Abstract: A rotating blade row is provided for the final stage of a steam turbine has blades with an integrated shroud. The shroud of each blade has a projection in the axial direction, in each case on its pressure side, which prevents droplets in the working fluid of the steam turbine from reaching the shroud fillet of the respective subsequent blade in the flow direction. The shroud fillet is therefore protected against erosion damage caused by droplets impact erosion. The projection is positioned and of such a size that mass equilibrium is ensured between the suction side and the pressure side of the shroud, and stress equilibrium is ensured between the projection on the pressure side and the suction-side shroud. The projection furthermore has a recess between its greatest axial extent and the leading edge.

Abstract: A steam turbine includes two or more rotating blades and a diaphragm outer ring. Each of the rotating blades includes a tip cover, moisture-trapping grooves, a droplet ejection hole, and a drain guide groove. The tip cover is provided to a tip of each of the rotating blades and is connected in contact with another tip cover adjacent to the tip cover. The moisture-trapping grooves are formed in a longitudinal direction of each of the rotating blades. The droplet ejection hole is to connect an outside of the tip cover on a side of the diaphragm outer ring with an inside of the tip cover. The drain guide groove is to connect ends of the moisture-trapping grooves on the side of the tip cover with the droplet ejection hole. The diaphragm outer ring includes a drain pocket which faces the droplet ejection hole.

Abstract: Systems and devices for thermodynamically regulating portions of a dynamoelectric machine are disclosed. In one embodiment, a fan assembly element includes: an axially inner shroud segment configured to form a portion of an annular assembly about a rotor of a dynamoelectric machine, wherein the axially inner shroud segment includes a rotor hub interface configured to physically connect to a complementary portion of a rotor hub; a set of fan blades physically connected to and extending axially from a face of the axially inner shroud segment; and an axially outer shroud segment physically connected to the set of fan blades.

Abstract: An eddy-type wind power generator includes an inlet tube, an outlet tube and an electricity-generating assembly. The inlet tube has a first end and a second end. The first end has an inlet, an eddy opening and a plurality of air-guiding holes. An intake air channel is formed inside the inlet tube. The outlet tube receives the inlet tube and has an opening end and a closed end. An exhaust channel is formed between the inlet tube and the outlet tube. A gap is formed between the closed end of the outlet tube and the second end of the inlet tube. The exhaust channel communicates with the intake air channel via the gap. The electricity-generating assembly is disposed in the intake air channel of the inlet tube.

Abstract: A tip shroud that includes a plurality of damping fins, each damping fin including a substantially non-radially-aligned surface that is configured to make contact with a tip shroud of a neighboring rotor blade. At least one damping fin may include a leading edge damping fin and at least one damping fin may include a trailing edge damping fin. The leading edge damping fin may be configured to correspond to the trailing edge damping fin.

Abstract: Gas turbine vanes of a gas turbine vane assembly have a reconfigured platform shape so as to reduce the ingestion of hot combustion gases into platform gaps between adjacent vane assemblies is disclosed. The vane platforms are configured so the joint between adjacent vanes is repositioned a sufficient distance away from the leading edge of the vane airfoil and the associated bow wave generated by the hot combustion gases passing over the airfoil leading edge.

Abstract: A turbine blade that may include a tip shroud, one or more cooling cavities formed within the tip shroud, and at least one discrete structural element defined within at least one of the cooling cavities. The discrete structural element may include an element that structurally connects a floor of the cooling cavity to a ceiling of the cooling cavity that does not originate from, terminate in, or connect to an interior wall of the cooling cavity or an outer edge of the tip shroud.

Abstract: The invention relates to a compressor, particularly a high pressure compressor, of a gas turbine, particularly of a gas turbine aircraft engine, having at least one rotating blade ring on the rotor side, and having at least one guide blade ring on the stator side, wherein the, or each, guide blade ring is formed of a plurality of guide blade segments, and wherein each guide blade segment is formed of a plurality of individual blades. According to the invention, adjacent individual blades (11, 12; 12, 13; 13, 14) are permanently connected to each other within each guide blade segment (10) of at least one guide blade ring on opposing surfaces positioned radially outward, whereas the same are not connected to each other on opposing surfaces positioned radially inward.

