Abstract: A strut cover for a gas turbine includes: a cylindrical sheet metal member having a hollow portion; and a flare member that is connected to one end of the cylindrical sheet metal member in an axial direction of the cylindrical sheet metal member and includes a curved portion having an outer surface such that a distance from a center axis of the cylindrical sheet metal member to the outer surface increases with increasing a distance from the cylindrical sheet metal member in the axial direction. The flare member has a thickness larger than a minimum thickness of the cylindrical sheet metal member at least in the curved portion.

Abstract: A casing for a bearing of a gas turbine engine includes a shaft extending along an axial direction. The casing includes an attachment feature at a radially outermost portion of the casing. The attachment feature is configured to be coupled to a static frame of the gas turbine engine. The casing further includes a plurality of support arms extend from the attachment feature to a radially innermost portion of the casing. At least one support arm of the plurality of support arms defines an internal cavity. Further, the radially innermost portion of the casing is configured to be coupled to an outer race of the bearing. The casing additionally includes a reinforcing member housed at least partially within the internal cavity of at least one support arm. Moreover, the reinforcing member includes a shape memory alloy material.

Abstract: An integrated strut and turbine vane nozzle (ISV) has inner and outer annular duct walls defining an annular flow passage therebetween. Circumferentially spaced-apart struts extend radially across the flow passage. Circumferentially spaced-apart vanes also extend radially across the flow passage and define a plurality of inter-vane passages. Each of the struts is integrated to an associated one of the vanes to form therewith an integrated strut-vane airfoil. The inter-vane passages on either side of the integrated strut-vane airfoil may be adjusted for aerodynamic considerations. The vanes may be made separately from the struts and manufactured such as to cater for potential misalignments between the parts.

Abstract: A gas turbine exhaust casing includes a tubular casing wall, a bearing box housed in the casing wall, a diffuser portion forming an annular exhaust gas flow passage between the casing wall and the bearing box, a plurality of struts disposed at intervals in a circumferential direction of the casing wall, and coupling the casing wall and the bearing box, and a plurality of fastening bolts disposed on the casing wall. The casing wall includes an upper half casing forming an upper half of the casing wall and a lower half casing forming a lower half of the casing wall. The plurality of fastening bolts fasten the upper half casing and the lower half casing. The plurality of struts include a penetrated strut which has an end penetrated by at least one fastening bolt of the plurality of fastening bolts.

Abstract: A shrouded conduit is provided for arranging, for example, in a gas path of a turbine engine. The shrouded conduit includes a tubular shroud extending longitudinally along a centerline. The shrouded conduit also includes a fluid conduit extending longitudinally in the shroud. A first portion of the fluid conduit is connected laterally to and may be formed integral with a first portion of the shroud.

Abstract: A turbofan engine comprising a fan shaft configured to rotate about an axis of the engine. A fan drive gear system is configured to drive the fan shaft. A first spool comprises a high pressure turbine and a high pressure compressor. A second spool comprises a lower pressure turbine, a lower pressure compressor, and a shaft coupling the lower pressure turbine to the intermediate pressure compressor. The engine has a plurality of main bearings. The lower pressure compressor has a plurality of disks and a forward hub mounted to a forwardmost disk.

Abstract: A gas turbine engine includes a low pressure compressor and a low pressure turbine, with a low pressure shaft coupled to the low pressure turbine through a turbine extension and coupled to the low pressure compressor through a compressor extension. A forward bearing assembly supports the low pressure shaft within a compressor section and at a location aft of the compressor extension and an aft LP bearing assembly supports the low pressure shaft within a turbine section at a location aft of the turbine extension.

Abstract: The present disclosure provides an assembly for a gas turbine engine. The assembly may comprise a tierod, a bearing mounting ring, and a joint coupling the tierod to the bearing mounting ring. The joint may be configured to increase a volume of a bearing compartment on an inner surface of the bearing mounting ring. A coefficient of thermal expansion of the bearing mounting ring may be substantially the same as the coefficient of thermal expansion of the tierod.

