Abstract: A hanger system for connecting components in a gas turbine engine has a first spaced component, a second spaced component arranged a desired distance from the first spaced component, and a plurality of spacers arranged between the first spaced component and the second spaced component. A T-bar having a shaft portion and a crossbar is arranged between the components. The shaft portion of the T-bar passes through an aperture in the first spaced component and the crossbar portion of the T-bar is arranged adjacent to the second spaced component. A bracket is coupled to the second spaced component and substantially encapsulates the crossbar portion of the T-bar.

Abstract: Gas turbine engine systems involving rotor bayonet coverplates and tools for installing such coverplates are provided. In this regard, a representative turbine assembly for a gas turbine engine includes: a turbine disk operative to mount a set of turbine blades; and a coverplate having an annular main body portion and a spaced annular arrangement of tabs extending radially inwardly from the main body portion with open-ended gaps being located between the tabs, the tabs being operative to secure an inner diameter of the coverplate to the turbine disk.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a nacelle assembly that includes an inlet lip section and an inlet internal diffuser section downstream of the inlet lip section. A variable area fan nozzle is positioned near an aft segment of the nacelle assembly, the variable area fan nozzle adaptable to move between a first position having a first discharge airflow area and a second position having a second discharge airflow area greater than the first discharge airflow area. At least one boundary layer control device is positioned near one of the inlet lip section and the inlet internal diffuser section. A controller is configured to move the variable area fan nozzle from the first position to the second position and to actuate the at least one boundary layer control device to introduce an airflow in response to an operability condition.

Abstract: The invention relates to a method for producing a compressor blade, comprising the following steps: forging a blank made of an austenitic-ferritic steel; uniaxially stretching and plastically deforming the blank while at least the elongation and the deformation force of the blank are detected and monitored; and ending the stretching after a defined limit value for the stress has been reached.

Abstract: A structural layer (30) may be bi-cast onto ligaments (62) extending from a porous cooling construction (20). The material of the structural layer may be optimized for high-temperature strength, while the material of the porous construction may be optimized for high thermal conductivity. A fugitive material (56) such as wax may be formed on the ligaments of the porous construction. A second fugitive material (58) such as ceramic may fill the remaining part of the porous construction. An investment casting shell (60) may be disposed around the porous construction and the fugitive materials. The first fugitive material may then be replaced with the material of the structural layer (30), and the second fugitive material may be removed to provide coolant paths (26). A second structural layer (52) may be bi-cast onto further ligaments (62) on a second side of the porous construction.

Abstract: A method for profiling a replacement blade for an axial turbomachine is provided. The method includes: measuring hub contour geometry and housing contour geometry of the flow channel of the old blade and the axial position of the centre of gravity of the blade aerofoil of the old blade; laying out geometry of the blade aerofoil of the replacement blade, the blade aerofoil having a rearward sweep on its leading edge; defining a region of the blade aerofoil near the mounting and in which positive influence of the rearward sweep on the degree of stage efficiency is rated as low; and axially displacing the replacement blade aerofoil section arranged outside this region in the upstream direction, until the axial position of the centre of gravity of the blade aerofoil of the replacement blade coincides with the old blade.

Abstract: A seal assembly for rotary machine is provided. The seal assembly includes multiple compliant plates disposed between a stationary component and a rotary component of the rotary machine, and coupled circumferentially along the stationary component. Each compliant plate comprises a tip configured to be disposed facing the rotary component, and at least one plate slot extending from the stationary component towards the rotary component. The seal assembly also includes at least one annular resistance member configured to be coupled to the stationary component and disposed in the at least one plate slot in the compliant plates and one or more rotor slots or grooves located circumferentially on a surface of the rotary component proximate the tip of each of the plurality of compliant plates.

Abstract: A system includes a turbomachine that includes at least one rotor disk or stage having a peripheral portion disposed about a rotational axis of the rotor disk or stage. The peripheral portion includes a groove that extends circumferentially about the peripheral portion. The groove has a first groove surface and a second surface disposed opposite the first groove surface. The turbomachine also includes a closure bucket disposed adjacent at least one bucket within the groove. The closure bucket has a first surface that interfaces with the first groove surface and a second groove surface disposed opposite the first surface. The closure bucket blocks circumferential movement of the at least one bucket within the groove relative to the rotor disk or stage. The turbomachine further includes a single wedge disposed between and contacting the second surface of the closure bucket and the second groove surface to secure the closure bucket within the groove.

