Abstract: A support bar for a steam turbine nozzle assembly is disclosed. In one embodiment, the support bar includes a hook-shaped portion for engaging a lip portion of a steam turbine diaphragm, wherein the steam turbine support bar is configured to non-affixedly join a steam turbine casing to the steam turbine diaphragm.

Abstract: A vane assembly for a gas turbine engine comprising an axial loading element disposed between a mounting element of the vane ring and a cooperating portion of the supporting structure, such as to generate a load force therebetween in an axial direction. The axial load force limits unwanted relative movement between the vane ring and the supporting structure during operation of the gas turbine engine.

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: The invention relates to a nozzle stage for a turbomachine compressor, the stage comprising two coaxial shrouds, a radially inner shroud and a radially outer shroud, and radial vanes extending between the shrouds and being connected via their ends to the shrouds, together with a support for abradable material that is mounted by crimping onto the upstream and downstream edges of the inner shroud, the inner shroud presenting openings in which the radially inner ends of the vanes are inserted and fastened. The radially inner ends of the vanes are plane and do not have any projecting tenons.

Abstract: A shell structure for a turbine engine that includes a plurality of diaphragms, wherein each diaphragm comprises: an annularly formed support structure that positions and secures a row of circumferentially spaced stator blades, and wherein the plurality of diaphragms are configured and axially stacked such that each diaphragm abuts the diaphragm that is positioned directly upstream from it and the diaphragm that is positioned directly downstream from it such that a first shell structure is formed; a second shell structure disposed outboard of the first shell structure; and an intermediate chamber defined between an outboard face of the first shell structure and an inboard face of the second shell structure; wherein: a downstream end and an upstream end of the first shell structure define the axial length of the first shell structure; one or more downstream radial ports are defined at the approximate axial position of the downstream end of the first shell structure, each downstream radial port fluidly connecti

Abstract: A support bar for a turbine diaphragm that facilitates reduced maintenance cycle time and cost is provided. In one aspect, the support bar is secured to the turbine diaphragm vertically rather than horizontally, allowing access to remove a lower diaphragm half without having to remove the rotor for maintenance.

Abstract: A radial annular flange of a rotor or stator element of a turbomachine including, at an inner/outer periphery, alternating solid portions and hollow portions, the solid portions including orifices for passing fastener bolts. The flange in the bottom of at least one hollow portion has a radius relative to the axis of the turbomachine that is less/greater than the radius of a circle that is tangential to the outsides/insides of the orifices for passing bolts through the solid portions.

Abstract: A transition duct used in a gas turbine engine to direct the hot gas flow from the combustor into the turbine section of the gas turbine engine. The transition duct includes a plurality of guide vane integral with the duct. The transition duct includes a circular shaped inlet end for connection to a can combustor and a rectangular and arched shaped outlet end for connection to a first stage turbine section. the guide vanes extend within the flow path between inner and outer projections each having a curved opening in the shape of the airfoil each airfoil includes inner and outer airfoil ends with retainer slots formed between the airfoil ends and the duct projections that form shear pin retainer slots. Shear pin retainers are secured within the slots to secure the guide vanes to the duct in a thermally uncoupled manner to reduce thermal stresses. The guide vanes can be made from a single crystal material for higher gas flow temperatures.

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 turbine shroud includes a ceramic shroud ring configured to surround a plurality of turbine rotor blades, a plurality of slots circumferentially distributed around the ceramic shroud ring, a forward metallic support ring, a plurality of tabs attached to a forward edge of the forward metallic support ring configured to engage a turbine support case, and a plurality of tabs attached to an aft edge of the forward metallic support ring received by the slots of the ceramic shroud ring. Only two axially extending radial surfaces of each of the tabs attached to the aft edge of the forward metallic support ring are configured to contact the slots of the ceramic shroud ring.

Abstract: A support arrangement for a diaphragm segment in a turbine casing that includes: 1) a support bar joined to a diaphragm segment; 2) a turbine casing comprising a vertical wall and a horizontal shoulder, wherein a portion of the horizontal shoulder underlies the support bar; 3) a cut out area defined by the vertical wall and an outer edge of the support bar; and 4) a shim interposed between the horizontal shoulder and the support bar. The cut out area may be a size that allows the shim to pass through.

Abstract: A compressor having a plurality of vane units each having at least one airfoil projecting from the base. Each base has a groove, so that when the vane units are disposed circumferentially adjacent, the grooves of the respective vane units are circumferentially aligned. A metal strip is disposed in the groove of a plurality of adjacent vane units to link the vane units forming a more rigid ring of vanes that are less susceptible to vane motion, e.g., caused by pressure fluctuations within the compressor of a gas turbine.

