WO2020099184A1 - Procédé de fabrication d'un composant pour une turbomachine - Google Patents

Procédé de fabrication d'un composant pour une turbomachine Download PDF

Info

Publication number
WO2020099184A1
WO2020099184A1 PCT/EP2019/080225 EP2019080225W WO2020099184A1 WO 2020099184 A1 WO2020099184 A1 WO 2020099184A1 EP 2019080225 W EP2019080225 W EP 2019080225W WO 2020099184 A1 WO2020099184 A1 WO 2020099184A1
Authority
WO
WIPO (PCT)
Prior art keywords
component
components
connecting elements
base element
turbomachine
Prior art date
Application number
PCT/EP2019/080225
Other languages
German (de)
English (en)
Inventor
Sebastian Motsch
Wolfgang Rothkegel
Björn HINZE
Original Assignee
Rolls-Royce Deutschland Ltd & Co Kg
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from DE102018219590.0A external-priority patent/DE102018219590A1/de
Priority claimed from DE102018219591.9A external-priority patent/DE102018219591A1/de
Application filed by Rolls-Royce Deutschland Ltd & Co Kg filed Critical Rolls-Royce Deutschland Ltd & Co Kg
Publication of WO2020099184A1 publication Critical patent/WO2020099184A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
    • B23K20/12—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
    • B23K20/12—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding
    • B23K20/129—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding specially adapted for particular articles or workpieces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
    • B23K20/22—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating taking account of the properties of the materials to be welded
    • B23K20/233—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating taking account of the properties of the materials to be welded without ferrous layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/006—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine wheels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3061—Fixing blades to rotors; Blade roots ; Blade spacers by welding, brazing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2101/00—Articles made by soldering, welding or cutting
    • B23K2101/001—Turbines
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/18—Dissimilar materials
    • B23K2103/26—Alloys of Nickel and Cobalt and Chromium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/239—Inertia or friction welding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades

Definitions

  • the present disclosure relates generally to engine technology.
  • the present disclosure relates to the production of engine components with a configuration suitable for friction welding production.
  • the present disclosure relates to a manufacturing method for an engine component with reduced vibration properties.
  • high-pressure turbines or compressor modules high-pressure turbines or compressor modules, rotor blades, mounted on a ring, are used which, compared to rotor blades in the medium or high-pressure region of a turbine, have comparatively long dimensions, at least in one direction of extension. exhibit.
  • These comparatively long moving blades which are used above all at rear stages in a turbine, usually have comparatively narrow configurations at the same time and are used in a turbine in a relatively low speed range or relatively low temperature range.
  • blisks or blings are used, in particular in the area of the low or medium pressure compressor.
  • a conventional manufacturing process for such blisks or blings consists of full machining
  • Such short blades have an uncritical vibration behavior and therefore do not require any further toothing or connection between adjacent blades, for example tensioning straps such as so-called snubbers, interlocking shrouds or Z-shrouds, which conventionally make it impossible to produce a friction weld due to the complex geometric structure or simply because of the fact that long blades with tensioning straps would already be connected and would therefore not be able to be attached to the disc individually using a friction welding process.
  • tensioning straps such as so-called snubbers, interlocking shrouds or Z-shrouds
  • a method for operating a turbomachine in particular for an aircraft engine, the turbomachine having a component, produced by the steps of providing at least one first component with a first connecting element, providing at least one second component with one second connecting element, providing a base element, attaching at least one of the at least one first component to the base element, attaching one of the at least one second component to the base element, the second component being attached next to the first component or arranged between two first components, and wherein connecting elements of the first component and the second component are non-positively and / or positively connected in an operating state of the turbomachine.
  • a method for producing a component for a turbomachine, in particular for an aircraft engine comprising the steps of providing at least one first component with a first connecting element, providing at least one second component with a second connecting element, providing one
  • Base element attaching at least one of the at least one first component to the base element, attaching one of the at least one second component to the base element, the second component being attached adjacent to the first component or between two first components, and wherein
  • Connecting elements of the first component and the second component after fastening the at least one first component and the second component are non-positively and / or positively connected.