Abstract: A turbine for a turbine engine is disclosed. The turbine includes a casing and a turbine nozzle stage made of a ceramic matrix composite material and including annular sectors forming a ring presenting an inner shroud and an outer shroud. Each annular sector has an inner platform forming part the inner shroud and an outer platform forming part of the outer shroud, and an airfoil extending between the outer platform and the inner platform and secured thereto. The airfoil presents a hollow profile defining an inside housing extending between the inner platform and the outer platform, and the inner and outer platforms each presenting an orifice communicating with the inside housing of the airfoil. Each annular sector includes a strut passing through the orifices in the platforms and through the inside housing of the airfoil. The strut is fastened to the casing and is connected with the annular sector.

Abstract: In a fan case having an annular outer wall with a plurality of fan case bolt holes there through, bushings are inserted into the fan case bolt hole and are dimensioned to define an annular gap between the bolt hole inner surface and the bushing outer surface. An adhesive material disposed within each annular gap between the bushing and the corresponding fan case bolt hole, with the adhesive material forming a liquid shim separating the bushing outer surface from the bolt hole inner surface.

Abstract: The invention relates to a module for a gas turbine comprising a rotationally symmetrical outer casing of a first material having a first linear thermal expansion coefficient, a rotationally symmetrical component for guiding hot gas of a second material having a linear thermal expansion coefficient which is lower than the first coefficient, at least one annular structure arranged radially within the component, and at least three struts having a radially inner end secured on the outer casing and a radially outer end secured on the annular structure. The component also comprises at least one first fixing which is free in radial direction and fixed in axial direction and arranged between the component and the outer casing and/or the annular structure, as well as at least three second fixings having an elastic effect in radial, axial and/or circumferential direction and being arranged between the component and the strut and/or the annular structure.

Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly defining a flow path through a gas turbine engine, as well as axial and radial directions that are orthogonal to one another and a circumferential direction extending about the axial direction, comprises a nozzle airfoil having a first end opposite a second end and a wall defining a flow path boundary. The wall has an opening therein through which the second end of the nozzle airfoil protrudes such that the second end extends outside of the flow path. The flow path assembly further comprises a cap extending over the second end of the nozzle airfoil and an attachment member extending through the second end and the cap to attach the second end to the cap. Other embodiments of a flow path assembly having nozzle airfoils decoupled from the flow path boundary also are provided.

Abstract: A centrifugal compressor includes a casing body (11) configured to rotatably support a rotation shaft (2) and an impeller (3) fixed to the rotation shaft around an axis (O), the casing body in which an intake volute (B1) which has a ring shape centered on the axis and through which a processing gas (G) is caused to flow in a direction of the axis and is introduced into a flow channel of the impeller, and a discharge volute which has a ring shape centered on the axis and through which the processing gas is discharged from the flow channel are formed; and a plurality of intake nozzles (16) which communicate with the intake volute and are able to cause the processing gas to flow into the intake volute from the outside and are provided at intervals in a circumferential direction around the rotation shaft.

Abstract: An inlet section for a gas turbine engine according to an example of the present disclosure includes, among other things, an outer case extending about a rotor that is rotatable about an engine axis. The rotor carries a plurality of airfoils. A plurality of guide vanes are operable to guide flow from an engine inlet toward the plurality of airfoils relative to the engine axis. A plurality of spokes are mechanically attached to the outer case. Each of the plurality of spokes is received in a respective one of the plurality of guide vanes, and at least one of the plurality of spokes define a fluid passage in flow communication with a bearing assembly.

Abstract: A fan assembly attaches to and may be used with an existing fan of a storage container. The fan assembly includes an exhaust fan, a mounting assembly for operatively mounting the exhaust fan to the existing fan of the storage container, and a sealing member operatively positioned between the exhaust fan and the existing fan to provide a seal to direct movement of air streams created, in part, by the exhaust fan. During operation of the exhaust fan, the exhaust fan pulls contaminated air and airborne matter from within the storage container through the existing fan and an existing duct in order to exhaust the contaminated air and airborne matter from the storage container.

