Abstract: A steam turbine diaphragm stage having a self-aligning flow splitter is disclosed. In one embodiment, a steam turbine flow splitter body is disclosed, the steam turbine flow splitter body having a central portion and two end portions, and including: a flow divider proximate to the central portion; and a substantially radially outward extending hook proximate to at least one of the two end portions.

Abstract: A mounting apparatus for a fan includes a bracket, two fixing members, two screws, and a shield plate. The bracket includes a fixing plate defining a vent and two first through holes adjacent to opposite ends of a top of the vent. The screws extend through the fixing members and the first through holes of the bracket, in that order, for engaging in an upper portion of the fan arranged behind the fixing plate, with the vent aligning with the fan. A top of the shield plate is rotatably connected between the fixing members. The shield plate hangs vertically by gravity to cover the vent upon a condition that the gravity of the shield plate is not overcome by airflow passing through the vent.

Abstract: 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.

Abstract: A mechanical joint for a gas turbine engine includes:(a) an annular first component having an annular, radially-extending first flange; (b) an annular second component having an annular, radially-extending second flange abutting the first flange; (c) a plurality of generally radially-extending radial channels passing through at least one of the first and second flanges; (d) a plurality of generally axially-extending channels extending through the first flange and communicating with respective ones of the radial channels; and (e) a plurality of fasteners clamping the first and second flanges together.

Abstract: A compressor diffuser for a gas turbine includes: a compressor diffuser having an upstream end and a downstream end, the downstream end defined by a peripheral annular edge, the annular edge formed with a plurality of substantially axially-oriented slots extending from an opening at the downstream edge in an upstream direction.

Abstract: An assembly for a stator stage of a turbomachine is disclosed. The assembly includes: an outer shroud presenting a series of openings for mounting each stationary vane by welding between the edge of an opening and the outline of the platform of the vane, the outline of the outer segment of an opening surrounding, in radial projection, the outline of the inner segment thereof, the shroud not having any other holes; and at least one stationary vane with its top including a non-pierced platform received in one of the openings prior to the welding step, such that an inside face of the platform bears against a bearing face of the shroud, the outline of the platform presenting a shape that is identical to the shape of the outline of the opening.

Abstract: A retaining seal assembly for use in a gas turbine engine is provided. The retaining seal assembly comprises an outer retaining ring coupled to an aft end of a gas turbine engine combustor. A turbine nozzle is coupled to the outer retaining ring and comprises an outer band. The outer band comprises a leading edge and an opposing trailing edge that defines a slot. A retention seal comprises a first end positioned within the slot, a generally opposing second end that contacts the outer retaining ring, and a body extending between the first end and the second end. The body further comprises an insertion portion positioned within a passage formed in the outer band. The retention seal is fabricated from a resilient material and is configured to facilitate coupling the turbine nozzle to the outer retaining ring.

Abstract: A nozzle segment for a gas turbine engine includes a flange which extends from a vane platform, the flange includes a hollow cavity.

Abstract: According to an aspect of the present invention, there is provided a variable geometry turbine comprising: a turbine wheel mounted on a turbine shaft within a housing assembly for rotation about a turbine axis, the housing assembly defining a gas flow inlet passage upstream of the turbine wheel; an annular wall member defining a wall of the inlet passage and which is displaceable in a direction substantially parallel to the turbine axis to control gas flow through the inlet passage; at least one moveable rod operably connected via a first end of the rod to the annular wall member, the rod being moveable to control displacement of the annular wall member, the rod extending in a direction substantially parallel to the turbine axis, the rod being connected to the annular wall member via a first arm and a second arm, a first end of the first arm and a first end of the second arm being attached to the rod, and a second end of the first arm being attached to the annular wall member at a first circumferential positi

Abstract: A vane fixing apparatus for removably fixing a vane plate (14) to a web (12) is described. The vane fixing apparatus comprises a mounting bracket (16) attached to the vane plate (14), and a mounting block (20,30) held on the web (12) by at least one fastener (18), wherein the mounting block (20,30) is moveable between a first configuration in which the mounting bracket (16) may engage and disengage the mounting block (20,30) and a second configuration in which the mounting block (20,30) securely retains the mounting bracket (16) relative to the web (12), and wherein the mounting block (20,30) is moveable between the first and second configurations by operation of the fastener (18).