  • a component for a gas turbine engine for an aircraft comprising a first component with a first connecting element, a second component with a second connecting element, and a base element, the first component and the second component on the base element are attached adjacent, wherein connecting elements of the first component and the second component are non-positively and / or positively connected, or wherein connecting elements of the first component and the second component are non-positively and / or positively connected in an operating state of the turbomachine.
  • a gas turbine engine for an aircraft comprising at least one component according to an embodiment of the present disclosure, produced according to an embodiment of a method of the present disclosure.
  • an operating method and a manufacturing method for rotor blades for low-pressure compressor areas in turbines are provided, as a result of which even complex, geometrically designed rotor blades can be fastened to a disk using a friction welding process and still have a preferred vibration behavior, in particular during operation.
  • the vibration behavior is influenced by the use of connecting elements, which are arranged essentially in the circumferential direction between two adjacent rotor blades and at least connect them appropriately during operation or are in contact by means of the connecting elements in order to be able to influence the vibration behavior of the rotor blades .
  • connections or contacts have been formed integrally and thus an integral connection between two moving blades, in particular in the case of a machining production process, made from the solid material.
  • the connecting element between two rotor blades or components has conventionally already been produced from the solid during the manufacture of the individual rotor blades.
  • the individual components or blades of a complex component have connecting elements in the radial circumferential direction, which are in contact with one another at least during operation, in particular in a form-fitting manner.
  • Designated contact points or contact surfaces a non-positive connection, which can thus be subjected to pressure, for example, can be realized, or a form-fitting connection is also possible through a suitably complex geometric configuration.
  • Components or rotor blades according to the disclosure have a comparatively large geometric length in a longitudinal direction in comparison to other rotor blades or components in a compressor.
  • the direction of longitudinal extension refers here to the radial direction starting from the disk or a base element, thus the inner attachment point of a component or rotor blade to its radially outer position, thus the length of the rotor blade in the radial direction Extension direction.
  • the connecting elements of adjacent rotor blades have essentially corresponding radial positions.
  • the connecting elements are arranged in a comparable radial position and can thus come into contact with one another, for example in contact with one another or rest on the adjacent surfaces of the connecting elements and thereby the contact between the connecting elements manufacture.
  • a positive connection can be achieved.
  • Components according to the present disclosure may have connecting elements at extreme radial positions or alternatively or additionally at intermediate radial positions of the longitudinal extension direction of the individual components.
  • individual components may be attached to a base element or a disk, which friction welding connection represents a first connection or fastening point of the component.
  • neighboring components may be connected to one another at further contact points or further contact surfaces. This connection may provide a non-positive or positive connection.
  • a component has at least one, preferably two or a multiple of two connecting elements with which one
  • Component is in contact with neighboring components.
  • a preferred embodiment of such a connecting element is, for example, the provision of a shroud in an external radial position.
  • Each component may have a portion of the shroud that is designed and dimensioned to come into contact with the corresponding shrouds of adjacent components.
  • the individual partial shrouds of the individual components may be joined together to form an overall shroud, at least during operation of the turbomachine, and thus form a substantially circumferentially closed shroud, by partial shrouds lying on top of one another, in particular with contact surfaces in the contact point .
  • components according to the present disclosure may have further connecting elements at further suitable radial positions.
  • the connecting elements can be designed in such a way that they come into contact with complementarily designed connecting elements of adjacent components or directly with the surface of an adjacent component.
  • the non-positive or positive contact between two components can only be established by means of the connecting elements when the component is in an operating state, thus when the engine is operating.
  • This may be possible, for example, by means of suitably dimensioned or constructed components by means of centrifugal expansion or thermal expansion.
  • the contact areas may be configured such that adjacent contact areas after the assembly on the
  • a component has a plurality of connecting elements which are formed on opposite sides of the component. As a result of the requirement to align connecting elements with neighboring components, these connecting elements essentially extend in the circumferential direction. Two, three, four or five or more connecting elements per component are thus conceivable, which may be arranged at the same or different radial positions on the opposite sides of the component. As a result, not all adjacent components or blades may have connecting elements with essentially the same radial positions. Rather, the connecting elements can, for example, alternately have alternating or generally different radial positions.