Abstract: A rotor assembly for an engine, comprising: a rotor, supported on bearings for axial rotation, a rotor portion forming a compression passage extending outwards from the axis, gases entering the rotor through inlets at the axis and flowing outwards through the compression passage; a combustion chamber supported within the compression passage near the maximum radius of the rotor having a closed outer end and combustion chamber gases inlets through which gases enter the combustion chamber, each combustion chamber having a fuel inlet, and; one or more expansion passages in fluidic connection with and extending radially inwards from the combustion chamber within a compression passage and fluidically connecting at or near the rotor axis to a combustion gas outlet tube that extends along the rotor axis, combustion gases created by combustion of fuel with inlet gases within the combustion chamber expanding as they flow inwards through the expansion passage.

Abstract: A turbine nozzle apparatus includes: a vane extending between inner and outer bands, the interior of the vane being open and communicating with an aperture in the outer band, wherein the vane and the bands are part of a monolithic whole of low-ductility material; a metallic baffle inside the vane, the baffle having upper and lower ends and a peripheral wall including a plurality of impingement holes defining an interior space, closed off by an end wall at the lower end; and a metallic retainer having a body with a shape generally matching the shape of the aperture, the body bearing against the upper end of the impingement baffle and being connected to the outer band by a plurality of mechanical fasteners.

Abstract: A centrifugal compressor for a chiller includes a casing, an inlet guide vane, an impeller downstream of the inlet guide vane, a motor and a diffuser. The casing has inlet and outlet portions with the inlet guide vane disposed in the inlet portion. The impeller is rotatable about a rotation axis defining an axial direction, and the impeller is adjustably mounted within the casing along the axial direction between at least a first flow rate position and a second flow rate position. The motor rotates the impeller. The diffuser is disposed in the outlet portion downstream from the impeller with a outlet port of the outlet portion being disposed between the impeller and the diffuser.

Abstract: A coupling support member including a pair of divided pieces is placed in a coupling part between a vane base end portion of a guide vane and an attachment flange, and the pair of divided pieces are joined to the vane base end portion from both the sides in the vane thickness direction. Linear protrusions are respectively formed on both the sides of the vane base end portion. Grooves engaged with the linear protrusions formed in the vane base end portion are respectively formed in the pair of divided pieces of the coupling support member. Side edges that are located on the vane center side of the pair of divided pieces and extend along the chord direction are formed so as to protrude toward the vane center, and the respective tip ends of the side edges are chamfered.

Abstract: A method includes (a) depositing a layer of a powder material on a work stage, the layer having a thickness, (b) solidifying a portion of the layer based upon data that defines an insert with a body that is shaped to fit into a cavity in a gas turbine engine component, and (c) lowering the work stage by the thickness. Steps (a)-(c) can then be repeated until the insert is complete. The insert can then be removed from the work stage. An insert formed by the above process is also disclosed.

Abstract: A fixture for positioning an object relative to a beam, wherein the beam includes a web, is disclosed. The fixture includes a first portion including a first positioning face, a first contact face, and a first clamping face. Each of the first positioning face, the first contact face, and the first clamping face is movable in a first working direction. The fixture also includes a second portion including a second positioning face, a second contact face, and a second clamping face. Each of the second positioning face, the second contact face, and the second clamping face is movable in a second working direction opposite to the first working direction. When the fixture is installed on the beam, the first contact face and the second contact face abut each other, and the first clamping face and the second clamping face engage the web.

Abstract: An interface within a gas turbine engine includes a sealing surface defined by a portion of a vane platform. A seal is in contact with said sealing surface. A barrier is transverse to the sealing surface.

Abstract: A guide vane includes an airfoil with a first end and a second end. A platform is disposed at a first end of the airfoil, and a K-gusset is disposed on the platform opposite the airfoil. The K-gusset includes four bosses and ribs extending between the bosses in a “K” configuration.

Abstract: Miniature (mesoscale) axial-flow pumps including an inlet guide, a stator spaced apart from the inlet guide, and a rotor rotatably disposed between the inlet guide and the stator.

