second end opposite the first end for attaching the strut on a housing or an internal boundary wall of the turbine center frame, and on the second end at least one flange-like element with at least one first aperture is removably arranged with at least one first aperture for accommodating or passing through an attachment means. The invention further relates to a turbine center frame for a jet engine, in particular a gas turbine as well as a method for producing a turbine center frame of a jet engine, in particular a gas turbine. | 02-10-2011 |
| 20110081240 | FABRICATED GAS TURBINE VANE RING - A static vane ring for gas turbine engines includes a plurality of radial struts extending between and interconnecting outer and inner duct walls which define an annular duct therebetween. A load transfer apparatus is attached to at least one of the outer and inner duct walls to transfer load from vane to ring, and between vanes. | 04-07-2011 |
| 20110103944 | STEAMPATH FLOW SEPARATION REDUCTION SYSTEM - A system for reducing flow separation in a turbo machine is provided, the system including a stationary vane coupled to a stationary vane support; at least one circumferential extraction band through the stationary vane or the stationary vane support; the circumferential extraction band having a first side proximate to an operative fluid flow through the turbo machine; at least one opening in the first side of the circumferential extraction band; and a channel having a first end in fluid connection with the circumferential extraction band and a second end extending through the stationary vane support, such that the operative fluid flow through the turbo machine is redirected through the extraction opening into the circumferential extraction band and through the channel towards a rotating blade. | 05-05-2011 |
| 20110158798 | SYSTEMS AND APPARATUS RELATING TO COMPRESSOR STATOR BLADES AND DIFFUSERS IN TURBINE ENGINES - A row of stator blades in a compressor of a combustion turbine engine, the combustion turbine engine including a diffuser located downstream of the compressor, and the row of stator blades disposed in close proximity to the diffuser; the row of stator blades comprising: a plurality of stator blades that include at least one of an inboard forward notch and an outboard forward notch. | 06-30-2011 |
| 20110189008 | RETAINING RING FOR A TURBINE NOZZLE WITH IMPROVED THERMAL ISOLATION - A retaining ring for a turbine nozzle of a gas turbine is disclosed. The retaining ring includes a main body and a pair of circumferential retaining lands projecting inward radially from the main body. The pair of circumferential retaining lands may be configured to be attached to a nozzle. Additionally, each retaining land of the pair of circumferential retaining lands may be segmented along its circumferential length. | 08-04-2011 |
| 20110189009 | MOUNTING APPARATUS FOR LOW-DUCTILITY TURBINE SHROUD - A turbine shroud apparatus is provided for a gas turbine engine having a central axis. The apparatus includes: (a) an annular support member; (b) a turbine shroud disposed in the support member, the shroud being a continuous ring comprising a low-ductility material and having opposed flowpath and back surfaces, and opposed forward and aft ends; and (c) a spring mounted between the support member and the shroud and arranged to resiliently urge the shroud to a concentric position within the structural member. | 08-04-2011 |
| 20110200430 | STEAM TURBINE NOZZLE SEGMENT HAVING ARCUATE INTERFACE - Steam turbine nozzle segments with conical interfaces are disclosed. In one embodiment a steam turbine static nozzle blade includes: an airfoil; an inner sidewall integral with a first side of the airfoil; and an outer sidewall integral with a second side of the airfoil; the inner sidewall and the outer sidewall each including: a pressure side having an arcuate concave surface extending substantially an entire length of the sidewall; and a suction side having an arcuate convex surface extending substantially the entire length of the sidewall. | 08-18-2011 |
| 20110211946 | WELDED NOZZLE ASSEMBLY FOR A STEAM TURBINE AND ASSEMBLY FIXTURES - A nozzle blade and nozzle ring assembly includes a nozzle blade having radially inner and outer sidewalls with an airfoil portion extending therebetween; the inner and outer sidewalls walls formed with axially-extending first surface features along forward and aft marginal edges of the inner and outer sidewalls, respectively; and radially inner and outer nozzle rings formed with corresponding axially-extending second surface features mated with the first surface features, wherein the radially inner and outer sidewalls are welded to the radially inner and outer nozzle rings only along the mated first and second surface features. | 09-01-2011 |
