Abstract: 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.

Abstract: A compressor nozzle device comprises a set of adjustable vanes which is interposed between two opposite wall members (3, 5), and a unison ring (7) for actuating said vanes (1). The unison ring (7) is arranged at a side of one of said wall members (3) opposite to the other side thereof facing the vanes (1).

Abstract: A gas turbine engine rotor drum includes spaced apart discs providing a cavity between the discs. The discs are configured to rotate in a rotational direction about an axis. An annular support is mounted on at least one of the discs and within the cavity. A cascade of relatively short anti-vortex members is mounted circumferentially on the annular support. The anti-vortex members include an outer end having a concave surface extending within the cavity radially outward from the annular support. The concave surface faces the rotational direction and promotes swirl as the rotor drum rotates.

Abstract: 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.

Abstract: 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.

Abstract: A locking member for a device for fastening ring sectors to an aircraft turbine engine casing is disclosed. The member has first and second clamping branches, which are connected together by curving joining portions, via a connecting branch. The joining portion of center thickness E1 has an inside surface of mean radius Rm1, and the joining portion of center thickness E2 has an inside surface of mean radius Rm2. Thickness E1 is strictly smaller than thickness E2, and mean radius Rm1 is strictly smaller than mean radius Rm2.

Abstract: A stage of variable-pitch vanes for a turbomachine is disclosed. The vanes include internal pivots engaged in corresponding housings of a sectorized internal ring. Each ring sector includes axial orifices for mounting two pins for the radial retention of the ring sector on the internal pivot of a vane. Each pin includes an immobilization device cooperating by shape coupling with a complementary immobilization device of the other pin in order to rotationally immobilize these pins in the orifices in the ring sectors.

Abstract: 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.

Abstract: A turbomachine stator forming a stator vane ring or upstream guide vane element including a plurality of vanes placed radially between a first inner ring and a second outer ring is disclosed. The two rings are concentric and the second ring has a cylindrical outer surface portion. The stator is characterized in that, on the outer surface portion, at least one vibration-damping laminate is attached. The laminate includes at least one layer of viscoelastic material in contact with the surface portion and one counterlayer of rigid material.

Abstract: The connection assembly of an arm to a sleeve is carried out substantially by parts of axes crossing the arm and the spacers between the parts of axes and the sleeve and the assembly bolts. The assembly and the disassembly are easy, even with highly reduced encumbrance, as the connection is light and devoid of high internal efforts, and a good position precision is obtained. The assembly may be applied to stators with an exterior sleeve and, an interior hub and radial link arms, which are encountered in certain turbomachines.

Abstract: A high-pressure turbine of a turbomachine, including at least one upstream guide vane element and an impeller mounted so as to rotate inside ring sectors attached to an annular support which is suspended from an outer casing, the upstream guide vane element including, at its radially inner end, a mechanism for attachment to an inner casing and, at its radially outer end, a mechanism for pressing axially on a fixed element of the turbine that is suspended from the outer casing independently of the annular support for attachment of the ring sectors.

Abstract: An exemplary embodiment of the invention is directed to a turbine engine having a circumferential casing with a circumferentially extending slot formed in an inner wall. A radially inwardly facing fin-ring is disposed in the slot and has a radially inwardly projecting fin extending axially there across. A radially inwardly extending stator blade has a base and an airfoil. The base is disposed in the casing slot, radially inwardly of the fin-ring. A complementary base slot is disposed in the stator blade base and is configured to receive the fin therein for the transfer of a circumferential force, applied to the stator blade, to the fin-ring.

Abstract: A gas turbine engine is provided comprising an outer casing and a plurality of circumferentially positioned vane segments. The outer casing is provided with a circumferential casing slot. The plurality of circumferentially positioned vane segments are coupled to the outer casing. Each vane segment comprises at least one vane airfoil, a radially inner shroud coupled to a first end of the airfoil, a radially outer shroud coupled to a second end of the airfoil, and a strongback fixedly coupled to axially spaced-apart portions of the outer shroud such that a gap is provided between the strongback and the outer shroud. The strongback may comprise axially spaced-apart first and second end portions received in the casing slot.