Abstract: A steam turbine rotor blade has a profile and a cover integrally formed on and at an end of the profile, the leading edge of the cover formed on the profile and the trailing edge of a cover formed on an adjacent preceding profile being in contact and connected with each other by the torsional return force produced during rotation. The cover formed on the profile is provided with a radially-formed stepped portion at the trailing edge, the stepped portion having a height large than the thickness of the cover.

Abstract: A turbine blade for use in high temperature applications includes an as-cast airfoil portion and an as-cast outer tip shroud portion and the outer tip shroud portion has at least one as-cast internal cooling circuit for cooling the outer tip shroud, and the at least one as-cast internal cooling circuit having a plurality of exits for discharging cooling air over exterior surfaces of the shroud. A process for forming a turbine blade comprises the steps of forming an as-cast turbine blade having an airfoil portion and a tip shroud and the forming step comprising forming at least one as-cast cooling circuit within the tip shroud.

Abstract: An arrangement between blade elements in a blade row in a turbine is described. Each blade element has at least one shroud element and a blade airfoil which abuts on, and is connected to, the shroud element, and essentially extends radially with regard to a principal axis of the blade row. When installed, the shroud element sides, which extend circumferentially, abut on the respectively adjacent shroud element of the respectively adjacent blade element, each forming an essentially radial gap. At least one blade element has a projection which projects into the shroud element of the abutting blade element and extends in the circumferential direction, and at least one blade element has a recess which accommodates such a projection. In the region of the projection or recess there is a stepped region of the radial gap, and the guiding of the radial gap in this stepped region is a labyrinth seal.

Abstract: A wind turbine is provided with turbine blades mounted for axial rotation about an axis. The blades are surrounded by a shroud to define an axial air passage. A conical ring is attached to the shroud and includes vanes for directing the airflow. Plates are attached to the shroud at a position radially outward from the shroud forming an air passage between the shroud and the plates. The plates have gaps between the adjacent plates so that air exiting the downstream opening of the shroud and air moving through the axial air passage between the shroud and the plates are mixed and a portion of the mixed air exits through the gaps.

Abstract: An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and for bridging the gap between two adjacent blades attached to the rotor disc. The annulus filler has a body portion which defines an airflow surface for air being drawn through the engine, and one or more hook portions which extend radially inwardly from the body portion. The hook portions are for connection to corresponding engagement portions on the radially outer face of the rotor disc. The or each hook portion is attached to the body portion by a joining arrangement in which a wedge part provided by one of the hook portion and the body portion is received in a complementary-shaped retention recess provided by the other of the hook portion and the body portion.

Abstract: A blade outer air seal segment assembly for a turbine in which adjacent segments form a curved metering and diffusion cooling slot for the discharge of film cooling air onto an inner surface of the segments. The segments include a first diffusion cavity connected to the backside surfaces of the segments through metering holes. The curved slot is connected to the first diffusion cavity. spend cooling air for cooling of the backside surfaces of the segments is metered into the first diffusion cavity and then discharged as film cooling air from the curved slot in a direction of rotation of the rotor blades to provide both sealing and cooling for the mate face of the segments.

Abstract: A turbine diaphragm includes an annulus of static blades and an outer diaphragm ring surrounding the annulus of static blades and welded to the outer platforms. Each static blade has an inner platform, an aerofoil, and an outer platform. The inner platforms serve the function of an inner diaphragm ring, thereby reducing material and manufacturing costs. Furthermore, confronting edges of the inner platforms have an interference fit with each other and the aerofoils are in a state of torsional stress between the inner and outer platforms. The latter two features improve the dynamic characteristics of the diaphragm.