| 20110243725 | TURBINE SHROUD MOUNTING APPARATUS WITH ANTI-ROTATION FEATURE - A turbine shroud mounting apparatus includes: (a) a shroud hanger having an arcuate body and including an arcuate first hook which protrudes radially inward and extends axially forward from the body, so as to define a first slot in cooperation with the body; (b) an anti-rotation element disposed within the first slot, the anti-rotation element being integrally formed with the shroud hanger; and (c) an arcuate shroud segment including an arcuate first mounting flange which protrudes radially outward and extends axially aft, the first mounting flange having a receptacle formed therein, where the first mounting flange is received in the first slot and the anti-rotation member is received in the receptacle. | 10-06-2011 |
| 20110280721 | Gas turbine - A gas turbine including a plurality of hook elements disposed one inside the other and designed substantially in the form of hollow cones or hollow cylinders, and including a stator blade support, is intended to enable an especially high efficiency while maintaining the greatest possible operating safety and operating life. To this end, at least one of the hook elements or the stator blade support has a substantially elliptical cross-sectional contour. | 11-17-2011 |
| 20120107111 | BLADE ARRANGEMENT, ESPECIALLY STATOR BLADE ARRANGEMENT - A blade arrangement on a wall of a fluid flow path of a turbomachine includes a locating channel disposed in the wall and having undercut flanks. A plurality of glades each having a blade-side root section corresponding to the undercut flanks a plurality of intermediate filling pieces correspond to the undercut flanks and separate each of the blade-side root sections. The plurality of blade-side root sections and intermediate filling pieces are seated in a form-fitting manner and fixed in a force-locking manner in the locating channel. The plurality of intermediate filling pieces fill out the locating channel so as to form a gas flow-side surface essentially free of a disturbing contour between the blade-side root sections. Each of the plurality of intermediate filling pieces includes a threaded hole disposed essentially perpendicular to a base of the channel. A screw is disposed in the threaded hole. | 05-03-2012 |
| 20120163968 | MODULE FOR A STEAM TURBINE - Module for a steam turbine including a low-pressure module, includes an internal turbine casing able to accommodate at least one set of fixed vanes and a rotor equipped with at least one set of blades, and a slab, the internal turbine casing resting on the slab via at least two bearers secured to said internal turbine casing, the connection between said bearers and the slab is provided by a plurality of mechanical connectors. The connectors each prevent the internal turbine casing from lifting in relation to the slab, and allow the internal turbine casing to slide on the slab. | 06-28-2012 |
| 20120213634 | GAS TURBINE ENGINE COMPONENT - In a gas turbine engine at least one vanes is made of a composite material and an end part of the vane is fastened to the ring element by at least a first bracket member arranged in a corner region formed by the vane and a ring element. The first bracket member is fastened to the vane by a first fastening device arranged in association with a first hole extending through the vane. The first bracket member is fastened to the ring element by a second fastening device arranged in association with a second hole extending through the ring element. An opening is arranged in the ring element. A second bracket member at least partly has an angular cross section. The second, angled bracket member is arranged through the opening such as to be positioned on an opposite side of both the vane and the ring element in relation to the first bracket member. The second, angled bracket member is fastened to the first bracket member by the first and second fastening devices. | 08-23-2012 |
