Abstract: A metallic annular connection structure between two parts for an aircraft turbomachine, with an arbitrary half-section including two primary branches and a base forming a first U opening up in the radial direction from a longitudinal axis, and two secondary branches forming a second U with one of the two primary branches opening up in the longitudinal direction. The primary and secondary branches and the base of the first U are made in a single piece.

Abstract: A turbine diaphragm assembly is described having an annulus of static blades, each static blade including at least an aerofoil and an outer platform; and an outer diaphragm ring or segments of a ring for holding the annulus of static blades; with confronting edges of the outer platforms and the ring are held by an interference fit when pushed in axial direction into contact with the interference fit designed to withstand the forces on the diaphragm during operation of the assembled turbine.

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: A gas turbine engine includes a compressor, a combustor section, and a turbine. The turbine includes an integrated case/stator segment that is comprised of a ceramic matrix composite material.

Abstract: A vane array adapted to be coupled to a vane carrier within a gas turbine engine is provided comprising: a plurality of elongated airfoils comprising at least a first airfoil and a second airfoil located adjacent to one another; a U-ring; first connector structure for coupling a radially inner end section of each of the first and second airfoils to the U-ring; second connector structure for coupling a radially outer end section of each of the first and second airfoils to the vane carrier; a platform extending between the first and second airfoils; and platform connector structure for coupling the platform to one of the U-ring and the vane carrier.

Abstract: A gas turbine having a guide vane assembly (2) and a securing ring (1) for axially locking the guide vane assembly in position that has a radially outer rim (1A) which is configured in a housing-side groove (3.1), a radially inner rim (1B) which is configured outside of the groove, and a slot (10) which extends from the radially outer rim to the radially inner rim, and a first flank having a radially inner rim section (12) and an undercut portion (11), the radially inner rim section forming an angle (?) of at least 50° with the radially inner rim.

Abstract: Various embodiments include an alignment pin for a turbomachine. In some embodiments, the alignment pin includes a hollowed head section for engaging a diaphragm slot in the turbomachine. In these embodiments, the alignment pin further includes an expandable sleeve section connected with the hollowed head, the expandable sleeve section for engaging a casing slot in the turbomachine.

Abstract: A part of a turbomachine distributor, including an outer platform, an inner platform, at least one blade interspaced circumferentially about a longitudinal axis of the part, radial ends of the at least one blade being respectively fixed to the inner platform and to the outer platform, and a fastening element extending from the outer platform, for fastening the part to a casing of the turbomachine. The fastening element includes, on ends thereof arranged on either side of the longitudinal axis, two separate fastening tabs for fastening the part to the casing, the cumulated sum of lengths of the two fastening tabs in relation to length of the fastening element according to a transverse axis of the part being between 25% and 35%.

Abstract: A turbomachine includes: a stator-side housing having: a plurality of stator-side guide vane supports fastened to the stator-side housing, stator-side guide vanes fastened to the stator-side guide vane supports, and axially spaced guide vane rings; and a rotor having a plurality of rotor-side moving blades. At least two guide vane supports are jointly fastened to and centered on a flange of the stator-side housing.

Abstract: A turbine flowpath apparatus for a gas turbine engine includes: a flowpath component exposed at least partially to a primary combustion gas flowpath of the engine, the flowpath component comprising low-ductility material; a metallic annular stationary structure surrounding the flowpath component, including a bearing surface which bears against the flowpath component, so as to restrain the flowpath component from axial movement in a first direction; and a spring element disposed between the flowpath component and the stationary structure which resilient urges the flowpath component in the first direction against the bearing surface.

Abstract: A composite annular shroud supported by a support assembly including at least two single piece full 360 degree rings and at least partially disposed within an innermost one of the rings. The shroud is biased against and in sealing engagement with an inner flange of the innermost ring. A three ring assembly includes the inner ring disposed radially inwardly of a middle ring disposed radially inwardly of an outer ring and the shroud at least partially disposed within the inner ring. At least three clocking pins extend radially inwardly from the middle ring through slots in the inner ring into notches in the shroud. The middle ring may be an aft end of a support ring fixedly connected to an engine backbone. Mounting pins may be press fitted into pin holes in the middle ring and extend radially outwardly from the middle ring through radial holes in the outer ring.