Abstract: A technique for refurbishing nozzle diaphragm sections of a gas turbine replaces an eroded section of the nozzle diaphragm with a replacement part designed to engage a slot machined in the nozzle diaphragm. The replacement part is formed of a material with capable of sustained exposure to higher temperature than the original eroded section, and with a similar coefficient of expansion as the material used for manufacture the original nozzle diaphragm. The combination of the nozzle diaphragm and the replacement part conform to the original manufacturer's dimensional specifications for the nozzle diaphragm.

Abstract: A variable stator vane airfoil is mounted on a button centered about a rotational axis and includes circular leading and trailing edges circumscribed about the rotational axis at a button radius. Contoured pressure and suction sides extend from the circular leading edge to the circular trailing edge and are recessed inwardly from a perimeter circumscribed about the rotational axis at the button radius. One of upstream and downstream pressure side portions of the contoured pressure side is straight and another of the upstream and downstream pressure side portions is convexly curved. One of the upstream and downstream suction side portions is straight and another of the upstream and downstream suction side portions is convexly curved. One of the upstream pressure side portion and upstream suction side portion is straight and another of the upstream pressure side portion and upstream suction side portion is convexly curved.

Abstract: A stator vane assembly for a compressor has a support structure which carries and is bounded by an annular stator vane structure. The stator vane structure comprises a central bore and a sleeve carried on the central bore. The sleeve is disposed between the support structure and bore of the annular stator vane structure. The annular stator vane structure is made from a non-metallic composite material and the sleeve is made from a first material. The coefficient of thermal expansion of the non metallic material is equal to or less than the co-efficient of thermal expansion of the first material.

Abstract: A turbine stage in a turbomachine is disclosed. The stage includes 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.

Abstract: A vane assembly for a gas turbine engine comprising a number of radial loading elements disposed between lugs of the vane ring and the vane support, such as to generate a radial load force against the vane ring. The radial load force prevents unwanted relative movement between the vane ring and the vane support during operation of the gas turbine engine.

Abstract: Protective insert plates (54, 56) installed on a working gas face (42) of a turbine vane platform (26) provide replaceable portions of a turbine shroud for improved maintenance. The plates act as tiles, and may be formed of ceramic materials for thermal protection. Two cages (58, 60) in the vane platform slidably receive the two insert plates (54, 56) from opposite circumferential sides (36, 38) of the platform. The plates slide into the cages up to the pressure and suction sides (32, 34) of the vane airfoil (22). The plates may have proximal edges (62, 64) shaped to fit the respective pressure and suction sides of the vane airfoil. A retainer plate 66 may be attached to a flange (72) on the cooled face (48) of each platform, and may contact each insert plate with a locking device (74, 76) to prevent sliding of the plate in the cage.

Abstract: A reaction mount system that provides support for the stator vane for a gas turbine engine is described comprising a stator hanger located on an outer band at a first location and a stator stopper located at a second location that is located circumferentially apart from the first location. A stator assembly for a gas turbine engine is described, the stator assembly comprising a stator vane having an airfoil, an outer band located on a radially outer end of the airfoil, a shroud hanger located axially adjacent to the outer band, the shroud hanger comprising a post wherein at least a portion of the post extends in an axial direction over a portion of the outer band, and a reaction mount system located on the outer band wherein the reaction mount system engages with the post to provide support for the stator vane.

Abstract: A straightener blade for a turbomachine, comprising a platform arranged at a radially external end of the blade and adapted to be engaged in a annular groove of a housing, and a threaded rod radially extending outwardly from the platform and adapted to pass through an orifice of the housing in order to receive a fixing nut, the upstream and downstream edges of the platform each comprising a protrusion extending in the plan of the platform in order to limit the rotation of the platform in the groove when the nut screwed on the threaded rod is tightened.

Abstract: A guide device for a turbomachine, particularly a steam turbine, with a guide vane ring and a plurality of guide vanes which are fastened to the guide vane ring so as to be distributed along the circumference of the guide vane ring. The guide vane ring has a groove, and the guide vanes also have grooves which are aligned with the groove of the guide vane ring in the assembled state. The guide vanes are fixed in their radial position at the guide vane ring by means of a retaining ring which engages in the groove of the guide vane ring and in the grooves of the guide vanes.