Abstract: A fan blade for a gas-turbine engine which comprises a supporting structure (2) in fiber-composite material is enclosed by a sheet-metal enveloping structure (4) only in an area of the airfoil (3) such that the loads and stresses acting on the blade root (11), as well as the risk of delamination caused by the high bending load in the transition area between airfoil and blade root, are minimized.

Abstract: A coolable borescope boss includes cooling passages extending through the boss and oriented for spraying cooling air into a hole extending through the boss. Centerlines of the cooling passages may intersect the a hole axis of the hole. The cooling passages may be cylindrical or open slots disposed through the boss. The boss may be on an arcuate gas turbine engine shroud segment circumscribed about an axial centerline axis. The segment may be part of an annular segmented turbine shroud having cylindrical shroud first and second sections and a conical shroud midsection therebetween and the segment having cylindrical segment first and second sections and a conical segment midsection therebetween. A hole exit of the hole being flush with the conical segment midsection. A borescope plug tip having a spherical tip chamfer may be used to seal against a conical boss chamfer of the boss.

Abstract: A blade for a stator in a torque converter, including: a first blade segment connected to an inner circumferential section of the stator; at least one second blade segment, separately formed from the first blade segment, and connected to the inner circumferential section; and a third blade segment, separately formed from the first and second blade segments, and connected to the inner circumferential section. In some aspects, the first, second, and third blade segments include respective outer radial portions and the outer radial portions are fixedly connected. In some aspects, the first and second blade segments are in contact and the second and third blade segments are in contact. In some aspects, the first, second, and third blade segments include respective edges and the first and second blade segments are in contact along the respective edges and the second and third blade segments are in contact along the respective edges.

Abstract: A turbine blade is provided comprising: an airfoil including upper and lower ends; a root coupled to the airfoil lower end; a shroud coupled to the airfoil upper end; and at least one sealing rail extending radially outwardly from an upper surface of the shroud and extending generally along a circumferential length of the shroud. The sealing rail may comprise a mid-section, opposing end sections and at least one intermediate section located between the mid-section and one of the opposing end sections. An axial thickness of the rail may vary.

Abstract: A shroud of adjacent turbine moving blades has the primary contact face portion, which has opposing flat faces forming an acute angle from a turbine rotating direction and has the secondary contact face portion which has opposing flat faces forming an obtuse angle from the turbine rotating direction. In a process of increasing the rotor speed of a turbine, the secondary contact face portion shifts from a contacting state to a separated state, and thereafter, the primary contact face portion shifts from the separated state to the contacting state. According to such arrangement, vibration in a turbine higher speed range can be suppressed in addition to the suppression of the contact reaction force between coupling members of adjacent turbine moving blade from increasing too high, thereby improving the reliability of the turbine moving blades.

Abstract: A shroud segment to be arranged on a gas turbine blade is disclosed. The shroud segment includes a shroud segment surface and a stiffening structure that is raised relative to the shroud segment surface. The stiffening structure is cross-shaped at least in some areas.

Abstract: A bucket for use in the low-pressure section of a steam turbine engine is provided. The bucket has a vane length of at least about 52 inches. The bucket is comprised of a dovetail section disposed near an inner radial position of the bucket, a tip shroud disposed near an outer radial position of the bucket and a part span shroud disposed at an intermediate radial position. The intermediate radial position is disposed at a location between the inner and outer radial positions the intermediate radial positioning adapted to promote aerodynamic performance of the part span shroud. The bucket is comprised of a chromium steel.

Abstract: A ceramic matrix composite (CMC) component such as a ring seal segment (50, 50A, 50B, 50C, 50D) for a gas turbine engine (10), the component formed with a base plate (52) and a frame portion (54) that extends substantially normally from the base plate around its perimeter. A grid of intersecting CMC ribs (73) is formed on the base plate within the frame portion. The ribs have a height (H) that may be within 3 times the total thickness (B) of the base plate, including any rib base (39) bonded to the base plate, along at least most of the rib length. The grid of ribs may be assembled from an array of CMC cups (40) bonded to the base plate, to adjacent cups, and to the frame portion.