Abstract: The invention relates to a low pressure turbine (1) of a turbomachine comprising a nozzle (62) belonging to an upstream stage (20B) and a nozzle (162) belonging to a downstream stage (20C), the nozzle (62) forming segments (62a) having an external structure (66) comprising: a tab (76) bearing radially on a hook (79) fixed to the case, a tab (85) bearing radially on a reaming (87) in the case, the tabs (76, 85) delimiting an annular upstream cooling air circulation cavity (91), a contact surface (84) extending in the downstream direction from the tab (85) and lined with an abradable element (86) on the inside, the contact surface comprising a downstream end (92) bearing axially on the nozzle (162) and bearing radially on a stop (93) of the case, the contact surfaces (84) delimiting an annular downstream cooling air circulation cavity (94) communicating with cavity (91).

Abstract: According to one aspect of the invention, a turbine assembly includes a first static structure and a second static structure radially outward of the first static structure. The assembly also includes a support member placed in a recess of the second static structure, wherein the support member includes first and second curved surfaces to contact the first and second static structures, respectively, and wherein the support member includes a biasing structure to retain the support member in the recess.

Abstract: A gas turbine engine includes an engine casing structure and a retention block assembly. The engine casing structure includes a pocket which receives the retention block assembly. The retention block assembly includes a stop block and a pin that retains the stop block within the pocket. The stop block is loose relative to the pin.

Abstract: A turbine stage of a turbine engine, the stage including a rotor wheel mounted inside a sectorized ring carried by an outer casing, the outer casing including at least a circumferential rim housed in an annular cavity to attach a downstream end of the ring sector. A bottom wall of the annular cavity of the ring sector remains radially spaced apart from the circumferential rim of the outer casing to provide a thermally insulating space between them and includes a radial positioning mechanism acting on the circumferential rim.

Abstract: In an integrated strut and turbine vane nozzle (ISV) configuration, lug/slot or tag/groove arrangements may be provided between an interturbine duct (ITD) of the ISV and a vane ring of the ISV such that struts of the ITD and associated vanes are angularly positioned to form integrated strut-vane airfoils, reducing mismatch at the integration.

Abstract: A low leakage, integral fixed vane system for a gas turbine engine compression system which can accommodate the latest 3-D aerodynamic airfoil geometries and provide endwall ovalization control. A unitized construction wherein the vanes are integral with the case wall in the compression system.

Abstract: A support ring for a row of vanes in an engine section of a gas turbine engine includes an annular main body portion to which a row of vanes is affixed for providing structural support for the vanes in the engine section, and an aft hook extending from an aft side of the main body portion with reference to a direction of air flow through the engine section. The aft hook is coupled to an outer engine casing for structurally supporting the support ring in the engine section. The support ring does not include a forward hook having a flange that extends axially from a forward or aft side of the forward hook with reference to the direction of air flow through the engine section.

Abstract: A shroud for a turbine and a method of assembling is provided. The turbine includes a housing, a rotatable shaft and a bucket extending outward therefrom. The shroud includes an alignment member which is coupled to the housing, wherein the alignment member includes a first end, a second end and a body extending between the first and second ends. The second end includes an arcuate portion to facilitate fluid flow downstream from the bucket. The shroud further includes a seal coupled to the body to facilitate sealing a gap defined between the bucket and the body.

Abstract: A device such as a drum for positioning at least one guide blade row from a plurality of guide blade groups in a turbomachine, the device on the outer circumferential side including at least one flange for attachment to a housing section of the turbomachine and on the inner circumferential side including a plurality of uniformly distributed receptacles for accommodating holding elements of the guide blade groups and a plurality of recesses, the device having a depth-reduced inner circumferential section, relative to the accommodating grooves, between at least two adjoining receptacles, which extends in each case from the one receptacle to the other receptacle; a blade-device combination; a method for assembling such a blade-device combination; and a turbomachine.

Abstract: A gas turbine engine includes a compressor section and a nosecone assembly. The compressor section includes an inlet guide vane assembly including an inner shroud, an outer shroud, and an inlet guide vane extending from the inner shroud to the outer shroud. The nosecone assembly is attached to the inner shroud.

Abstract: A method for servicing a gas turbine engine includes disassembling a bearing compartment, providing access from a forward side of the gas turbine engine to a gearbox contained within said bearing compartment. The gas turbine engine provides a core flow path that extends from the forward side aftward in a core flow direction. The method includes servicing a component located within the bearing compartment. A method for servicing a gas turbine engine includes providing access from a forward side of a front center body assembly, and servicing a component located within a bearing compartment aft of the front center body assembly. The gas turbine engine includes a seal package located aft of a bearing package. A front wall is mounted to the front center body support and is removable from a front center body support to access at least one of the gearbox, the bearing package and the seal package.