Abstract: A torque converter includes a pump shell constituting an internal space for retaining ATF and capable of rotating about the rotation axis; a blade engaging with the pump shell; and an extension sleeve pressing the blade against the pump shell. The pump shell has a groove into which a tip portion of the blade is fit formed at its inner peripheral surface. In the state where the tip portion is fit into the groove, the extension sleeve presses the blade to fix the blade to the pump shell. The groove forms an acute angle ? with respect to a meridian of the shell passing through the groove. The groove extends in one direction, has one end opened and the other end closed, and has a width larger on the side of the one end than on the side of the other end. The groove has a portion smallest in width equal to the width of the tip portion.

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 fairing for a structural strut in a gas turbine engine includes: (a) an inner band; (b) an outer band; (c) a hollow, airfoil-shaped vane extending between the inner and outer bands; (d) wherein the fairing is split along a generally transverse plane passing through the inner band, outer band and vane, so as to define a nose piece and a tail piece; and (e) complementary structures carried by the nose piece and the tail piece adapted to secure the nose piece and the tail piece to each other.

Abstract: Exemplary embodiments provide an information system adapted to focus a plurality of audio messages to a plurality of different locations. As a consumer passes a display, their attention is attracted based on the series of messages. Further, a consumer can obtain more and different information as they change their position. Exemplary embodiments may also display a different image to the consumer depending on the position of the consumer relative to the display. Further embodiments may utilize touch-screen technology to allow a user to select an icon from the screen and obtain further information either through additional messages, video, or both.

Abstract: A retention structure includes a center body including an outer surface, an enclosed end, an open end, and a contact section, the outer surface adapted to define a first portion of a flowpath, and the contact section extending radially outwardly from a centerline and located on the enclosed end and configured to reduce a radial and a torsional component of a first load that exceeds a first threshold applied to the contact section, when the turbine rotates and applies the first load to the contact section and an energy absorber coupled to the center body, disposed adjacent to the contact section, and having an outer surface adapted to define a second portion of the flowpath, the energy absorber further adapted to collapse, when the turbine rotates and contacts the energy absorber and applies a second load that exceeds a second threshold to the energy absorber.

Abstract: A turbine nozzle assembly and a method for assembling the turbine nozzle assembly with respect to a combustor of a gas turbine engine are provided. The method includes coupling a radial outer retaining ring to an aft end of the combustor. A plurality of turbine nozzles are provided. Each turbine nozzle includes an inner band, a radially opposing outer band, and at least one vane extending between the inner band and the outer band. The outer band of each turbine nozzle is coupled to the outer retaining ring to define the turbine nozzle assembly. An inner retaining ring is positioned about an axis of the gas turbine engine and coupled to the inner band of each turbine nozzle.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.

Abstract: An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1. X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape.

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 method facilitates assembling a diaphragm assembly for a steam turbine. The method includes forming at least one opening within a radially outer band and forming at least one opening within a radially inner band. The method further includes coupling at least one partition to at least one opening within the radially outer band including a radially inner surface and a radially outer surface wherein the at least one opening is at least partially defined by a wall that extends obliquely between the outer band radially inner surface and the outer band radially outer surface. The method additionally includes coupling the at least one partition to the at least one opening within the radially inner band wherein the at least one partition extends between the at least one radially outer band opening and the at least one radially inner band opening.

Abstract: An assembly for a gas turbine engine includes a combustor and a vane assembly disposed downstream thereof. A portion of an outer platform of the vane assembly defines an axial sliding joint connection with the combustor, and includes a plurality of depressions located in an outer circumferential surface thereof opposite the combustor. The depressions are disposed in regions of expected higher thermal growth about the circumference of the outer platform such that thermal growth of the entire outer platform is substantially uniform circumferentially therearound.

Abstract: A turbine nozzle includes outer and inner bands bounding nozzle vanes. The outer band includes an aft flange. An impingement baffle bridges the outer band and aft flange at the root thereof to provide impingement cooling.