Abstract: A turbine rotor blade with a tip shroud that has a baffle seal with a knife edge to form a seal with a honeycomb seal of the shroud, where the tip shroud includes larger ribs that form separate compartment each with smaller ribs that form serpentine flow cooling circuits within the compartment to provide cooling for the tip shroud. Two hard faces each include an impingement cavity connected to one of the serpentine to provide impingement cooling to the backside wall of the hard face surface. The tip shroud periphery includes film cooling holes to discharge the spent cooling air from the serpentine circuits out from the tip periphery. A row of baffle seal cooling holes connect the serpentine circuit to the pressure side of the knife edge to provide cooling for the baffle seal.

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 steam turbine rotating blade for a low pressure section of a steam turbine engine is disclosed. The steam turbine rotating blade includes an airfoil portion. A root section is attached to one end of the airfoil portion. A dovetail section projects from the root section, wherein the dovetail section includes a skewed axial entry dovetail. A tip section is attached to the airfoil portion at an end opposite from the root section. A cover is integrally formed as part of the tip section. A part span shroud is attached at an intermediate section of the airfoil portion between the ends thereof. The blade includes an exit annulus area of about 47.7 ft2 (4.43 m2) or greater.

Abstract: A device for reducing inter-seal gap in gas turbines. Embodiments of a gas turbine with a first arcuate component adjacent to a second arcuate component; a first slot and a connected second slot on an end of the first arcuate component; a first seal disposed into the first slot and a first adjacent slot on the second arcuate component; a second seal disposed into the second slot and a second adjacent slot on the second arcuate component, leaving a gap between the first seal and the second seal; and a connector coupled to the first seal and the second seal and substantially covering the gap between the first seal and the second seal.

Abstract: A winglet is coupled with an end of a fan blade. The fan blade has an upper surface, a lower surface, a leading edge, and a trailing edge. The fan blade defines a chord and a maximum thickness. The winglet comprises a substantially vertical member that has a perimeter defined by a lower edge, an upper edge, and a rear edge, which meet at rounded corners. The rear edge of the vertical member has a length that is greater than the maximum thickness of the end of the fan blade. The vertical member has a length that is greater than the chord of the fan blade. The rear edge of the vertical member protrudes rearwardly relative to a vertical plane tangential to the trailing edge of the end of the fan blade. A mounting member may extend from the vertical member to couple the winglet with the fan blade.

Abstract: The present invention relates to a rotor for gas or steam turbines having a disk (1), an outer cover (2) and a plurality of blades (3). The disk (1) defines the portion of less diameter of the rotor and has an inner surface configured to be coupled on a shaft (100) of the turbine or connected to an axially adjacent disk (1?, 1?); an outer surface configured for housing a plurality of blades (3). The outer cover (2) defines the portion of greater diameter of the rotor. The blades (3) have a root (31) configured to be coupled on the disk (1) and a tip (32) opposite to the outer cover (2). Between these blades there is a plurality of blades (3) welded together at the tip (32) to form groups of blades (3a) and individual blades (3b) intercalated between groups of blades (3a).

Abstract: A turbine bucket that may include an airfoil having a tip shroud, the tip shroud having an edge; wherein the edge has a profile substantially in accordance with values of X and Y in a Cartesian coordinate system set forth in Table 1 at points 1-14, wherein X and Y represent distances that may be proportionally scaled by a common multiplier which, once scaled and connected, define the profile of the edge of the tip shroud.

Abstract: A spoke for a stator component for conducting a gas flow during operation includes at least two wall parts connecting a leading edge and a trailing edge of the spoke, and a middle portion between a first and a second end portion along a longitudinal extension. A first imaginary extension line from a first segment of the first wall part to a second segment of the second wall part and a second imaginary extension line from a second segment of the first wall part to a first segment of the second wall part are intersecting within the wall parts in the middle portion.