Abstract: A method is provided for adjusting a position of a blade ring relative to a rotor in a gas turbine engine. An outer casing surrounds the blade ring and the blade ring surrounds the rotor. The method comprises: determining an amount of vertical movement needed to reposition the blade ring relative to the rotor so that the blade ring is at a desired position relative to the rotor; providing at least one torque pin assembly comprising a torque pin and a variable thickness defining structure; determining a change in the thickness of the variable thickness defining structure so as to effect the necessary vertical movement of the blade ring; changing the thickness of the variable thickness defining structure; and coupling the at least one torque pin assembly to the outer casing such that at least one torque pin engages the blade ring. A gas turbine engine is provided having structure for adjusting a position of a blade ring relative to a rotor.

Abstract: A flowpath assembly for a gas turbine engine includes a plurality of flowpath insert ducts arranged in a cascade configuration. Each flowpath duct includes a radially inward wall, a radially outward wall, a first side wall, and a second side wall. A flowpath volume is defined between the inward, outward, first side and second side walls. The first side wall of a given one of the plurality of flowpath insert ducts is positioned adjacent to the second sidewall of an adjacent one of the plurality of flowpath insert ducts in the cascade configuration.

Abstract: A system for supporting a turbine nozzle includes an inner barrel having a forward end, an aft end and an outer surface that extends between the forward end and the aft end. A first fitting that extends through the outer surface is defined within the inner barrel. The system further includes a nozzle support ring that defines a second fitting that is complementary to the first fitting defined within the inner barrel.

Abstract: A stationary vane assembly for a turbine engine including an inner casing and at least two angular sectors forming a high-pressure guide vane assembly, each angular sector including a fastening tab for fastening the angular sector on the casing. The stationary vane assembly including a ring of abradable material fixed on the casing, on the side of a mobile vane assembly using a plurality of screw-nut assemblies, the stationary vane assembly also including radial retaining pins for the angular sectors introduced into first bores formed in the fastening tabs and in the mounting clip, the bores having axes substantially parallel to the longitudinal axis, the mounting clip being fixed on the casing by the same screw-nut assemblies as those fixing the ring of abradable material support on the casing.

Abstract: An assembling of a guide vane assembly of a turbomachine turbine, formed by an annular row of stationary flow-stabilizing vanes. An outer edge of the guide vane assembly is axially bearing on a line of an external casing of the turbine and an inner edge of the guide vane assembly is in axial sliding connection with the line of the internal casing of the turbine, the axial sliding connection allowing the inner edge to be free along the motor axis with the axial stop being achieved by the axial bearing of the outer edge of the vane.

Abstract: An alignment member for a turbine diaphragm segment is disclosed. The alignment member is configured to span radially across a portion of the turbine diaphragm segment and an adjacent turbine casing segment. The alignment member can include: a main body having a first aperture for aligning with a first corresponding aperture in one of the turbine diaphragm segment or the turbine casing segment; and a flange extending from the main body, the flange including a second aperture for aligning with a portion of the other of the turbine diaphragm segment or the turbine casing segment, the alignment member for adjusting a position of the turbine diaphragm segment relative to the adjacent turbine casing segment.

Abstract: Systems for increasing the efficiency of a turbine and an overall power plant system are disclosed. In one embodiment, a turbine includes: an outer shell including a set of grooves configured to complement components of a wheel and diaphragm steam path section; a drum rotor disposed within the outer shell; a set of shell converts connected to the outer shell via the set of grooves, the set of shell converts configured to complement components of the drum rotor; and a working fluid passage substantially defined by the drum rotor and the set of shell converts.

Abstract: An assembly for a turbine engine includes a stator vane arrangement and an anti-rotation lug that is rotatably connected to a turbine engine case. The stator vane arrangement includes a platform, an airfoil and an anti-rotation slot. The platform extends circumferentially around an axial centerline and is engaged with the case. The airfoil extends radially from the platform and is arranged circumferentially around the centerline. The slot extends radially into the platform, and is mated with the lug. The lug is configured with a substantially equilateral polygonal geometry.

Abstract: A fixed vane section for a gas turbine engine includes an anti-rotation slot that receives a pin for maintaining a desired position while providing for movement encountered during operation. The example anti-rotation slot includes a compound radius on inner surfaces to reduce stresses encountered during operation.