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 turbine module for a gas turbine engine includes at least an annular distributor and a turbine rotor inside a casing, where the annular distributor includes a plurality of elements in the form of a ring sector, of which a first part supports fixed blades positioned radially towards the turbine axis, and a second part forms a seal with the tips of the turbine rotor blades. The elements in the form of a ring sector are held inside the casing by attachment resources.

Abstract: A diaphragm assembly of a centrifugal compressor includes a return channel wall having a generally ring-like shape; a vane assembly having a plurality of vanes formed integrally with at least one ring-shaped track having a rail structure extending therefrom; and a diaphragm wall having a generally ring-like shape and at least one groove extending around a circumference thereof. The vane assembly is fixedly coupled to the return channel, thereby forming a return channel assembly. The return channel assembly is coupled to the diaphragm wall by sliding the rail structure into the at least one groove of the diaphragm wall.

Abstract: An example exit guide vane for a gas turbine engine is mounted adjacent to a diffuser case defining an air flow path. A thrust balance seal is attached to the diffuser and the exit guide vane is mounted adjacent the diffuser case for guiding air flow into the air flow path. The exit guide vane is mounted adjacent to the diffuser without interfering with the air flow path or restricting thermal expansion.

Abstract: A bladed stator sector for a turbo-engine reduces the occurrence of thermally-induced stress cracks in stator blades by increasing the flexibility of the sectors by using one or more cutouts. The stator sector includes at least one stator blade between inner and outer platforms and at least one flange on one or more of the platforms. Each flange has a first end portion fixed to one of the platforms and a second end portion that is not fixed to either of the platforms. The one or more cutouts may be located on the flange and may be non-opening.

Abstract: A rotary machine and a method of assembling a rotary machine having a casing extending at least partially around a rotor are provided. The method includes providing a diaphragm patch ring. The method also includes assembling a diaphragm assembly by configuring a diaphragm bore portion to receive the diaphragm patch ring and forming a diaphragm patch member sub-assembly by coupling the diaphragm patch ring to the configured diaphragm bore portion, such that the diaphragm bore portion defines at least one dowel passage and at least one bolt passage. The method further includes inserting at least one dowel generally radially into the at least one dowel passage, inserting at least one fastening bolt generally radially into the at least one bolt passage to secure the diaphragm patch ring to the diaphragm bore portion, and positioning the diaphragm assembly in a gap formed by the casing and the rotor.

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 mid-turbine frame connected to at least one mount of a gas turbine engine transfers a first load from a first bearing and a second load from a second bearing to the mount. The mid-turbine frame includes a load transfer unit, a torque box rotatably positioned within the load transfer unit, and a plurality of struts. The load transfer unit has a first locking element and combines the first load and the second load into a combined load. The torque box has a second locking element that is engagable with the first locking element of the load transfer unit. The plurality of struts are connected between the torque box and the mount, and transfer the combined load from the torque box to the mount. The first locking element and the second locking element are at least one of a rib or a groove.

Abstract: Aspects of the invention relate to a system for reducing relative movement between the outer shroud of a compressor diaphragm and the compressor shell of a turbine engine, thereby minimizing the wear and prolonging the life of such parts. Embodiments of the invention include a system for applying a preload on the outer shroud of a compressor diaphragm. The preload can be applied in the axial and/or radial directions. The preload can be applied at or proximate the joint between two shell segments, which is typically the location of the largest relative movement. In one embodiment, the preload can be achieved by providing one or more load applying members that operatively engage the outer shroud. A load applying member according to aspects of the invention includes a first portion, a second portion, and a biasing member operatively positioned therebetween. The biasing member can be a plurality of spring washers.

Abstract: A method and system for assembling a turbine is provided, wherein an annular nozzle carrier is positioned radially inwardly from a casing such that a cavity is defined between the nozzle carrier and the casing. The method and system also includes a flange that is extended from at least one of a leading edge of the annular casing and a leading edge of the nozzle carrier, and a seal ring that is extended between the nozzle carrier and the casing such that the seal ring seals the cavity, wherein the seal ring is positioned between the flange and at least one of the nozzle carrier and the casing.