Abstract: The present invention relates to an impeller blade for turbomachine formed by molding, comprising a blade, at one end of which is provided a heel formed of a single piece with the blade, to which it is joined at the level of a connection area, the heel comprising a platform on which is provided at least one sealing plate, a first bath being provided in the platform, characterized in that a second bath is provided in the first bath, at the level of the connection area between the blade and the heel.

Abstract: Third stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z? set forth Table I wherein X and Y values are in inches and the Z? values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z? values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelope of +/?.0.040 inches in directions normal to the surface of the airfoil.

Abstract: A turbine bucket including a bucket airfoil having a hollow tip shroud, the hollow tip shroud having a hollow core having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, in inches, wherein the shape of the core is defined by the cloud of points listed which are distributed around each surface of the shroud, and the complete hollow portion of the tip shroud could be constructed by defining smooth sheet surfaces through the listed points.

Abstract: A stage for a gas turbine engine, having a plurality of circumferentially spaced apart radially extending aerofoils, includes a plurality of annulus fillers to bridge the spaces between adjacent aerofoils to define an inner wall of a flow annulus through the stage. Each annulus filler has opposing side faces which are spaced circumferentially from the adjacent blades and which correspond in profile therewith, and resilient seal strips each including a stiffener are mounted adjacent the opposing side faces of the annulus fillers to seal the gaps between the annulus fillers and the aerofoils. The stiffeners have three-dimensional curvature.

Abstract: A rotating blade for a steam turbine includes a root section and an airfoil section contiguous with the root section. The airfoil section is shaped to optimize aerodynamic performance while providing optimized flow distribution and minimal centrifugal and bending stresses. The blade also includes a tip section continuous with the airfoil section, and a cover formed as part of the tip section. The cover defines a radial seal that serves to minimize tip losses. The rotating blade is capable of running at operating speeds between 5626 and 11250 rotations per minute.

Abstract: A rotating blade for a steam turbine includes a root section and an airfoil section contiguous with the root section. The airfoil section is shaped to optimize aerodynamic performance while providing optimized flow distribution and minimal centrifugal and bending stresses. The blade also includes a tip section continuous with the airfoil section, and a cover formed as part of the tip section. The cover defines a radial seal that serves to minimize tip losses. The rotating blade is capable of running at operating speeds between 5626 and 11250 rotations per minute.

Abstract: A rotating blade for a steam turbine includes a root section and an airfoil section contiguous with the root section. The airfoil section is shaped to optimize aerodynamic performance while providing optimized flow distribution and minimal centrifugal and bending stresses. The blade also includes a tip section continuous with the airfoil section, and a cover formed as part of the tip section. The cover defines a radial seal that serves to minimize tip losses. The rotating blade is capable of running at operating speeds between 5626 and 11250 rotations per minute.

Abstract: A rotating blade for a steam turbine includes a root section and an airfoil section contiguous with the root section. The airfoil section is shaped to optimize aerodynamic performance while providing optimized flow distribution and minimal centrifugal and bending stresses. The blade also includes a tip section continuous with the airfoil section, and a cover formed as part of the tip section. The cover defines a radial seal that serves to minimize tip losses. The rotating blade is capable of running at operating speeds between 5626 and 11250 rotations per minute.

Abstract: A method of repairing a damaged notch fillet radius of a turbine blade shroud includes a replacement notch fillet radius and a hardface nugget. The damaged notch fillet radius is blended out and a hardface structure positioned proximate the damaged notch fillet radius is removed. A replacement notch fillet radius is formed with weld filler and the hardface nugget is welded to at least a portion of the replacement notch fillet radius.

Abstract: A winglet includes a vertical member and a mounting member. The mounting member is configured to facilitate the mounting of the winglet to the tip of a fan blade. The vertical member is configured to extend perpendicularly relative the tip of a fan blade. A cuff extends from the vertical member to substantially cover at least a portion of the interface between the end of a fan blade and the vertical member. Adding winglets to fan blades may improve the aerodynamics of the fan blades, and thereby increase efficiencies of a fan.