| 20120219412 | STATIONARY VANE UNIT OF ROTARY MACHINE, METHOD OF PRODUCING THE SAME, AND METHOD OF CONNECTING THE SAME - The stationary vane unit of a rotary machine includes: a first band member that extends in the circumferential direction and comes into contact with the outer shrouds of the plurality of stationary vane members from one side thereof in the main axial direction in which a central axis extends; a second band member that extends in the circumferential direction and comes into contact with the outer shrouds of the plurality of stationary vane members from the other side thereof in the main axial direction; and a fastening member that fastens the first band member and the second band member to each other so that the outer shrouds of the plurality of stationary vane members are connected to each other. | 08-30-2012 |
| 20120251313 | APPARATUS AND METHOD FOR GAS TURBINE ENGINE VANE RETENTION - A vane assembly of a gas turbine engine has a plurality of vanes extending radially and inwardly from an annular casing. An outer end of each vane radially and outwardly projects from the casing and is received in one of apertures defined in an elastomeric ring which is placed around the casing. A strap of a non-metallic material is placed in a pre-tensioned condition around the elastomeric ring to compress the elastomeric ring and to radially retain the outer end of each vane. | 10-04-2012 |
| 20120251314 | CMC TURBINE NOZZLE ADAPTED TO SUPPORT A METALLIC TURBINE INTERNAL CASING BY A RADIAL CONTACT - Composite material turbine nozzle blade including an airfoil ( | 10-04-2012 |
| 20120308376 | VARIABLE GEOMETRY TURBOCHARGER LOWER VANE RING RETAINING SYSTEM - A vane ring assembly which includes a lower vane ring ( | 12-06-2012 |
| 20130177411 | SYSTEM AND METHOD FOR SEALING A GAS PATH IN A TURBINE - A system for sealing a gas path in a turbine includes a stator ring segment, a shroud segment adjacent to the stator ring segment, and a first load-bearing surface between the stator ring segment and the shroud segment. A first non-metallic gasket is in contact with the first load-bearing surface between the stator ring segment and the shroud segment. A method for sealing a gas path in a turbine includes placing a non-metallic gasket between any two of a stator ring segment, a shroud segment, and a casing. | 07-11-2013 |
| 20130177412 | Gas Turbine Stator Assembly - According to one aspect, a turbine assembly includes a second component circumferentially adjacent to a first component, wherein the first and second components each have a surface proximate a hot gas path and a first side surface of the first component to be joined to a second side surface of the second component. The assembly also includes a first slot formed longitudinally in the first component which extends from a first slot inner wall to the first side surface and a second slot formed longitudinally in the second component which extends from a second slot inner wall to the second side surface. The assembly also includes a first groove formed in a hot side surface of the first slot, the first groove extending from the first slot inner wall to the first side surface, wherein the first groove comprises a tapered cross-sectional geometry. | 07-11-2013 |
| 20130195642 | METHOD FOR REPAIRING A SHROUD TILE OF A GAS TURBINE - A method for repairing a shroud tile of a gas turbine is disclosed. The method may generally include removing a portion of the shroud tile along at least one of a first side and a second side of the shroud tile and securing at least one side rail to the shroud tile in place of the removed portion of the shroud tile. | 08-01-2013 |
| 20130209248 | Anti-Rotation Stator Segments - A stator assembly for a turbofan gas turbine engine is disclosed. The stator assembly is coupled to a shroud of the engine. The stator assembly includes an endless case fixedly coupled to the engine shroud. The case includes a forward portion, an aft portion and a central portion disposed therebetween. The case extends about an axis of the engine. The forward and aft portions of the case include rails that extend towards each other and form forward and aft pockets with the central portion respectfully. The stator assembly also includes a locking stator segment. The locking stator segment includes a shroud that includes a forward hook and a pair of aft hooks with a platform disposed therebetween. The forward and aft hooks are retained in the forward and aft pockets of the case respectfully. | 08-15-2013 |