Abstract: The invention relates to a turbine (1), in particular of an exhaust gas turbocharger, having a turbine rotor (4), which is rotatably mounted in a housing (2), with which at least one radial inlet channel (9) for a guide apparatus (7) forming a medium which drives the turbine rotor (4) is associated, wherein said guide apparatus (7) has multiple guide vane bearing rings (10), which radially enclose said turbine rotor (4) and have guide vanes (8) which lie in said inlet channel (9), and a guide vane cover ring (12), and wherein said inlet channel (9) is axially delimited by said guide vane bearing ring (10) and said guide vane cover ring (12) and said guide apparatus (7) is mounted in the housing (2) so it is axially and/or radially movable for material relaxation. Furthermore, the invention relates to an exhaust gas turbocharger, in particular for a motor vehicle.

Abstract: A centerline suspension arrangement (42) for a turbine (40). A turbine inner casing (44) is supported within an outer casing (46) via a support member (60) that includes an inner portion (62) contacting the inner casing and an outer portion (66) extending into a slot (68) formed in the outer casing. The support member is slid into an axially oriented slot (64) formed in the inner casing and is body bound therein with respect to radial movements, with the support member and the inner casing slot including opposed vertical support surfaces (82, 90) and a pair of oppositely facing opposed horizontal support surfaces (80, 88 and 86, 92). Thus, dead weight and operating loads from the inner casing are reacted through the support member and into the outer casing without the necessity for any bolting or other fastener attachment in the design load path between the support member and the inner casing.

Abstract: A vane structure for a gas turbine engine includes a multiple of CMC airfoil sections integrated between a CMC outer ring and a metal alloy inner ring.

Abstract: A rectifier stage of an axial turbine engine compressor is placed directly downstream of the input blower of a turbo-reactor or turboshaft engine compressor. The blade roots of the rectifier stage are housed inside the inner shroud by insertion into respective slots. The blade roots include at least one opening protruding from the slot of the shroud, so as to receive a spiral ring having at least two loops so as to prevent the blade roots from escaping from the respective slots of the inner shroud, and so as to form a connection between the blade roots.

Abstract: A method for suspending a fan case and a fan case assembly in which a fan case is suspended are disclosed herein. The fan case assembly includes an inner ring encircling an axis. The fan case assembly also includes a first outer ring encircling the axis and having an annular flange. The fan case assembly also includes a plurality of struts each extending radially outward from an inner end engaged with the inner ring to an outer end engaged with the first outer ring. The fan case assembly also includes a second outer ring abutting the first outer ring along the axis. The fan case assembly also includes a plurality of leaves each fixed to the second outer ring and extending along the axis. The leaves are slid over an outer surface of the first outer ring to engage the first and second outer rings together.

Abstract: Disclosed are a band structure and a micro gas turbine having the same. An insert wall and a nozzle ring casing are respectively surrounded in part by a first band structure of a heat resistant material and a second band structure of a material that is identical or similar to the material of the first band structure to prevent thermal deformation of the insert wall and of the nozzle ring casing and a nozzle vane so as to maintain constant gaps between a blade tip of a turbine wheel and the insert wall and between a leading edge of the turbine wheel and the nozzle vane, thereby preventing reduction in both the power output of the turbine wheel even after a prolonged drive period and the operation efficiency of the micro gas turbine.

Abstract: Various embodiments include a turbomachine diaphragm ring. In various particular embodiments, a turbomachine diaphragm ring includes: a packing slot sized to house a dovetail section of a turbomachine packing, the packing slot extending circumferentially about a rotational axis of the turbomachine; a key slot connected with the packing slot sized to house a portion of a key member, the key slot extending at least one of radially or axially from the packing slot; and a retaining slot connected with the key slot and extending substantially circumferentially from the key slot, the retaining slot sized to house a retaining member for retaining the key member.

Abstract: The present application relates to the stator blades of an axial turbomachine intended to be fitted on a ferrule in an annular row of identical blades. Each blade includes a platform with opposed lateral edges and a means of attachment to the ferrule. The contour of the platform has, at each of the lateral edges, an angular profile designed to mate with the contiguous edge of the platform of an adjacent blade. This feature enables the angular position or pitch of the blade to be set. The present application also relates to a stator comprising the blade row. Mechanical clearances J1, J2 and J3 and the means of clamping cause an average angular orientation error. The blades are made with a compensatory angle to offset the angular orientation error.

Abstract: A radial annular flange including in inner or outer periphery alternating solid portions including orifices for passing fastener bolts, and hollow portions having bottoms that are substantially flat. The bottom of at least one keying hollow portion is situated radially inside, or outside, respectively, a circle centered on the axis of the flange and externally, or respectively internally, tangential to the orifices. Two hollow portions are situated on either side of the keying hollow portion having bottoms of concave curved shapes situated radially on the outside, or respectively on the inside, relative to the flat bottoms of the other hollow portions.