Abstract: A turbine vane ID support system usable to support the ID of a turbine vane and including a transition seal system and a turbine vane ID forward rail seal system. The transition seal system may seal the turbine vane ID support body to a transition, and the turbine vane ID forward rail seal system may seal the turbine vane ID support body to a turbine vane. Use of the transition seal system and the turbine vane ID forward rail seal system eliminates the problems inherent with conventional seals used to seal transitions directly to turbine vanes. The turbine vane ID support system may also be configured such that the turbine vane ID support system may be removed to facilitate removal of turbine vanes and blades for repair or replacement.

Abstract: A support for the first row turbine vanes (12) in a gas turbine engine, the support including a support framework (18). The support framework (18) includes an outer vane carrier (34), and an inner vane carrier (36) connected to the outer vane carrier (34) by a plurality of struts (44, 46). The outer vane carrier (34) is mounted to an inner casing (16) of the engine and the struts (44, 46) support the inner vane carrier (36) in cantilevered relation to the outer vane carrier (34). An aft outer flange (94) of each first row vane (12) is supported on the outer vane carrier (34) and a forward inner flange (114) of the vane (12) is support on the inner vane carrier (36).

Abstract: A fairing for a structural strut in a gas turbine engine includes: (a) an inner band; (b) an outer band; (c) a hollow, airfoil-shaped vane extending between the inner and outer bands; (d) wherein the fairing is split along a generally transverse plane passing through the inner band, outer band and vane, so as to define a nose piece and a tail piece; and (e) complementary structures carried by the nose piece and the tail piece adapted to secure the nose piece and the tail piece to each other.

Abstract: A compressor vane having a root, a tip and an airfoil portion extending between the root and the tip is disclosed. A grommet is used in conjunction with the vane and has a lip sealingly surrounding a portion of the vane root and a circumferential portion protruding around a perimeter of the lip in engagement with a surface of a platform of the vane root. The circumferential portion has a profile similar to that of the airfoil portion.

Abstract: A vane for a vane assembly of a gas turbine engine includes a vane root connected to the airfoil portion opposite a tip thereof. The vane root includes a platform and a button portion interconnecting the platform and the airfoil position. The button portion has relatively blunt leading and trailing ends which respectively protrude beyond leading and trailing edges of the airfoil portion.

Abstract: A vane assembly for a gas turbine engine including a shroud with openings defined about a circumference of the shroud and vanes extending radially from the shroud with a vane tip in each opening. Isolating apparatus are disposed in each opening to isolate the vane tip from the shroud ring. Each vane tip is engaged with the shroud by retaining apparatus for restricting movement of the vane tip in an axial direction relative to the shroud.

Abstract: A vane including a root, a tip and an airfoil portion extending between the root and the tip, the vane also including a button portion interconnecting the airfoil portion and the root. The button portion protrudes beyond a profile of the airfoil a distance less than the root. The button portion includes leading and trailing ends free of sharp edges. The leading and trailing ends respectively protrude beyond leading and trailing edges of the airfoil portion.

Abstract: A vane assembly for a gas turbine engine including a shroud ring with openings and isolating arrangement isolating a vane extremity within each opening, the isolating arrangement cooperating to form a continuous gas path surface completely covering at least an axial portion of a surface of the shroud ring.

Abstract: A bling nozzle/carrier interface design for a steam turbine is provided wherein there is limited contact between the carrier (casing, shell) to allow for ease of assembly. There is also limited contact in strategic locations to both reduce the roll, or downstream deflection, of the inner portion and to improve disassembly due to limited contact in areas where corrosion can occur.

Abstract: A retaining key for a turbine nozzle includes a key body having top and bottom surfaces, a pair of sides and a pair of ends including a forward end having a pair of horizontal shoulders on opposite sides of a center rib, the shoulders located substantially midway between the top and bottom surfaces such that the forward end has a substantially inverted T-shaped profile, and a rearward end having a first surface portion extending from and substantially perpendicular to the top surface and a second surface portion extending at an acute angle downwardly and toward the forward end and intersecting the bottom surface.