Abstract: A gas turbine engine includes a housing including an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case. The geared architecture includes an epicyclic gear train. A fan is rotationally driven by the geared architecture. A shaft provides a rotational axis. A hub is operatively supported by the shaft. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively.

Abstract: An example method of maintaining a serviceable component of a gas turbine engine includes selecting a used component, using a fluid to move an abrasive against a surface of the used component, and removing material from the used component using the abrasive. In one example, the method moves the abrasive against the surface of the used component when the used component is installed within the gas turbine engine.

Abstract: A turbine design method that can easily construct a turbine stage structure in which an unsteady force acting on a rotor blade can be reduced and degradation in performance and increase in rotor shaft length can be prevented is provided. Unsteady forces and exciting forces by the potential field interaction acting on the rotor blade are respectively obtained, exciting forces by the wake interaction acting on the rotor blade are obtained, the exciting forces by the potential field interaction and the wake interaction are mathematically expressed, the unsteady force acting on the rotor blade when the distance between stator and rotor blades is an arbitrary value is calculated, and the distance between stator and rotor blades is determined based on a calculation result.

Abstract: A repair device and method for repairing a forward frame v-blade on an aircraft engine are described in which the repair device replaces a section of the forward frame v-blade. In one embodiment, the repair device includes a supplemental part, which is secured to the forward frame v-blade. The supplemental part includes a central web and a pair of legs with a leg thickness that is greater than the thickness of corresponding flanges on the forward frame v-blade. Fasteners such as rivets are used to couple the supplemental part to the forward frame v-blade.

Abstract: A method of assembling a seal in a horizontal split plane gas turbine engine including providing a rotor assembly including a turbine blade assembly defining a forward face and a seal ring extending axially from the forward face. The rotor assembly is positioned extending through a lower compressor casing and a lower turbine casing, the positioning including tilting the rotor assembly at an angle relative to the longitudinal axis for the engine. An upper turbine casing is positioned over the tilted rotor assembly, and the upper and lower turbine casings define a circumferentially extending seal groove. The rotor assembly is moved in an axially forward direction to position the seal ring in axially overlapping relation within the seal groove. The longitudinal axis of the rotor assembly is then aligned with the longitudinal axis of the turbine engine to further position the seal ring within the seal groove.

Abstract: Described are a gas turbine engine fan blade platform, related rotor assembly and gas turbine engine, as well as a method of assembling the same. The platform has a forward portion proximal to an axis of rotation, an aft portion, and a transition portion between the forward and aft portions. The forward portion has a forward interface surface facing axially forward, the aft portion has an aft interface surface facing radially outward, and the transition portion has at least one mounting feature. For the method of assembly, an aft support is installed on a fan disk and booster spool assembly. A plurality of fan blades are installed into a fan disk, followed by installing a fan platform between adjacent blades and securing the mounting features to the disk, thereby filling the annulus of the fan disk. Finally, a forward support is installed on the fan disk.

Abstract: A method of manufacturing turbine engine casings having at least one boss includes, in one exemplary embodiment, forming an engine casing having an outer wall, machining a tapered opening through the casing outer wall, and machining a tapered portion in a metal plug where the tapered portion is sized to mate with the tapered opening in the casing outer wall. The method also includes inserting the metal plug into the tapered opening in the casing outer wall, and welding the metal plug to the casing.

Abstract: A gas turbine engine includes a bushing that is non-round in cross-section, the bushing receivable within an aperture. A fastener passes through the bushing to retain a second component to a third component with respect to the first component.

Abstract: An installation apparatus for handling a component of a wind turbine is provided. The installation apparatus includes a base, a support portion and an extensible arm having opposing ends connected to the support portion and the base, respectively. The extensible arm is adapted to move the support portion relative to the base and about a transverse axis of the installation apparatus between a transport position and an installation position. In the transport position the support portion rests on the base. In the installation position the support portion and the base form an angle. An assembly including such an installation apparatus and a method of mounting a wind turbine are also provided.