Abstract: A fan shroud with modular vane members for a cooling system. A plurality of modular vane set members are positioned around the inner surface of the fan shroud ring, each of the modular vane set members having a plurality of vane members. The modularity provides flexibility and versatility for the fan shroud and corresponding efficiencies in costs and manufacturing.

Abstract: A guide disc segment for a horizontally split turbomachine housing is provided. The guide disc segment includes a plurality of guide blades and an outer ring segment. The guide blades are fixed to the outer ring segment along an inner circumference. The outer ring segment can be rolled into or out of a guide blade carrier of the turbomachine housing. The outer ring segment has, along an outer circumference, a toothing into which a drive device engages. A tangential force can be applied to the outer ring segment by the toothing such that the guide disc segment can be driven during the rolling into or rolling out of the outer ring segment.

Abstract: A turbine nozzle attachment assembly includes an outer turbine component (a shroud or a turbine shell) formed with a circumferential groove open in a forward-facing axial direction; a nozzle segment including a vane extending between inner and outer bands, the outer band provided with an upstanding annular hook formed with a hook element extending in an aft-facing axial direction and received in the circumferential groove. The upstanding annular hook and hook element are formed with a circumferentially-oriented slot. An anti-rotation block is located in the circumferentially-oriented slot, and an anti-tipping plate having a circumferential width greater than a corresponding circumferential width of the circumferentially-oriented slot substantially covers a forward face of the anti-rotation block. The anti-rotation block and the anti-tipping plate are fastened directly to the outer turbine component.

Abstract: A shroud for turbine engines. The shroud has an integrated anti-rotation device that prevents circumferential movement of the shroud during normal engine operation, and which allows for circumferential installation in split annular case designs. Since the anti-rotation device is an integral part of the shroud and/or annular split turbine case, no additional parts are necessary for assembly or disassembly. Moreover, existing annular split turbine cases can be reworked to accept the anti-rotation device and yet still be backwards compatible with original shroud designs.

Abstract: A stator blade carrier, particularly for a gas turbine, is provided. The stator blade carrier includes a number of axial segments and is intended to attain a particularly high degree of operational reliability and long service life. To this end, two neighboring axial segments are connected to a number of tie rods, each enclosed by a support tube, wherein a spherical disk is arranged on at least one end of the respective support tube and mounted in a conical socket supported on the respective axial segment.

Abstract: A stator vane assembly includes: inner and outer vane supports, and vanes extending radially between the supports. The supports have openings for receiving the ends of the vanes, and each vane is connected to the supports by a vane boot. Each vane boot has: a rim portion shaped to locate the boot within the corresponding opening in the vane support, the rim portion engaging with the inner surface defining the opening, an abutting portion for abutting against the vane support in the region surrounding the opening, and a vane pocket for accommodating the end of the vane. The vane pockets of the vane boots are shaped so as to position the vane with a predetermined stagger angle.

Abstract: A fluid flow machine has a main flow path which is confined by a hub (3) and a casing (2) and in which at least one row of variable stator vanes (1) is arranged. The stator vanes (1) are rotatably borne around a rotary axis 4. On at least one of the hub (3) and the casing (2), at least one arrangement with at least two stator vanes (1) connected to a common rotary base (5) is provided, such that the at least two stator vanes (1) are rotatable around the rotary axis (4) when this multi-vane variable stator unit is varied.

Abstract: A turbomachine diaphragm includes a sealing section having a first end portion that extends to a second end portion through an intermediate portion. At least one rail member includes a first end section that extends from the first end portion of the sealing section to a second end section through an intermediate section having an inner surface section and an outer surface section. The second end section includes a machined surface having a repair coupon mounting element. A repair coupon is mounted at the repair coupon mounting element and operatively connected to the at least one rail member. A method of repairing a turbomachine diaphragm is also disclosed herein.

Abstract: An adjustable support apparatus for a steam turbine nozzle assembly is disclosed. In one embodiment, a steam turbine apparatus includes: a diaphragm segment having a horizontal joint surface and an angled ledge below the horizontal joint surface, the angled ledge configured to receive a complementary angled portion of a wedge member.

Abstract: A method for preventing cracking of a turbine engine case includes the steps of disposing at least two rails upon an exterior surface of a turbine engine case; and securing a first rail to a first means for attaching at least one fan exit guide vane to the turbine engine case and securing a second rail to a second means for attaching the at least one fan exit guide vane to the turbine engine case.