| 20130209249 | ANNULAR ANTI-WEAR SHIM FOR A TURBOMACHINE - A turbomachine compressor or turbine including annular anti-wear shims mounted against hooks of a stator, each shim being substantially of channel-section defining an annular groove for engaging on a hook, the shim mounted against the downstream hook bearing axially via its middle annular wall on the stator, or on the casing, and one of its side walls includes bearing means at its end remote from the middle annular wall for bearing against the casing or the stator, respectively, which bearing means are elastically deformable in an axial direction so as to urge the stator upstream. | 08-15-2013 |
| 20140044537 | GAS TURBINE - A gas turbine stage, in particular a low-pressure compressor stage, for a gas turbine, in particular an aircraft engine gas turbine having a guide vane assembly having at least one guide vane ( | 02-13-2014 |
| 20140064955 | GUIDE VANE ASSEMBLY FOR A GAS TURBINE ENGINE - A guide vane assembly for a gas turbine engine includes: a strut having: a root, a tip, a leading edge, a trailing edge wall, and opposed sidewalls extending between the leading edge and the trailing edge wall; and a pair of spaced-apart prongs extending axially aft from the trailing edge wall, each prong having an outer wall that is flush with a respective one of the sidewalls; and a flap positioned axially aft of the strut, the flap having a root, a tip, a leading edge, a trailing edge, and opposed sides extending between the leading and trailing edge, wherein a portion of the leading edge is disposed between the prongs, and wherein a disk-like flap button is disposed at the tip of the flap adjacent its leading edge, the flap button including a pair of spaced-apart notches formed therein. | 03-06-2014 |
| 20140064956 | GUIDE VANE ASSEMBLY - A guide vane assembly for a stator vane stage comprises at least two aerofoil members joined together using a vane assembly attachment web. The vane assembly attachment web may be provided at the inner and/or outer radius of the aerofoil members. The vane assembly attachment web allows the guide vane assembly to be attached to an inner and/or outer attachment ring, thereby forming a stator vane stage. Such an arrangement may allow composite fibre reinforced guide vane assemblies to be readily assembled together to form stator vane stages. Stator vane stages that comprise such composite fibre reinforced guide vane assemblies may be lighter than conventional metallic stator vane stages. | 03-06-2014 |
| 20140178193 | Blade-Retaining Plate with Internal Cut-Outs for a Turbomachine Stator - The invention relates to an axial turbomachine stator ( | 06-26-2014 |
| 20140186173 | DIFFUSER USING DETACHABLE VANES - A system, in certain embodiments, includes a plurality of detachable, three-dimensional diffuser vanes attached to a diffuser plate of a centrifugal compressor. In certain embodiments, the detachable, three-dimensional diffuser vanes may be attached to the diffuser plate using threaded fasteners. In addition, dowel pins may be used to align the detachable, three-dimensional diffuser vanes with respect to the diffuser plate. However, in other embodiments, the detachable, three-dimensional diffuser vanes may include a tab configured to fit securely within a groove in the diffuser plate. In addition, the tabs of the detachable, three-dimensional diffuser vanes may include indentions that mate with extensions extending from the diffuser plate, wherein the tabs may slide into slots between the extensions and the grooves of the diffuser plate. | 07-03-2014 |
| 20140193251 | STATOR ANTI-ROTATION DEVICE - A stator vane assembly for a gas turbine engine is disclosed and includes a plurality of vanes received within channels defined within a case. An anti-rotation plate extends from a flange of the case between adjacent ones of the plurality of vanes for preventing rotation of the plurality of vanes relative to the case. | 07-10-2014 |
| 20140234098 | TURBINE CASE RETENTION HOOK WITH INSERT - A method of repairing a turbine engine case includes the steps of removing worn material from a retention hook in a casing, and inserting an insert into a recess within the hook. | 08-21-2014 |
| 20140271171 | COMPRESSOR AIRFOIL - Aspects of the present invention relate to systems and methods of a vane design utilizing welding techniques. The present invention concerns a method for preventing cracking within a vane assembly utilizing full penetration welding. Additional embodiments concern a vane design that, when assembled with another vane, comprises an axial slot that prevents cracking within a vane assembly. | 09-18-2014 |