Abstract: A retention pin for fastening retaining lugs of an outer sidewall, of a turbine nozzle, within a groove between a forward land and an aft land of a retaining ring. The retention pins fit through coaxial holes in the lug and the lands, securing the radial and circumferential location of the nozzles as well as allowing transitional motion. While maintaining limited contact with both the nozzles and the retaining ring they significantly reduce conductive heat transfer from the nozzle to the retaining ring. By positioning the nozzles, they also set the desired nozzle throat areas for targeted turbine performance. The pins have been designed such that the nozzle cannot disengage within the assembly due to the pin backing out of its nominal axial position, and the pin will not fail due to low cycle fatigue, creep, or yielding, all of which prevent nozzle fallout.

Abstract: Gas turbine systems having flexible chordal hinge seals are provided. According to an embodiment, a turbine system comprises: a nozzle segment comprising a stator vane extending between an inner band segment and an outer band segment; an inner support ring adjacent to the inner band segment; and an inner chordal hinge seal in operable communication with the nozzle segment, the inner chordal hinge seal comprising a flexible inner rail extending inwardly from the inner band segment, the inner rail having a projection for sealingly engaging the inner support ring.

Abstract: 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.

Abstract: An intermediate casing for use in a gas turbine engine comprises inner and outer casing walls 2, 4, a support plate 6, supporting an axial end of each of the casing walls 2, 4, a splitter 8, and an array of vanes 10. At least one of the casing walls 2, 4, the support plate 6, the splitter 8 and the array of vanes 10 is formed from at least one blank of sheet material, such as steel. The formation of one or more components of the assembly from a flat blank of material provides a significant reduction in manufacturing cost.

Abstract: A variable nozzle for a turbocharger includes a plurality of vanes rotatably mounted on a nozzle ring and disposed in a nozzle flow path defined between the nozzle ring and an opposite nozzle wall. Either or both of the faces of the nozzle ring and nozzle wall include(s) at least one step that defines sealing surfaces positioned to be substantially abutted by airfoil surfaces of the vanes in the closed position of the vanes and to be spaced from the airfoil surfaces in positions other than the closed position. This substantial abutment between the airfoil surfaces and the sealing surfaces serves to substantially prevent exhaust gas from leaking past the ends of the airfoil portions. At the same time, clearances between the nozzle ring face and the end faces of the airfoil portions can be sufficiently large to prevent binding of the vanes under all operating conditions.

Abstract: An outer seal assembly of a turbine rotor stage is secured within a circumferential groove of the turbine casing in such a manner as to both fix the outer seal assembly in its installed position and also provide for sealing around its outer periphery so as to thereby prevent the leakage of cooling air therearound. A plurality of arcuate elements having an angle-shaped cross sectional profile are provided to interface between radially extending arms of the outer seal assembly and the inner surface of the casing, with a locking mechanism then being applied to secure the two structures in their installed positions. Each of the arcuate elements includes a radially extending panel, a plurality of forwardly extending hooks that are disposed within a groove in the casing, and a second forwardly extending flange that engages the rear surface of the outer seal assembly arm.

Abstract: A centrifugal pump with a volute and at least one stage with an associated impeller and removable diffuser assembly comprises: multiple diffuser segments, each diffuser segment comprising a central passage from an inner curvilinear surface to an outer curvilinear surface and a curvilinear leading engagement surface between a leading end of its curvilinear inner surface and its curvilinear outer surface; multiple curvilinear volute mounting surfaces within the volute, each curvilinear mounting surface receiving a corresponding diffuser segment to mount the diffuser segments in a generally annular pattern about the impeller to form the removable diffuser assembly, with the curvilinear inner surface of each diffuser segment proximate an outer periphery of the impeller and the curvilinear leading engagement surface of each diffuser segment engaging a trailing portion of the curvilinear outer surface of an adjacent one of the diffuser segments; and a volute connecting passage within the volute for coupling the cen

Abstract: 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.

Abstract: A load pin has an end portion, and a vane has a base with a cutout in the base, wherein the end portion of the load pin engages a wall portion of the cutout in the base of the vane, thereby inhibiting any movement of the vane in a particular direction.

Abstract: 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.

Abstract: 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.

Abstract: A ring vane nozzle for a gas turbine engine according to an exemplary aspect of the present disclosure includes a multiple of fixed turbine vanes between an inner vane ring and an outer vane ring and a multiple of rotational turbine vanes between the inner vane ring and the outer vane ring, each of the rotational turbine vanes rotatable about an axis of rotation.