Abstract: A turbomachine has a stator and a rotor, wherein the rotor has blades (21) and the stator has a housing (20) and stationary guide vanes (17), wherein the guide vanes (17) form guide vane rings (11, 12) that adjoin the housing (20) with radially outwardly positioned ends (18) and adjoin the rotor with radially inwardly positioned ends. The guide vane rings are spoke-centered with the aid of bearing journals or guide pins (24) allocated to the housing (20) and penetrating through the housing (20). The guide pins (24) extend at a slant relative to the radial direction and the axial direction of the turbomachine, wherein the ends (26) of the guide pins (24) reaching into the housing engage in forked elements (27) allocated to the radially outer ends (18) of the guide vane rings (11, 12).

Abstract: A variable vane arm has a hook portion comprising a radially inner leg connected to a radially outer leg by an arcuate connection, and an actuation lever extending from the hook portion. The hook portion and actuation lever are formed from a singular piece of material.

Abstract: A method of operating a gas turbine engine includes forming at least one stator ring passage within at least a portion of a radially inner surface of a casing. The method also includes providing at least one stator ring segment that is sized to be inserted into the at least one stator ring passage. The method further includes forming at least one radial passage within at least a portion of the at least one stator ring segment such that at least a portion of the at least one radial passage is adjacent to at least one substantially axial stator blade passage.

Abstract: Turbomachine with an annular combustion chamber including at its upstream end an annular chamber bottom, and attached at its downstream end by annular flanges to a radially inner casing and outer casing, wherein the upstream end of the chamber is connected to the inner casing or outer casing by elastically deformable bridges.

Abstract: Method and apparatus for assembling steam turbines are provided. The method of assembling a steam turbine includes providing an annular outer member, providing an annular inner member, coupling a plurality of airfoils to the inner member with a plurality of generally radial fastener assemblies such that the plurality of airfoils extend substantially radially outward from the inner member, and coupling each of the plurality of airfoils to the outer member.

Abstract: What is described is a turbine guide vane having a guide vane leaf and with a radially outer platform connected to the guide vane leaf and having a platform surface which faces radially away from the guide vane leaf and on which a connecting structure is provided for fastening the guide vane to a supporting structure which has side wall portions which project radially beyond the platform surface and delimit an inner cavity and on which is provided at least in portions a joining contour which can be inserted into a reception shape countercontoured within the supporting structure. At least one seal is provided between the connecting structure and the supporting structure.

Abstract: A stator assembly having a windage cover for structure adjacent to a cavity bounded by rotating elements in a rotary machine is disclosed. Various construction details are developed for damping vibrations in the windage cover as the windage cover bounds a cavity having swirling high velocity gases that are capable of transmitting acoustic energy and kinetic energy to adjacent structure. In one detailed embodiment, the windage cover in the uninstalled condition has diverging arms that are resiliently compressed during installation to exert a frictional force on the adjacent structure.

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: Embodiments for a compressor stator vane assembly in a gas turbine engine are disclosed. In an embodiment of the present invention a stator vane assembly is provided having a plurality of vanes each with an attachment and channels machined into the forward and aft walls of the attachment. A forward hook ring segment is pressfit into the channel in the forward wall of the attachment and an aft hook ring is pressfit into the channel in the aft wall of the attachment. The hook ring segments join a plurality of vanes together so as to provide a uniform engagement of mounting slots in the compressor case. Such an arrangement increases the contact area between the hook rings and the compressor case such that damping of individual vane vibrations are improved and operating stresses are reduced.

Abstract: A method of assembling a turbine engine is provided. The method includes providing a bushing including at least one retaining mechanism formed integrally therewith, coupling a shim to the bushing such that at least one retainer extending from the shim is received within the bushing retaining mechanism, and coupling the bushing and shim within the turbine engine to facilitate aligning a first engine component relative to a second engine component.

Abstract: A turbine stage includes a stator nozzle having a row of vanes mounted between inner and outer bands. The inner band terminates in an ovate ledge converging aft from the vanes with radially outer and inner convex surfaces joined at a convex apex. The ovate ledge reduces aerodynamic losses at the rotary seal with a row of following turbine rotor blades.

Abstract: A turbine nozzle segment includes a band having a plurality of tabs, an airfoil extending from the band and a support structure attached to the tabs. The support structure has a plurality of biasing structures.

Abstract: A turbine nozzle segment includes a first band, an airfoil extending from the first band and a support attached to the first band. The support may have a plurality of circumferentially spaced apart tabs.

Abstract: A turbine nozzle segment includes a band having a plurality of circumferentially spaced apart tabs and a single airfoil extending from the band.