  • the overall vibration behavior or the individual vibration behavior of a plurality of components can be improved compared to an embodiment with essentially the same radial positions of the connecting elements, and thus a minimization or optimization of the vibration behavior can be realized.
  • Adjacent and thus complementarily designed connecting elements on adjacent components may, in particular, have the same radial position.
  • adjacent components can also be connected with two or more connecting elements.
  • Adjacent components may thus not only touch at contact points or a contact surface, but at several contact points and thereby transmit forces.
  • the connecting elements may be the same or of different types are in contact, in other words may be in a non-positive and / or positive contact. Further optimization of the vibration behavior of the component may be possible through a suitable configuration of the contact types, thus the points of attack or types of attack or connection types of connecting elements of adjacent components.
  • the radial position of a connecting element may be selected or determined in particular taking into account the vibration behavior of the component, in particular to reduce the tendency to vibrate of the individual components.
  • a suitable selection of the radial positions of connecting elements can thus be used to detune a dynamic overall system, so that a reduction or optimization of the vibration behavior of the component can be achieved.
  • Such a targeted influencing of the vibration behavior of individual rotor blades may have a positive influence on the tendency of a complex component to vibrate for a turbomachine, so that blades with larger dimensions than those conventionally suitable for a friction welding process may also be used for the production of a component by means of a friction welding process.
  • first connecting elements and second connecting elements like one another have directed contact surfaces, the contact surfaces of first connecting elements and second connecting elements in the
  • a complementary configuration of contact areas enables preferred power transmission between adjacent components, at least during operation.
  • the contact surfaces may also be suitably discontinuous, for example having indentations and complementary shapes which are brought into engagement with one another and thereby form a non-positive or positive connection.
  • the contact areas may be in a non-operating state
  • Turbo machine can be arranged at a distance.
  • the contact surfaces In a non-operating state, the contact surfaces may be arranged slightly spaced apart, thus have a so-called cold gap, and are not (yet) non-positively or positively connected.
  • the gap between the contact surfaces in an operating state, that is to say when the turbomachine is in operation, the gap between the contact surfaces may be reduced to zero, and thereby realize the non-positive or positive connection.
  • the majority of the first and second components may form a non-positive and / or positive connection in the circumferential direction, separately from, by means of the connecting elements, at least in operation
  • Fastening points of the components on the base element may appear as the formation of one further, alternative frictional connection or positive connection for fastening the components on the base element can be understood.
  • the entirety of the connecting elements of the components attached to a base element or ring may result, for example, in a self-contained cover band, and thereby realize the frictional connection or positive connection.
  • this is achieved by filling gaps between connecting elements of first components with the suitably designed connecting elements of second components, so that the connecting elements of adjacent components are in contact with one another and are set up for power transmission.
  • the fastening of the first component and / or the second component may be designed as a fastening by means of friction welding.
  • Friction welding may be a preferably simple connection of the first component and the second in connection with the desired or intended area of use of the components according to the disclosure
  • the first component and / or the second component may be designed as a moving blade.
  • the first component and / or the second component may be formed with a length in the direction of the longitudinal extent of less than 250 mm, in particular less than 100 mm, furthermore in particular less than 10 mm. Such lengths of the components may be particularly suitable for providing a component for use in a low-pressure compressor area.
  • the component may be designed as a component used in a speed range of less than 40,000 revolutions per minute (rpm), in particular less than 15,000 rpm, furthermore in particular less than 10,000 rpm.
  • the component may be designed as a component used in a temperature range of less than 1,400 ° C., in particular less than 1,100 ° C., more particularly less than 750 ° C.
  • a plurality of first components may first be attached to the base element and subsequently a plurality of second components.
  • first components 1, 3, 5 etc. may thus first be fastened and the gaps between the first components may subsequently be filled with second components 2, 4, 6 etc.
  • Component between two first components at the end of the friction welding process may be the contact surfaces of the connecting element or the connecting elements of the second component Contact surfaces or connecting elements of the first two components are brought into connection.