Abstract: A turbine section of a gas turbine engine includes a first turbine supported for rotation about an axis, a second turbine spaced axially aft of the for first turbine section for rotation about the axis, and a mid-turbine frame disposed between the first turbine and the second turbine defining a passage between the first turbine and the second turbine. A first case surrounds the first turbine and a second case surrounding the second turbine and attached to the first case. The mid-turbine frame is disposed between the first turbine section and the second turbine section and includes at least one support structure extending through an interface between the first turbine case and the second turbine case.

Abstract: An assembly for a gas turbine engine includes a strut and a heat shield. The heat shield is disposed adjacent the strut and the heat shield and is adapted to contain a cooling air flow that passes along first cavity between the heat shield and the strut.

Abstract: A gas turbine engine has a first particle separator stage including a surface for impacting air at outer periphery of an air flow passage, capturing impacted particles at the outer periphery, and routing captured particles towards a second particle separator stage. Air inward of the first particle separator stage passes towards a core of the engine. Cleaner air upstream of the second particle separator stage is utilized for an air function at a location other than the core engine. A particle discharge is disposed downstream of said second particle separator stage.

Abstract: A wave soldering tank includes a soldering tank body for housing molten solder and a solder feed chamber disposed within the soldering tank body. An axial-flow, multiple-blade screw-type pump is disposed so as to draw molten solder into the solder feed chamber through an inlet and discharge the molten solder through an outlet. In a preferred embodiment, the pump includes a rotatable hub and a plurality of helical blades secured to the hub at equal intervals in the circumferential direction of the hub, each of the blades overlapping an adjoining one of the blades when the blades are viewed in the axial direction of the impeller.

Abstract: The invention relates to a mid-frame (10) for a gas turbine, having at least one outer casing element (24), having at least one hub element (26) arranged on the inside of the outer casing element (24) in the radial direction, having a least one strut (42) by means of which the outer casing element (24) is connected to the hub element (26), and having at least one fairing element (46) that delimits at least partially a duct (44) at least in the radial direction, through which a gas can flow, and is constructed separately from the casing element (46), said fairing element having a passage opening (48), through which the strut (42) passes, for at least partial cladding of the strut on the outer peripheral side, wherein the fairing element (46) is coupled exclusively to the hub element (26), at least in the radial direction.

Abstract: A mid-turbine frame for a gas turbine engine includes an outer frame case and an inner frame case. At least one spoke connects the outer frame case to the inner frame case. The spoke includes a cooling airflow passage that extends in a radial direction and an axial direction, an elongated cylindrical portion, and a flange.

Abstract: An integrated strut and turbine vane nozzle (ISV) comprising: inner and outer duct walls defining a flow passage therebetween, an array of circumferentially spaced-apart struts extending radially across the flow passage, and an array of circumferentially spaced-apart vanes extending radially across the flow passage. At least one of the struts is aligned in the circumferential direction with an associated one of the vanes and forms therewith an integrated strut-vane airfoil. The adjacent vanes on opposed sides of the integrated strut-vane airfoil have uneven axial chords relative to the other vanes.

Abstract: A coupling support member including a pair of divided pieces is placed in a coupling part between a vane proximal end portion of a guide vane and an attachment flange, and the pair of divided pieces are joined to the vane proximal end portion from both the sides in the vane thickness direction. A groove is formed in one end portion joint surface of the coupling support member, a linear protrusion is formed on the other end portion joint surface, the vane proximal end portion is formed into a concavo-convex shape, a linear protrusion that is engaged with the groove which is formed in the end portion joint surface is formed on a joint surface to the one end portion joint surface, a groove that is engaged with the linear protrusion formed on the end portion joint surface is formed in the joint surface to the other end portion joint surface.

Abstract: Disclosed are a casing arrangement and a method to reduce vibrations in a gas turbine casing. The casing arrangement includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A damping blanket damps the vibrations and is coupled to a surface of the inner flow path via a constraining layer.