| 20140301840 | GUIDE VANE ARRANGEMENT - A guide vane arrangement for a turbomachine, particularly a gas turbine, is disclosed. The guide vane arrangement includes an external shroud band, on which at least two guide vanes protrude radially inward. A pair of axial ribs spaced apart from each other in the peripheral direction and disposed between two adjoining guide vanes in the peripheral direction protrude radially outward from a circumferential surface of the external shroud band and/or axially from a radial flange of the external shroud band. | 10-09-2014 |
| 20140356158 | GAS TURBINE ENGINE VANE ASSEMBLY AND METHOD OF MOUNTING SAME - The gas turbine engine vane assembly has a vane having an elongated airfoil body extending to a tip and a grommet disposed around the tip. An insert having a closed loop shape with an inner surface matingly shaped to receive the outer surface of the grommet, and an outer surface matingly shaped to be snugly received in the slot. A method of mounting such a vane assembly is also disclosed. | 12-04-2014 |
| 20150030442 | SEAL MEMBER, TURBINE, AND GAS TURBINE - In a seal member, a turbine, and a gas turbine, a plurality of vanes includes a vane main body extending in a radial direction of an axis, an outer shroud, an inner shroud and forming a main flow path of a combustion gas between the outer shrouds and the inner shroud, and a retainer protruding from an inner surface in the radial direction of the inner shroud to the inside in the radial direction. The retainers in the vanes, which are adjacent to each other in the circumferential direction, are adjacent to each other in the circumferential direction via a third gap, and relative to one end of the seal member, the other end is positioned downstream in a direction along the axis in the combustion gas to close the third gap. | 01-29-2015 |
| 20150064000 | COUPLING PART STRUCTURE FOR VANE AND JET ENGINE INCLUDING THE SAME - A coupling support member including a pair of divided pieces is placed in a coupling part between a vane proximal end portion of a guide vane and an attachment flange, and the pair of divided pieces are joined to the vane proximal end portion from both the sides in the vane thickness direction. A linear protrusion is formed on one of joint surfaces of the vane proximal end portion to the pair of divided pieces. A groove engaged with the linear protrusion formed in the vane proximal end portion is formed on one of respective joint surfaces of the pair of divided pieces of the coupling support member. The vane proximal end portion is held between the pair of divided pieces of the coupling support member, by the fastening force that is applied to the pair of divided pieces of the coupling support member from both the sides in the vane thickness direction. It is possible to obtain a high structural strength while contributing to a reduction in weight of a jet engine. | 03-05-2015 |
| 20150098812 | INTEGRATED STRUT AND TURBINE VANE NOZZLE ARRANGEMENT - An integrated strut and turbine vane nozzle (ISV) arrangement according to an embodiment, includes a single-piece interturbine duct (ITD) and a plurality of vane nozzle segments removably attached to the ITD. Vane airfoils of the vane nozzle segments in combination with trailing edge portions of the struts, form a vane nozzle integrated with the ITD. | 04-09-2015 |
| 20150098813 | LOCK LINK MECHANISM FOR TURBINE VANES - A lock link for locking variable stage stator vanes in a compressor includes a substantially planar body portion having a slot formed on one edge and a narrow neck portion extending away from an opposite edge, the narrow neck portion adapted to seat in a corresponding slot in an adjacent lock link attached to an adjacent vane; and a profiled opening in the substantially planar body portion adapted to receive a key provided on a vane stem to prevent relative rotation between the vane and the lock link. | 04-09-2015 |
| 20150104303 | Turbocharger - A turbocharger for an internal combustion engine having a housing, an impeller arranged in the housing interior having an impeller shaft and being mounted in a bearing block, and an intermediate element between the impeller and the bearing block. The housing includes at least one flow channel for feeding or discharging a fluid to or from the impeller, and the intermediate element includes a wall section that delimits a least a section of at least one of the flow channels. | 04-16-2015 |