  • first components and second components thus have an alternating sequence on the ring as an example.
  • FIG. 1 is a side sectional view of a gas turbine engine in accordance with the present disclosure
  • FIG. 2A shows a first embodiment of a component for a gas turbine engine according to the present disclosure
  • 3A-C show details of the connection of two components in accordance with the present disclosure
  • FIG. 5 shows an exemplary embodiment of the method for setting a component for a turbomachine according to the present disclosure.
  • FIG. 1 shows a gas turbine engine 10 with a flaup rotation axis 9.
  • the engine 10 includes an air inlet 12 and a fan 23 that generates two air streams: a core air stream A and a bypass air stream B.
  • the gas turbine engine 10 includes a core 11 that receives the core air stream A.
  • the core engine 11 comprises, in axial flow order, a low pressure compressor 14, a high pressure compressor 15, a
  • Combustion device 16 a high-pressure turbine 17, a low-pressure turbine 19 and a core thrust nozzle 20.
  • An engine nacelle 21 surrounds the gas turbine engine 10 and defines a bypass duct 22 and a bypass thrust nozzle 18.
  • the bypass air flow B flows through the bypass duct 22.
  • the fan 23 is attached to the low-pressure turbine 19 via a shaft 26 and is driven by the latter.
  • the core air flow A is accelerated and compressed by the low pressure compressor 14 and passed into the high pressure compressor 15, where further compression takes place.
  • the compressed air discharged from the high pressure compressor 15 is conducted into the combustion device 16, where it is mixed with fuel and the mixture is burned.
  • the resulting hot combustion products then propagate through and drive the high pressure and low pressure turbines 17, 19 before being expelled through the nozzle 20 to provide some thrust.
  • the high-pressure compressor 15 is driven by the high-pressure turbine 17 through a connecting shaft.
  • Fan 23 generally provides most of the thrust.
  • low pressure turbine and “low pressure compressor” as used herein can be understood to mean the turbine stage with the lowest pressure and the compressor stage with the lowest pressure (ie that they are not the fan 23) and / or the turbine and compressor stage connected by the lowest speed connecting shaft 26 in the engine (ie, that it does not include the transmission output shaft that drives the fan 23).
  • the "low pressure turbine” and the “low pressure compressor” referred to here may alternatively be known as the “medium pressure turbine” and “medium pressure compressor”.
  • the fan 23 can be referred to as a first compression stage or compression stage with the lowest pressure.
  • gas turbine engines to which the present disclosure may apply may have alternative configurations.
  • such engines can have an alternative number Compressors and / or turbines and / or an alternative number of connecting shafts. As another example, this is shown in Figure
  • FIG. 1 relates to a turbofan engine, the disclosure may be applicable to any type of gas turbine engine, such as a gas turbine engine.
  • B in an open rotor (in which the fan stage is not surrounded by an engine nacelle) or a turboprop engine.
  • the geometry of the gas turbine engine 10 and components thereof is defined by a conventional axis system that has an axial direction (which is aligned with the axis of rotation 9), a radial one
  • 2A a first embodiment of a component for a gas turbine engine according to the present disclosure is illustrated as above.
  • 2A shows a component 30 consisting of two as an example
  • Components 32a, b which are arranged on a base element 38.
  • the base element 38 is only shown in sections and provides an essentially circumferential direction 36 for the entire component 30 completely closed disc 44.
  • Components 32a, b have a longitudinal extent 34a, b which points radially outwards from the base element 38.
  • the components 32a, b can, for example, be blades of a component of an engine turbine.
  • the components 32a, b are on their inner side, thus in a first radial position connected to the base element 38.
  • this connection can be formed in the context of the present disclosure by a friction weld connection 46, as a result of which each of the components 32a, b independently with the
  • Base element 38 or a disc 44 is connectable.
  • the component 30 or the components 32a, b has connecting elements 40a, b, designed as partial sections of a shroud which connect the components 32a, b to one another in the radial position r 2 .
  • the cover band 40a, b is only shown schematically in FIG. 2A and forms a closed force or form fit in the finished component 30 in the circumferential direction 36.