Abstract: A turbine assembly having an outer casing (36), an inner structural ring (38), and an annular gas path (42) defined between outer and inner flow path walls (44, 46) for conducting a gas flow through the turbine assembly. A plurality of structural struts (52) are spaced apart in a circumferential direction, each strut (52) including a strut body (52a) extending in a radial direction for supporting the inner structural ring (38) to the outer casing (36). A first strut end (64) at a radially outer end of the strut body (52a) is detachably attached to the outer casing (36) with a first fastener structure (68) engaging the outer casing (36), and a second strut end (66) at a radially inner end of the strut body (52a) is detachably attached to the inner structural ring (38) with a second fastener structure (70) engaging the inner structural ring (38).

Abstract: The invention concerns a method for manufacturing of a gas turbine engine component (37) comprising an outer ring structure (42, 47), an inner ring structure (41), and a plurality of circumferentially spaced elements (46, 46a, 46b) extending between the inner ring structure (41) and the outer ring structure (42), wherein a primary gas channel for axial gas flow is defined between the elements (46, 46a, 46b), and wherein the component (37) has an inlet side for gas entrance and an outlet side for gas outflow. The invention is characterized in that the method comprises the step of machining a one-piece metal blank as to form a one-piece part (47) comprising: a portion (46b) of each of said elements (46), wherein said portion (46b) relates to a portion of an extension length of the elements (46) between said ring structures (41, 42); and a ring-shaped member (42) that connects said element portions (46b) and that is intended to form part of one of the ring structures.

Abstract: A turbine frame for a turbine engine having an axial centerline, includes an inner hub, an outer hub encircling the inner hub, a plurality of struts extending between the inner and outer hubs, at least one vane segment comprising at least first and second fairings mounted to the inner and outer hubs and encircling one of the struts and a single piece outer retaining ring that is operably coupled to the vane segment to fix a radial position of the vane segment relative to the inner and outer retaining rings and methods of assembling at least one vane segment having at least one vane formed from a pair of fairings to an exhaust frame.

Abstract: The invention concerns a gas turbine engine component (27) comprising an outer ring (21), an inner ring (20), a plurality of circumferentially spaced elements (22) extending between the inner ring (20) and the outer ring (21), wherein a primary gas channel for axial gas flow is defined between the elements (22), wherein the component (27) has an inlet side for gas entrance and an outlet side for gas outflow, and an annular load transfer structure (23) positioned internally of the inner ring (20) for transferring loads between said elements (22) and a bearing structure (24) for a turbine shaft (11) positioned centrally in the component (27), wherein the annular load transfer structure (23) extends circumferentially along at least a part of an inner side of the inner ring (20) and inwards in a radial direction of the component (27), wherein the annular load transfer structure (23) has a first portion (23a) and a second portion (23b), and wherein the first portion (23a) is located closer to the inner ring (20) t

Abstract: Systems and methods for controlling a clearance between a rotor and a stator of a steam turbine during transient operations rely upon heating or cooling a shell support structure of the steam turbine that supports the stator of the steam turbine. Selectively heating or cooling the shell support structure makes it possible for thermal growth/contraction rates and magnitudes of the shell support structure to better match the thermal growth/contraction rates and magnitudes of a bearing support structure of the steam turbine during transient operations. As a result, the clearance between the rotor and the stator of the steam turbine can be maintained.

Abstract: A composite article includes a substrate and a metal-containing layer on the substrate. The metal of the metal-containing layer is oxidizable to a plurality of different oxide phases. The metal-containing layer includes a plurality of phase-specific seed particles promoting formation of a selected one of the different oxide phases.

Abstract: An integrated single-piece exhaust system (SPEX) with modular construction that facilitates design changes for enhanced aerodynamics, structural integrity or serviceability. The SPEX defines splined or curved exhaust path surfaces, such as a series of cylindrical and frusto-conical sections that mimic curves. The constructed sections may include: (i) a tail cone assembly fabricated from conical sections that taper downstream to a reduced diameter; or (ii) an area-ruled cross section axially aligned with one or more rows of turbine struts; or both features. Modular inner and outer diameter inlet lips enhance transitional flow between the last row blades and the SPEX, as well as enhance structural integrity. Modular strut collars have large radius profiles between the SPEX annular inner diameter and outer diameter flow surfaces, for enhanced airflow and constant thickness walls for uniform heat transfer and thermal expansion. Scalloped mounting flanges enhance structural integrity and longevity.