Abstract: In a method for producing a cellular wheel made of metal, the following steps are conducted consecutively: (a) providing a sheet metal strip (26) having a length (1) that corresponds at least to the length of a circumferential line of an intermediate sleeve and a width (b) that corresponds at least to the length of the cellular wheel; (b) placing disks (16) in predetermined locations in predetermined quantities on both sides of the sheet metal strip (26) perpendicular to the sheet metal surface and perpendicular to the longitudinal direction of the sheet metal strip (26) and connecting the disks (16) to the sheet metal strip (26) by welding or brazing; (c) bending the metal strip (26) equipped on both sides with the disks (16) and connecting the two ends of the sheet metal strip (26) by welding or brazing to form the intermediate sleeve; (d) placing a first tubular sleeve that is concentric to the intermediate sleeve as an outer sleeve, and a second tubular sleeve that is concentric to the intermediate sleeve

Abstract: A casing for an aircraft engine includes an outer ring and an inner hub defining an airflow passage therebetween, the outer ring having an axis defining an axial direction; a plurality of struts arranged in a circumferential array and extending radially from the inner hub to the outer ring to mount the inner hub to the outer ring; wherein the outer ring is defined by a double skin including an axially-extending annular outer skin of sheet metal concentrically surrounding and radially-spaced from an annular inner skin of sheet metal, the outer and inner skins generally parallel to one another, an annular front end ring and an annular rear end ring welded or brazed to the outer and inner skins adjacent respective front and rear edges of the skins to define an annular cavity between them, and the outer ring further comprising a plurality of circumferentially spaced axially-extending ribs interconnecting the outer and inner skins to reinforce the double skins.

Abstract: A first process is provided for forming a stack of leaves for use in a leaf seal which effects a seal between two components. Corresponding processes are provided for forming a leaf-spacer pair and then for forming a stack of leaves from such pairs. Each leaf of the stack has a leaf section which maintains wiping contact with one of the components and a root section which is fixed relative to the other component and from which the leaf section extends. The stack includes a plurality of spacers which interpose between the root sections.

Abstract: A liner and attachment structure has an exhaust liner for use in a gas turbine engine. At least one hanger has feet secured to the liner. The hanger has an aperture extending at a central web. A flanged washer is received within the opening in the hanger. The flanged washer allows adjustment relative to the hanger. The flanged washer has a spherical recess. A collet has a plurality of part-spherical fingers separated by slots, and are received in the spherical recess of the flanged washer. A member extends into the collet to hold the part-spherical fingers radially outwardly. The member is also utilized to secure static structure, and to secure the liner to the static structure.

Abstract: A turbomachine seal assembly includes a rotor disposed about an axial centerline, the rotor having an outer surface. Also included is a stationary component extending circumferentially about the rotor. Further included is at least one primary annular seal ring operably coupled to the stationary component and extending radially inwardly to close proximity with the outer surface of the rotor. Yet further included is a secondary annular seal ring operably coupled to the stationary component and integrally formed with the at least one primary annular seal ring, the secondary annular seal ring extending radially inwardly to close proximity with the outer surface of the rotor.

Abstract: A turbine engine comprises compressor and turbine sections. An epicyclic gear train includes a carrier, a sun gear and intermediate gears arranged about and intermeshing with the sun gear. The intermediate gears are supported by the carrier. A baffle includes a lubrication passage near at least one of the sun gear and intermediate gears for directing a lubricant on at least one of the sun gear and intermediate gears. A method of designing a turbine engine is also disclosed.

Abstract: The present disclosure is directed to the use and manufacture of cooling features within a component used in a hot gas path, such as within a turbine. In one embodiment, channels are formed within an external surface of the component and filled with a removable material. The external surface and channels may then be coated with one or more layers, such as a structural layer and/or top coat. The removable material may then be removed to leave the channels free of the removable material.