| 20150118040 | OUTER VANE SUPPORT RING INCLUDING A STRONG BACK PLATE IN A COMPRESSOR SECTION OF A GAS TURBINE ENGINE - A support ring for a row of vanes in an engine section of a gas turbine engine includes an annular main body portion for providing structural support for a row of vanes in the engine section, an aft hook, a forward wall, and a strong back plate. The aft hook extends from an aft side of the main body portion and is coupled to an outer engine casing for structurally supporting the support ring in the engine section. The forward wall extends generally radially outwardly from a forward side of the main body portion. The strong back plate spans between the forward wall and the aft hook and effects a reduction in dynamic displacement between the forward wall and the aft hook during operation of the engine. | 04-30-2015 |
| 20150118041 | METHODS AND SYSTEMS FOR SECURING TURBINE NOZZLES - A nozzle assembly includes at least one stationary nozzle and an outer ring having a predefined shape. The outer ring includes at least one groove defined therein configured to receive at least a portion of the at least one stationary nozzle. The nozzle assembly also includes an attachment member coupled between the stationary nozzle and the outer ring. The attachment member has a first configuration at a first nozzle assembly operating temperature a second configuration at a second nozzle assembly operating temperature. | 04-30-2015 |
| 20150125290 | CORE RING WITH CUT OR LANCED FEATURES - A core ring for a torque converter comprising: an annular body portion including an inner concave surface, an outer convex surface, an inner circumferential edge, and an outer circumferential edge; a plurality of blade tab slots for receiving a plurality of blades; and at least one positioning element including material protruding axially inward from the inner concave surface to form a tip of the positioning element for aligning a stator. A method for installing a torque converter onto a transmission is also provided. | 05-07-2015 |
| 20150132124 | INNER RING OF A FLUID FLOW MACHINE AND STATOR VANE ARRAY - An inner ring of a fluid flow machine includes fixing rings and seal carriers split into at least two fixing ring segments and into at least two seal carrier segments, respectively. The fixing ring segments and the seal carrier segments are arranged with the respective end faces facing each other. A first fixing ring segment has a first ring segment shoulder and a second fixing ring segment has an offset second ring segment shoulder. A first seal carrier segment has a first carrier segment shoulder, and a second seal carrier segment has a second carrier segment shoulder, which is offset with respect to the first carrier segment shoulder. In a separation plane of the inner ring, the first carrier segment shoulder abuts the second ring segment shoulder at the end face. Also in the separation plane, the second carrier segment shoulder abuts the first ring segment shoulder at the end face. | 05-14-2015 |
| 20150292363 | Faceted Housing For Axial Turbomachine Compressor - The invention relates to an external composite housing for a compressor of an axial turbomachine, the housing having a generally circular wall with a matrix and fiber reinforcement. The housing includes a circular wall with an internal surface having a continuous curve around the circumference of the wall. The wall includes flat facets that are flush with the internal curved surface of the wall. The facets are arranged in annular rows to receive annular rows of stator vanes. The facets are flat disks against which the vanes bear to optimize the orientation of the vanes, while reducing the concentrations of mechanical stresses at the platform/wall interfaces. | 10-15-2015 |
| 20150354597 | METHOD FOR ATTACHING/REMOVING VANE RING AND AUXILIARY SUPPORT DEVICE FOR VANE SEGMENT USED IN SAID METHOD - The present invention provides a method, in which a casing disposing step is executed for disposing a top casing ( | 12-10-2015 |
| 20160025108 | Vane with Sealed Lattice in a Shroud of an Axial Turbomachine Compressor - The present application relates to a stator of an axial turbomachine compressor. The stator includes a circular wall, such as an internal shroud, with a guiding surface in order to guide the primary flow of the turbomachine. The stator further includes a circular row of stator vanes, each of them including an airfoil which extends radially in the primary flow of the turbomachine, and a securing portion. The securing portion of the vane includes a lattice which has rods and which is secured and/or sealed in the shroud in order to fix the vanes to the shroud via the lattices. The stator includes a joint of abradable material which is arranged inside the internal shroud, and in which the lattice is secured in order to ensure retention, a fixing between the vane and the internal shroud. The vane is produced by means of additive production. | 01-28-2016 |