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: 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: Systems and methods involving multiple torque paths of gas turbine engines are provided. In this regard, a representative spool assembly for a gas turbine engine, which incorporates a compressor, a turbine and a gear assembly, includes: a shaft operative to be driven by the turbine; a first spool segment operative to couple the shaft to the compressor; and a second spool segment operative to couple the shaft to the gear assembly. The first spool segment and the second spool segment are not coupled to each other.

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: Disclosed herein is a stator assembly for a steam turbine. The stator assembly includes a stacked stator section and a retention device. The stacked stator section has a plurality of adjacently disposed stator plates. The retention device retains the adjacent stator plates proximate to each other.

Abstract: The present invention provides a steam turbine that has upper and lower halves of diaphragm. The steam turbine of the present invention also provides an adjustable support bar attached to at least the upper half or the lower half of the diaphragm. The adjustable support bar of the present invention has a screw therein such that the adjustable support bar can raise or lower the upper half or the lower half of the diaphragm without removing each half of the diaphragm. Also provided are methods for adjusting and supporting a vertical position of the upper half and the lower half of the diaphragm at a horizontal split line in a steam turbine.

Abstract: A device (10) for suspending gas channel elements, in particular for suspending guide blades or guide blade segments or gas channel segments, on a housing of a gas turbines is provided. The device comprises first plate-shaped elements (11, 12, 13, 14) and second plate-shaped elements (15, 16, 17), whereby the first plate-shaped elements (11, 12, 13, 14) and the second plate-shaped elements (15, 16, 17) are connected together by web-like elements (18) which extend in an essentially perpendicular manner in relation to the first and second elements and form a meandering or crenelated profile.

Abstract: Aspects of the invention relate to a system for reducing relative movement between the outer shroud of a compressor diaphragm and the compressor shell of a turbine engine, thereby minimizing the wear and prolonging the life of such parts. Embodiments of the invention include a system for applying a preload on the outer shroud of a compressor diaphragm. The preload can be applied in the axial and/or radial directions. The preload can be applied at or proximate the joint between two shell segments, which is typically the location of the largest relative movement. In one embodiment, the preload can be achieved by providing one or more load applying members that operatively engage the outer shroud. A load applying member according to aspects of the invention includes a first portion, a second portion, and a biasing member operatively positioned therebetween. The biasing member can be a plurality of spring washers.

Abstract: A support arrangement for a diaphragm segment in a turbine casing that includes: 1) a support bar joined to a diaphragm segment; 2) a turbine casing comprising a vertical wall and a horizontal shoulder, wherein a portion of the horizontal shoulder underlies the support bar; 3) a cut out area defined by the vertical wall and an outer edge of the support bar; and 4) a shim interposed between the horizontal shoulder and the support bar. The cut out area may be a size that allows the shim to pass through.

Abstract: A compressor includes a stator having a plurality of vane sectors each with an outer shroud having a forward and a rearward guide vane extending there form, the vane sector being mounted in an annular slot of the casing, the guide vanes forming a gap between the tips and an inner shroud, and a spring member located on the outer shroud in the rearward portion to bias the rearward shroud in a radial direction, where a space is formed in the slot to allow for the outer shroud to move in the radial direction when the rearward guide vane tip makes contact with the inner shroud due to thermal growth of the stator components. This arrangement allows for the rearward guide vane tip to maintain contact with the inner shroud without inducing high compressive stresses in the stator components due to the thermal growth.

Abstract: Methods and apparatus for a machine casing component carrier configured to support a machine component such that the longitudinal axis of the machine component is adjustable with respect to a longitudinal axis of a rotatable member of the machine are provided. The carrier includes a support member configured to fixedly engage the machine component, an outwardly radially extending flange configured to engage a complementary receptacle formed in the turbine casing such that the weight of the carrier is supported at least partially by the receptacle, and a selectably adjustable shim member positionable within the receptacle configured to control an alignment of the longitudinal axis of the machine component with respect to the longitudinal axis of the rotatable member.

Abstract: A vane arrangement (1) of a turbo machine (4), in particular of a gas turbine, includes at least one vane carrier (2) attached to a housing (5) of a turbo machine (4), and several vanes (3) attached to the vane carrier (2) and circumferentially arranged side by side, wherein the attachment between the vane carrier (2) and respective vane (3) is adapted for being axially pluggable. In order to simplify dismounting of a single vane (3) at least one of the vanes (3) is provided with an extraction device (35) having at least one axially extending extraction through-hole (36). The respective extraction through hole (36) is provided with an inner thread (37), and the vane carrier (2) is provided with an abutment zone (38) axially opposing the extraction through hole (36).

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.