Abstract: Disclosed are a micro gas turbine and a method of assembling the same. The micro gas turbine includes an ignitor assembly having an ignitor, along with an ignitor-coupling structure. The ignitor-coupling structure includes a mounting bracket having first and second ends, the first end being coupled to the ignitor and the second end being provided on its outer circumference with an external screw. A coupling member is mounted to a liner casing surrounding a combustor and has, on its inner circumference, an internal screw corresponding to the external screw. A bellows surrounds the mounting bracket.

Abstract: In one aspect, a method of forming a hot gas path component is provided. The method includes forming at least one groove in an outer surface of a substrate, wherein the at least one groove has a base and a top. The method further includes filling the at least one groove with a filler. The method also includes applying at least one cover layer over at least a portion of the outer surface of the substrate such that the at least one groove and the at least one cover layer define at least one micro-channel for cooling the component. The filler is automatically removed from the at least one micro-channel during application of the at least one cover layer. Methods for coating a hot gas component and for assembling a turbine engine assembly are also provided.

Abstract: A modular exhaust gas assembly includes a turbocharger housing having an exhaust flange and a bearing flange receptacle, and a plurality of turbine scrolls of different sizes for selective installation into the turbocharger housing in dependence on a power of an engine. Each turbine scroll has an inlet zone and is connected to the bearing flange receptacle via a selected one of a plurality of different bearing flanges and to the exhaust flange via a selected one of a plurality of different exhaust links. The inlet zone of each turbine scroll is configured to complement a contour of an outlet zone of a standard manifold so that the turbine scrolls are selectively connectable via their inlet zone to the manifold to suit the engine power at hand.

Abstract: A method of positioning a bearing of a turbomachine in a squeeze film annulus is disclosed. The method includes providing a bearing in which a rotor shaft is disposed and a bearing support mounted about and radially supporting the bearing, with the bearing support at least in part defining the squeeze film annulus. A further step typically includes providing a plurality of centering elements associated with the bearing and bearing support and acting to center the bearing within the squeeze film annulus, with the centering elements provided at radially spaced locations around the bearing. An additional step in the method may include individually machining or shimming the centering elements to adjust the positioning of the bearing in the squeeze film annulus or to impart pre-load to improve the resiliency of the centering elements.

Abstract: A variable geometry turbine of the kind used in a turbocharger has a variable geometry element such as a nozzle ring or an annular array of swing vanes that is operated by an actuator. The actuator has an output shaft coupled to a transmission mechanism for moving the variable geometry element. A rotary sensor device coupled to the output shaft of the actuator has a sensor wheel with a stop, slip clutch mechanism and a rotary position sensor. The device converts movement of the actuator output shaft into rotation of the wheel and the sensor generates an output signal representative of the rotary position of the wheel to provide a value indicative of the position of the variable geometry element.

Abstract: A turbine engine part forming a compressor stator or a turbine nozzle and including an inner shroud, an outer shroud, and vanes extending substantially radially between the inner and outer shrouds and being secured thereto. The part is made of composite material and is obtained by densifying a fiber preform with a matrix. The fiber preform includes a set of yarns extending continuously along a path passing longitudinally along the preform portions of at least two consecutive vanes by passing through the inner shroud preform portion and the outer shroud preform portion, and the woven fiber reinforcement yarns extends continuously in the circumferential direction along an inner shroud segment and along an outer shroud segment between which the consecutive vanes extend.

Abstract: A method for manufacturing a turbine nozzle having a non-linear cooling conduit is disclosed. In one embodiment, a method includes: providing a turbine nozzle. The turbine nozzle includes: an airfoil, a cavity, having an inner surface, located within the airfoil, at least one endwall adjacent the airfoil, and a fillet region connecting the airfoil and the endwall. The fillet region also includes an outer surface. The method also includes: forming a non-linear cooling conduit within the fillet region and adjacent the outer surface of the fillet region of the turbine nozzle. The forming of the non-linear cooling conduit includes curved drilling through a portion of the outer surface of the fillet region of the turbine nozzle.