Abstract: A method is provided for attaching a shim to at least one of a base of a stator vane unit and a ring segment of a ring segment assembly in a gas turbine compressor. The method includes providing a shim shaped to conform to an engaging face of the base of the stator vane unit or the segment ring of the segment ring assembly, with a predetermined thickness dimension; boring at least one hole, normal to the face of the shim and extending fully through the thickness dimension of the shim; positioning the shim on the engaging face of the at least one of the base of the stator vane unit and the segment ring of the segment ring assembly; and welding the shim to the engaging face of the at least one of the base of the stator vane unit and the ring segment of the stator ring assembly.

Abstract: A turbine and a method for dismantling a blade of a turbine. A turbine includes a rotor that extends in an axial direction and an accessible combustion chamber, which communicates with an annular hot-gas conduit, in which a plurality of blades that form a blade row is arranged. Each blade has a blade root that is fixed to the internal housing and a blade head that lies opposite the root and faces the rotor, the head being fixed to a fixing ring of the turbine that encircles the rotor. To reduce the down time of a turbine during repair, inspection and/or maintenance work, the blade root and/or the blade head can be fixed by means of a manually detachable clamping device. The clamping device is released from the blade and locked in a parking position beyond a displacement path used for removing the blade through the combustion chamber.

Abstract: This present invention concerns an axial gas turbine engine compressor which includes a casing and a distributor wheel composed of a multiplicity of sectors in arcs of circles, with radial stator blades fixed to an external platform, characterized by the fact that the said platform is retained in the casing by two joints of the tongue and groove type, one upstream and the other downstream of the stator blades, the said downstream joint being formed between a transverse flange provided on the external platform and a flange provided on the casing, with a securing resource to create a tight joint between the two flanges. It is preferable that the securing resource should be a bolt. The invention provides for effective retention of the sector so as to prevent wear in the surfaces in contact. The solution is easy to implement.

Abstract: A simplified vane mounting arrangement by which a vane ring can be pre-assembled to an inner support ring before being installed in an outer casing.

Abstract: The retaining hooks (32) of a flange (22) of straightening sectors (20), bearing fixed blades in a turbomachine, are advantageously placed on an end plate (30) distinct from the casing (21) but assembled on the latter. In this way, these hooks no longer constitute weak points in the casing, as if they were all in one piece with it, assembly of the sectors (20) is facilitated, and the assembly is more rigid.

Abstract: A housing including an outer casing provided with bearer hooks for stator rings and sealing rings. The hooks are discontinuous angularly and joined to a casing by tenon and mortise assemblies. The hooks and the casing may therefore be made in different materials, the hook material having good resistance to heating and the other material lending itself better to machining and forming. Ventilation, clearance piloting and heat protection are facilitated.

Abstract: A machine stator and assembly and disassembly methods. The elements of a casing portion are formed of consecutive shells in line with grooves configured to house roots of guide vane stages that are fixed in place by springs and pins for stopping rotation. The elements are arranged in a complete circle, and the assembly is made by axially separating the elements to insert the guide vane stages between the elements by a radial movement.

Abstract: A device for stopping rotation of a fixed blade bearing sector in a gas turbine casing. Sectors of synchronizing ring blades are maintained against tangential rotational movements by sliding into grooves of a casing by pins passing through perforations in an extension of the two parts. The pins are prevented from accidental removal either by a flexible lock ring or by a locking tab maintained between the two parts when they have been completely assembled.

Abstract: A method enables a gas turbine engine including a first rotor assembly and a second rotor assembly coupled in axial flow communication downstream from the first rotor assembly to be assembled. The method comprises coupling an upstream end of an extension duct to an outlet of the first rotor assembly, wherein the extension duct includes a plurality of panels coupled circumferentially, and coupling a downstream end of the extension duct to an inlet of the second rotor assembly using at least one fish mouth seal.

Abstract: A stator vane span attachment for a gas turbine having a casing 1 in which several stator vane spans 2 are located, wherein means 3 are provided for restraining the stator vane spans 2 against the casing 1.