| 20160047257 | MOUNTING ARRANGEMENT FOR AEROFOIL BODY - The present disclosure provides an aerofoil body comprising a root portion and a tip portion, each having a pressure surface and a suction surface. The pressure surface and suction surface of the root and/or tip portion each comprise a respective ridge portion. Each ridge portion has an inclined first face and an oppositely inclined second face. Each ridge portion may be, for example, a triangular or semi-circular prism. | 02-18-2016 |
| 20160053621 | GAS TURBINE ENGINE AIRFOIL PLATFORM EDGE GEOMETRY - An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. The aft surface extends from a first aft edge to a second aft edge at a circumferentially extending edge. The contoured surface is arranged inboard from at least one of the first and second edges. | 02-25-2016 |
| 20160069199 | STATOR VANE PLATFORM WITH FLANGES - Disclosed is a gas turbine engine that includes a plurality of stator vanes. Each of the stator vanes includes an airfoil section and a platform provided at an end of the airfoil section. The platforms are provided with flanges on opposed ends thereof, and the flanges are fastened to corresponding flanges of an adjacent one of the plurality of stator vanes. | 03-10-2016 |
| 20160069200 | Turbine Vane With Platform Pad - A vane has an airfoil extending between a radially outer platform and a radially inner platform. At least one of the platforms has nominally radially thinner portions, and a pad defining a radially thicker portion. The pad has a radial thickness that is greater than a thickness of the nominal radially thinner portions. The pad surrounds an outer periphery of the airfoil on a side of the radially outer platform. The pad has a varying radial thickness. A mid-turbine frame and a gas turbine engine are also disclosed. | 03-10-2016 |
| 20160082674 | COMPOSITE WOVEN OUTLET GUIDE VANE WITH OPTIONAL HOLLOW AIRFOIL - A composite woven outlet guide vane ( | 03-24-2016 |
| 20160084097 | VANE RING BAND WITH NANO-COATING - An inner band used on a turbine engine is disclosed herein. The inner band may include a core comprising polymeric materials and a shell comprising nanocrystalline metallic materials applied to the core to cover at least a portion of the core. | 03-24-2016 |
| 20160090840 | CARRIERS FOR TURBINE COMPONENTS - A carrier segment for forming a carrier section for one or more gas turbine engine components, the carrier segment including a carrier wall extending between front and rear carrier ends and having a circumferential profile, the carrier segment being configured for defining radially inwardly thereof a chamber for receiving cooling air from an outboard feed source via the front end, wherein the circumferential profile of the carrier wall is undulating, e.g. with a simple waveform configuration or a more complex arrangement of interleaved series of oppositely oriented part-conical surface formations. | 03-31-2016 |
| 20160097291 | STATOR ASSEMBLY FOR A GAS TURBINE ENGINE - A stator assembly includes a platform located on a radially inner end of a plurality of vanes that connects a first vane to a second vane. There is a platform groove on a radially inner side of the platform between the first vane and the second vane. | 04-07-2016 |
| 20160169014 | IMPELLER HAVING SPOILERS FOR A TURBINE ENGINE TURBINE | 06-16-2016 |
| 20160177761 | Ceramic Matrix Composite Nozzle Mounted With a Strut and Concepts Thereof | 06-23-2016 |
| 20160186610 | AUSTENITIC SEGMENT FOR STEAM TURBINE NOZZLE ASSEMBLY, AND RELATED ASSEMBLY - An austenitic segment for a steam turbine nozzle assembly, along with related assemblies. Various embodiments include a steam turbine austenitic ring segment having: a body portion sized to substantially fill a pocket in a steam turbine outer diaphragm ring, the body portion having a greater circumferential length than an axial depth or a radial width thereof; and a hook-shaped portion extending radially inward from the body portion, the hook-shaped portion sized to engage a hook-shaped slot in the steam turbine outer diaphragm ring, wherein the body portion and the hook-shaped portion form a unitary structure. | 06-30-2016 |
| 20160194970 | ARRANGEMENT FOR SECURING TURBINE BLADES | 07-07-2016 |
| 20160201689 | FAN CASING AND FAN APPARATUS | 07-14-2016 |
| 20180023591 | METHOD FOR IMPROVING TURBINE COMPRESSOR PERFORMANCE | 01-25-2018 |