Abstract: A method and ground support equipment (GSE) for attaching an engine core to an engine fan module on an aircraft pylon. The GSE may comprise GSE supports and lifting components attached to the pylon, two suspension rails attached to the lifting components, two translating rails translatably attached to the two suspensions rails and fixedly attached to opposite sides of the engine core, and two alignment fittings fixed to the engine fan module. The method of using the GSE may comprise lifting the engine core vertically using the lifting components and anchoring the suspension rails to the alignment fittings. The translating rails and engine core may then be translated in an aft-to-forward direction such that portions of the translating rails engage portions of the alignment fittings to cooperatively guide the translating rails into a final forward position in which the engine core is aligned relative to the engine fan module.

Abstract: A transition duct is provided for coupling a combustor and a turbine section of a gas turbine. The transition duct includes a transition duct skin. The transition duct skin comprises a first surface section, a second surface section, and a clinch welded joint connecting the first surface section and the second surface section. Also provided is a method for manufacturing such a transition duct.

Abstract: A method for forming an inclined-blade blower wheel is provided by arranging a plurality of blades about respective circumferences of first and second end caps. The plurality of blades extend longitudinally between the first and second end caps and parallel to an axis defined by respective centers of the first and second end caps. The first end cap is rotated with respect to the second end cap a predetermined amount, therein skewing the plurality of blades at a desired longitudinal pitch between the first end cap and second end cap. The first end cap and second end cap are then rotated in unison while crimping the circumferences of the first end cap and second end cap, therein securing the plurality of blades to the first and second end caps and fixing the desired longitudinal pitch of the plurality of blades from the first end cap to the second end cap.

Abstract: A system and methods for a self-rotating fluidic traverse actuator are presented. A turbine rotates in response to a fluid flow, and an outer cylinder with a longitudinal slot that ejects the fluid flow. An inner cylinder rotates inside the outer cylinder in response to a rotation of the turbine and at least one helical slot of the inner cylinder ejects the fluid flow into the longitudinal slot.

Abstract: A rotational component for a gas turbine engine includes at least one passage with a semi-spherical end.

Abstract: Embodiments of a turboshaft engine are provided, as are embodiments of a method for manufacturing a turboshaft engine. In one embodiment, the turboshaft engine includes an Inlet Particle Separator (IPS) system having an IPS scavenge flow circuit fluidly coupled to the engine's inlet section. A heat exchanger and a heat exchanger bypass duct are fluidly coupled to the IPS scavenge flow circuit. The heat exchanger bypass duct is configured to direct airflow around the heat exchanger. A particle separation device, such as an IPS blower, is fluidly coupled in series with the heat exchanger in the IPS scavenge flow circuit. The particle separation device is positioned to direct particulate matter entrained within the airflow through the IPS scavenge flow circuit into an inlet of the heat exchanger bypass duct and thereby reduce the amount of particulate matter ingested by the heat exchanger during operation of the turboshaft engine.

Abstract: A process for manufacturing a metal part reinforced with ceramic fibers including machining at least one housing for an insert in a metal body having an upper face. At least one insert formed from ceramic fibers in a metal matrix is placed in the housing. The insert is covered with a cover. A vacuum is created in the interstitial space around the insert and the interstitial space is hermetically sealed under vacuum. The assembly, namely the metal body with the cover, is treated by hot isostatic pressure. The treated assembly is machined in order to obtain the part. The cover includes an element covering the insert in the slot and projecting from the upper face, and a sheet covering the upper face with said element. In particular, the insert is straight and the housing for the insert in the metal body forms a straight slot.

Abstract: A fluid conduit has a constant diameter and a chamber in the conduit has a larger diameter than the diameter of the conduit. Within the chamber, an impeller is rotatable by fluid moving through the conduit and the chamber. The impeller includes blades extending spirally along an impeller shaft. When rotated, the impeller blades define a cylinder having a diameter greater than the conduit diameter and less than the chamber diameter.

Abstract: A method of forming a hollow component with an internal structure from first and second panels includes the step of forming at least one protrusion on a surface of at least one of the first and second panels by a material deposition process. The first and second panels are assembled into a preform the panels being oriented such that each panel defines an interior and an exterior facing surface, with the at least one protrusion extending from an exterior facing surface of a panel. The preform is expanded against a die, such that the at least one protrusion is transferred from the exterior surface of a panel to the interior surface of a panel so as to define an internal structure. Forming the at least one protrusion may include encapsulating an elongate member on the surface of a panel by a material deposition process.