Abstract: An annular hanger for supporting an annular wall element from a gas turbine engine annular outer casing is circumscribed about a centerline extending in opposite first and second axial directions and has an annular first hook extending in the first axial direction from said body section and an annular second hook extending in the second axial direction. One of the hooks has circumferentially spaced apart tabs extending equal axial lengths from the body section and corresponding notches circumferentially disposed between a corresponding adjacent pair of the tabs. The annular hanger is used to support at least in part a wall element from the outer casing as part of a bayonet mount. The bayonet mount further includes a bayonet slot on one of the casing and the wall element and the hanger tabs are received within the bayonet slot.

Abstract: A turbine nozzle assembly for a gas turbine engine, including: a plurality of segments joined together to form an outer band; a plurality of segments joined together to form an inner band; at least one airfoil positioned between the outer and inner bands; a leaf seal attached to each inner band segment by at least one pin member; and, a leaf seal attached to each outer band segment by at least one pin member. Each of the inner band segments includes a protrusion extending from a surface thereof so as to provide balanced support to the corresponding leaf seal in conjunction with the pin members. Each of the inner band segments further includes a first portion having a flange extending therefrom, a second portion opposite the first portion, a first end, and a second end opposite the first end, wherein the surface extends between the first and second ends and the first and second portions.

Abstract: A steam turbine of the type which incorporates a turbine case defining a plurality of passages having outlets opening through an inside end wall of the turbine case in a direction generally parallel to the turbine shaft, with nozzles positioned over the outlets to direct steam against the periphery of the turbine wheel, can be modified to a higher efficiency design. To perform the modification, the nozzles are removed, an arcuately shaped housing is positioned in covering relationship with the outlets, and an arcuately shaped louver is positioned so as to form an end wall of the housing. The louver has a plurality of vanes to direct the steam against the periphery of the turbine wheel to cause rotation of the turbine shaft and the housing forms a confined steam flow path from the outlets to the louver. The downstream turbine blading can be modified if desired.

Abstract: A turbine nozzle assembly for a gas turbine engine, including: a plurality of segments joined together to form an outer band; a plurality of segments joined together to form an inner band; at least one airfoil positioned between the outer and inner bands; a leaf seal attached to each inner band segment by at least one pin member; and, a leaf seal attached to each outer band segment by at least one pin member. Each of the inner band segments includes a protrusion extending from a surface thereof so as to provide balanced support to the corresponding leaf seal in conjunction with the pin members. Each of the inner band segments further includes a first portion having a flange extending therefrom, a second portion opposite the first portion, a first end, and a second end opposite the first end, wherein the surface extends between the first and second ends and the first and second portions.

Abstract: A seating spring is provided for a gas turbine engine compressor stator having a casing with a circumferential casing slot for mounting a plurality of vane sectors at outer bands thereof. The seating spring has at least one reaction tab configured to abut the casing at one side of the casing slot and a spring arm connected to the reaction tab and configured to abut a respective one of the outer bands to bias the outer band against the casing at a second side of the casing slot. A retention arm is connected to the reaction tab and engages the casing so as to be prevented from moving radially outward. The spring arm is thereby retained in contact with the outer band.

Abstract: A turbine bucket tip shroud is reinforced by introducing a reinforcing material such as a ceramic-matrix composite as reinforcing rods or bars into the casting of the tip shrouded turbine bucket, to provide resistance to creep deformation. By reducing creep deformation, unlatching of the interlocked tip shrouds is minimized, and bucket overload and vibratory failures are avoided.

Abstract: The invention provides a novel sealing device and plenum assembly particularly adapted for forming a plenum inwardly of a circumferential stator blade array in a gas turbine engine. A Tangential On Board Injection plenum (T.O.B.I.) is defined by assembly of: a forward plate; a rearward plate; and a segmented inner shroud disposed between the forward and rearward plates. Releasable elongate fasteners are disposed in joints between a series of inner shroud segments with sealing sheaths laterally surrounding the fasteners. While clamping the shroud segments between the forward and rearward plates, the fasteners and sheaths simultaneously seal the joints and secure the inner shroud segments with forward and rearward plates in a rigid structural assembly.