Abstract: In one embodiment, a turbine bucket includes: a tip shroud with a front edge and a following edge, the front edge and the following edge including a Z-Notch profile according to the Cartesian coordinate values of X, Y and Z set forth in Table I; wherein the coordinate values are dimensional values representing a distance from an origin of an internal coordinate system for the bucket; and wherein when the X and Y values are connected by smooth continuing arcs, the Z-Notch profile is defined. A turbine is provided.

Abstract: A tip-turbine engine comprises a fan-turbine rotor assembly that includes one or more turbine ring rotors. Each turbine ring is assembled from a multitude of turbine blade clusters. By forming the turbine blades in clusters, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine blade clusters to a diffuser surface includes axial installation and radial locking of each turbine blade cluster. This is accomplished by attachment lugs protruding from the underside of the arcuate base of the turbine blade clusters. Torque load surfaces are also integrated into the arcuate base.

Abstract: A tip turbine engine comprises a fan-turbine rotor assembly that includes one or more turbine ring rotors. Each turbine ring is assembled from a multitude of turbine blade clusters. Assembly of a multitude of turbine blade clusters to a diffuser includes axial installation and radial rotation. The clusters are axially installed, then rotated toward a radial stop in a direction which will maintain each cluster against the radial stop during operation of the fan-turbine rotor assembly. A multitude of turbine rotor ring stages may also be locked together to future increase the rigidity of the turbine.

Abstract: A turbomachine (1), in particular a turbine or compressor, includes a rotor (2) which has at least one moving blade row (4) with a plurality of moving blades (5), and a stator (3) which has at least one guide vane row (6) with a plurality of guide vanes (7), at least in one of the blade or vane rows (4, 6) all the blades or vanes (5, 7) each having a shroud plate (10). In order to simplify the maintenance of the turbo-machine (1), the shroud plates (10) are separate components with respect to the respective blade or vane (5, 7) and are mounted on the respective blade or vane (5, 7), shroud plates (10) adjacent in the circumferential direction (9) being coupled to one another for the transmission of tensile forces in the circumferential direction (9).

Abstract: A shroud includes a body portion 5B, a mount 7 positioned at a center of the body portion 5B and supporting rotary vane wheel driver 6, and multiple support beams 10 radially extending from the mount 7 and joining the mount 7 and the body portion 5B, where each of the support beams 10 becomes thicker from an upstream side of a flow direction of air toward a downstream side thereof, and an edge portion 10ti of each of the support beams 10 on the downstream side of the flow direction of the air discharged by the rotary vane wheel 8 is oriented in a direction parallel to a rotation axis of the rotary vane wheel 8, and the edge portion on the upstream side is oriented in a direction opposite to a rotation direction of the rotary vane wheel 8.

Abstract: A turbine exhaust thin strut includes an airfoil section having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

Abstract: A method of repairing a vane segment for a gas turbine engine includes removing an engine-run cooling baffle from the vane segment, forming a non-engine-run manufacturing detail that includes an inner platform, an outer platform, and an airfoil, attaching the engine-run cooling baffle to the non-engine-run manufacturing detail, and marking the non-engine-run manufacturing detail with a serial number associated with the vane segment from which the engine-run cooling baffle was removed.

Abstract: A system in a turbine engine for preventing wear on a tip shroud of a turbine blade that includes a pocket formed in a contact surface of the tip shroud and a plug that fits within the pocket and has a durable outer surface. The durable outer surface may include a cobalt-based hardfacing powder. The pocket may be machined out of the contact surface, and the plug may include a plug of predetermined size that fits snugly into the pocket. In some embodiments, the durable outer surface may substantially align with the contact surface after the plug is fitted into the pocket. In other embodiments, the durable outer surface may remain slightly raised from the contact surface after the plug has been fitted into the pocket.

Abstract: A turbine blade tip shroud. The tip shroud may include a platform, a number of Z-notched positioned within the platform, a number of seal rails positioned on the platform, and a number of cavities positioned within the platform and adjacent to seal rails and the Z-notches.