Abstract: A gas turbine engine includes a heat exchanger, a mid-turbine frame, a passageway that extends through at least a portion of the mid-turbine frame and a first nozzle assembly. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The mid-turbine frame is in fluid communication with the heat exchanger. The conditioned airflow is communicated through the passageway and is received by the first nozzle assembly to condition gas turbine engine hardware.

Abstract: A mid-turbine frame located in a gas turbine engine axially aft of a high-pressure turbine and fore of a low-pressure turbine includes an outer frame case, an inner frame case, and at least a first spoke connecting the outer frame case to the inner frame case. The first spoke includes a tie rod having a first threaded surface and a connector having a second threaded surface. The first and second threaded surfaces overlap partially but not completely.

Abstract: A mid-turbine frame located in a gas turbine engine axially aft of a high-pressure turbine and fore of a low-pressure turbine includes an outer frame case, an inner frame case, and at least a first spoke connecting the outer frame case to the inner frame case. The first spoke is tightened so as to be in tension during substantially all operating conditions of the gas turbine engine.

Abstract: A static structure of a gas turbine engine includes a multiple of airfoil segments and at least one structural reinforcement ring mounted to the multiple of airfoil segments.

Abstract: A shield system for a gas turbine engine extends between an inner case structure and a vane pack.

Abstract: A gas turbine according to the present invention includes: a strut which passes through an outer diffuser and an inner diffuser, and connects an exhaust chamber wall and a bearing housing; a strut cover which covers the strut along the extending direction of the strut; a partitioning wall which is arranged between the inside of the inner diffuser in the radial direction and the outside of the bearing housing in the radial direction, of which the upstream side portion is sealed between the bearing housing and the partitioning wall, of which the downstream side portion is sealed between the inner diffuser and the partitioning wall, and in which a strut through-hole through which the strut passes is formed; and a hole seal member which seals a gap between the strut through-hole and the strut.

Abstract: A mid turbine frame of a gas turbine engine has a plurality of circumferentially spaced load transfer spokes extending radially between outer and inner cases. The load transfer spokes have a circumferentially enlarged inner end which is mounted to the inner case by a plurality of axially disposed fasteners extending through the inner case and spokes.

Abstract: A gas turbine engine case structure includes inner and outer annular case portions radially spaced from one another to provide a flow path and circumferentially arranged airfoils extend radially and interconnect the inner and outer annular case portions. The airfoils include multiple vanes and multiple strut-vanes. Each vane has a vane leading edge. Each strut-vane includes a strut-vane leading edge. The vane leading edges and strut-vane leading edges are aligned in a common plane. The vanes include a first axial length and the strut-vanes include a second axial length that is at least double the first axial length.

Abstract: A turbine engine support including a pair of arms for use in an arrangement of an engine having an inner case, an outer case and an interim fairing, the engine support arms comprising integrally formed arms arranged to extend from the outer case to the inner case and to be connected to the cases by a first and second end region respectively, and with an intermediate region of the pair of arms arranged to extend through the fairing, the pair of arms having a common first region located in the region of the outer case with the arms diverging from each other towards the inner case, and a fastening arrangement connecting the outer case to the arms, the fastener arrangement accessible from a direction extending between the two arms towards the first end region.

Abstract: An inlet connection piece for an axial compressor, particularly for a turbocompressor, includes an inlet housing (1) in which is arranged a bearing housing (2) with a bearing (3), particularly a radial and/or axial bearing, for a rotor. The bearing housing (2) is connected to the inlet housing (1) by an inlet strut (4) which is connected to the inlet housing in a front cross section. The center of the bearing (3) is arranged axially in the flow direction of a fluid to be compressed behind the area center of the front cross section by at least 0.1-times, particularly at least 0.15-times, particularly at least 0.2-times, particularly at least 0.25-times, the chord length of the front cross section. In addition or alternatively, a fluid passage (5, 6) is formed in the inlet strut (4), and at least portions of this fluid passage (5, 6) form an acute angle with a normal plane relative to the longitudinal axis of the inlet connection piece.