Abstract: 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.

Abstract: A nozzle blade comprising radially inner and outer walls with an airfoil portion extending therebetween; the inner and outer walls formed with alignment features on respective oppositely-facing surfaces aligned with a longitudinal center axis through the nozzle blade.

Abstract: 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.

Abstract: 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.

Abstract: 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 rigid ring of 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 slit in a casing that receives the vane units allows for the installation of vane units with interlocking pins without the necessity of having to remove the rotor from the casing.

Abstract: A technique for refurbishing nozzle diaphragm sections of a gas turbine replaces an eroded section of the nozzle diaphragm with a replacement part designed to engage a slot machined in the nozzle diaphragm. The replacement part is formed of a material with capable of sustained exposure to higher temperature than the original eroded section, and with a similar coefficient of expansion as the material used for manufacture the original nozzle diaphragm. The combination of the nozzle diaphragm and the replacement part conform to the original manufacturer's dimensional specifications for the nozzle diaphragm.

Abstract: 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.

Abstract: A method facilitates the assembly of a gas turbine engine. The method of assembly comprises providing a turbine nozzle including an inner band, an outer band, at least one vane extending between the inner and outer bands, and at least one leading edge fillet extending between the at least one vane and at least one of the inner and outer bands, wherein a leading edge of the at least one vane is downstream from the leading edges of the inner and outer bands, and coupling the turbine nozzle within the gas turbine engine such that the leading edge fillet is configured to facilitate minimizing vortex formation along the vane leading edge adjacent at least one of the inner and outer bands.

Abstract: 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.

Abstract: The present invention relates to a turbine engine rectifier stage comprising a plurality of fixed vanes connecting an inner ferrule support 19 to an outer ferrule support 14, said inner ferrule support and said outer ferrule support defining an aerodynamic vein and comprising a set of contiguously assembled sectors 20,15 respectively, the plurality of fixed vanes comprising so-called structural vanes 5 surrounding so-called non-structural or aero vanes 6 so as to form boxes 7, said structural vanes 5 being rigidly attached to the ends of the sectors of the inner ferrule support 20 by means of attachment elements 17 in order to impart increased stiffness to the boxes 7.

Abstract: An example variable stator vane assembly includes at least one button, a vane airfoil adjacent to the button, and a fillet defined between the button and the airfoil. In one example, the fillet defines a constant radius and extends beyond the button at least greater than a distance of 60% of a length of an overhang portion of the vane airfoil.

Abstract: The present invention relates to a device for attaching a turbomachine stator vane in an annular casing (20) of the turbomachine, the vane comprising a tip formed of a platform (14) with two edges (141, 142), one of them forming an upstream edge (141) and the other forming a downstream edge (142), an airfoil (11) and a root (13), the annular casing (20) comprising a circumferential groove (23) formed in its interior wall with an upstream flank (21) and a downstream flank (22), the vane being held by engagement of the platform (14) in the groove (23), the upstream edge against the upstream flank (21) and the downstream edge (142) against the downstream flank (22) of the groove (23), the downstream flank (22) of the groove (23) being in the form of a slot (22) opening axially in the upstream direction, the downstream edge of the platform (23) being engaged in said downstream flank (22) and a fastening means (40) being attached in order to hold the platform (14) in the groove on the upstream side, wherein the va

Abstract: A diffuser/guide vane assembly for an aircraft turbojet or turboprop engine is disclosed. The diffuser includes annular flanges joined by blades and the guide vane assembly includes cylindrical shelves joined by vanes. The annular flanges and the cylindrical shelves are formed from metal sheets to which the vanes are assembled by brazing.

Abstract: A gas turbine includes a nozzle vane and a sealing unit engaged with the nozzle vane inside a turbine supplied with combustion gases produced by mixing and burning air for combustion and fuel. The nozzle vane and the sealing unit are disposed in a channel of the downward flowing combustion gases on the outlet side of a gas path. A plurality of engagement portions between the sealing unit and the nozzle vane are provided successively from the upstream side toward the downstream side in a direction of flow of the combustion gases, and a downstream one of the plurality of engagement portions has a contact interface formed in a direction across a turbine rotary shaft. A reduction in the thermal efficiency of the gas turbine can be suppressed.

Abstract: 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.

Abstract: 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.