Abstract: A method is provided for machining a slot having a slot base in a turbine engine rotor disk. The method includes forming a preform slot that extends along a longitudinal axis through the rotor disk. The preform slot includes a preform slot endwall connected laterally between a first slot sidewall and a second slot sidewall. A cutting tool is rotated about its axial centerline, which is substantially parallel to the longitudinal axis. The preform slot endwall is machined with the rotating cutting tool to form the slot base.

Abstract: A locking plate for use in an air turbine starter has a lock plate body including an oil slinger extending away from a base. The base is positioned on an outer peripheral surface of a clutch frame. The slinger extends away from the base for a distance, and a ratio of the distance to a thickness of the base is ten and thirty. A clutch and air turbine starter, and a method of assembly are also disclosed.

Abstract: Method and gas turbine system having a reduced footprint. The gas turbine system includes a gas turbine configured to produce energy and having a gas turbine shaft; an auxiliary equipment attached to the gas turbine; an overhung shaft of the auxiliary equipment being configured to be attached to the gas turbine shaft; a flexible joint configured to be provided between the shaft of the auxiliary equipment and the gas turbine shaft; and a bearing system having at least two bearing units provided at a first end of the shaft of the auxiliary equipment next to the flexible joint. A second end of the shaft of the auxiliary equipment is free of bearings.

Abstract: Implementations of the present disclosure are directed to turbine assemblies for turbocharger systems. In some implementations, turbine housings include a body that defines an inlet for fluid communication with a fluid source, and a wall, the wall dividing the inlet into an inner inlet and an outer inlet, and a fluid guide assembly disposed within the housing, the fluid guide assembly including a plurality of vanes that demarcate an inner volute and an outer volute within the housing, the inner volute being in fluid communication with the inner inlet and the outer volute being in fluid communication with the outer inlet, each vane of the plurality of vanes being fixed at a respective angle relative to a radial direction, the plurality of vanes guiding fluid flow from the outer volute to the inner volute.

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: Apparatus for lateral fitting and removing of a compressor barrel into and out of a casing of a turbocompressor, the barrel having an inner core section with split disks which are bolted together coaxially, a cap rotatably mounted on a bearing block, and a rotor, wherein the disks are bolted to the cap and the rotor, and wherein the casing is vertically split and has a suction connection and a pressure connection. A support arm has a proximal end which can be releasably connected to the bearing block and a distal end which extends beyond the rotor and is displaceably supported on the casing when the proximal end is connected to the bearing block. A support device can be releasably mounted to the bearing block oppositely from the support arm, the supporting device being movable laterally on a guide to move the barrel into and out of the casing.

Abstract: With a method for the repair of compressor rotors designed in blisk technology the damaged stage is severed from the rotor, and a new blisk is joined to the rotor by electron-beam welding. For stress relieving the rotor is subjected to local thermal treatment by means of a current produced in the weld area by electro-magnetic induction.

Abstract: On an intake cone made of fiber compound material for a gas turbine engine, the conical part, the attachment part and the fairing part are manufactured as one piece from a plurality of mutually crossing and covering winding layers (1) forming an interlace (2). The winding layers include parallel, alternately adjacent glass fiber strands and carbon fiber strands of equal thickness. The one-piece intake cone is producible and mountable cost-effectively and is characterized by elasticity, stiffness and impact resistance.

Abstract: An apparatus for installing a turbine casing including a first drive subassembly and a member coupled to the first drive subassembly configured for engaging a first segment of the turbine casing. The apparatus may also include a second member coupled to the second drive subassembly configured for engaging the first segment of the turbine casing. The apparatus may be provided with a first retainer connected to the first member and configured for engaging a second segment of the turbine casing, and a second retainer connected to the second member and configured for engaging the second segment of the turbine casing.

Abstract: In a method of making a turbocharger housing surfaces of a sheet-metal shell which bound a gap towards the turbine wheel are measured, after the sheet-metal shell has been joined with a bearing flange provided for support of a turbine wheel, to generate measuring values. Subsequently, the bearing flange is machined in dependence on the measuring values for establishing a position of the turbine wheel in relation to the bearing flange and thus of the sheet-metal shell.