  • Base element 38 moves what is indicated by arrow 48 as a so-called shortening.
  • FIG. 2A is only qualitative, since, in particular within the scope of the present disclosure, comparatively long components 32a, b can be used, so that in particular the radial positions h and r 2 may be further apart than the representation in FIG. 2A.
  • Connecting elements 40a, b are by means of contact point 41 or
  • FIGS. 2B, C further configurations of a component according to the present disclosure are illustrated.
  • FIGS. 2B, C furthermore show various assembly configurations of components, for example configured as rotor blades on a disk for an engine turbine.
  • components 32a, b are attached to an independent base element 38a, b. This can be done via a friction welding connection, or it can also be realized by further, conventional connection methods.
  • the components 32a, b are arranged next to one another and subsequently attached to the disk 44 using a friction weld connection 46.
  • a friction weld connection 46 can first be formed for component 32a and then component 32b can be attached by means of a friction weld connection between base element 38b and washer 44.
  • FIG. 2C the assembly of a so-called pair of blades on disc 44 is shown.
  • Components 32a, b are first attached to a common base element 38 in accordance with the method described in FIG. 2A.
  • a plurality of pairs of moving blades can thus be provided, which can be attached to the disk 44 in a subsequent step, for example using a friction welding connection 46.
  • a friction welding connection 46 As an alternative to the friction weld connection 46, however, conventional further connection methods are also conceivable.
  • 3A to C detailed representations of the connection of two components according to the present disclosure are presented.
  • 3A to C show possible configurations of contact surfaces 41 of adjacent connecting elements 40a, b and thus of the adjacent components 32a, b, which are not shown in detail in FIGS. 3A to C.
  • FIGS. 3A, B each show the circumferential direction 36 and the longitudinal directions 34a, b of the components 32a, b, only connecting elements 40a, b being shown of components 32a, b.
  • the connecting element 40a is arranged schematically in the radial position r 2 and can therefore be regarded as a component already fastened on the base element 38.
  • Component 32b is initially shown in a radial position r 2 ⁇ , which is offset radially outwards by the amount of shortening 48. After the friction welding step has been carried out, connecting element 40b approaches radial position r 2 or also assumes the same as connecting element 40a.
  • the thickness d of the connecting element 40b can be greater or less than the amount of shortening 48.
  • the connecting elements 40a, b can be at least partially in contact before the friction welding process is carried out. This may result in a preferred assembly, since the partially overlapping or connected connecting elements 40a, b may provide a certain stability through power transmission before the friction welding step is carried out.
  • Component 32b, the connecting elements 40a, b are arranged essentially at the same radial position r 2 .
  • 3B shows a different type of configuration of the contact surfaces 41 of adjacent components.
  • 3B shows an exemplary 45 ° beveled contact surface, the mutually aligned contact surfaces still being complementary.
  • a discontinuous transition 42 for example a kink or jump in the contact surface 41, supports a positive connection of adjacent connecting elements 40a, b.
  • a beveled configuration of the contact surface as shown in FIG. 3B provides a simple positioning of adjacent components 32a, b for performing a friction welding step.
  • 3C shows four components 32a, b by way of example after their fastening, these being arranged alternately, thus a first component alternating with a second component.
  • the connecting elements 40a, b are shown, while the remaining elements of the components 32a, b are only indicated.
  • the connecting elements 40ab are in contact with one another via contact surfaces 41.
  • 3C shows in particular the beveled configuration of the contact surfaces. If a first plurality of first components 32a are first attached to the base element 38, these components are spaced apart or have a gap for introducing the second components 32b. According to the effect shown in FIG.
  • components 32b introduced into the gap between the first components 32a, are initially arranged in a radial position r 2 ⁇ before the friction welding step is carried out.
  • fill the second components 32b successively fill the gap between the first components 32a by reducing the radial position from r 2 - to r 2 and thus successively form the fully closed positive or positive connection in the circumferential direction, in particular when all second components 32b are fastened on the base element.
  • a cover band which is made up of individual elements but is now self-contained, is formed, which provides the non-positive or positive connection in the circumferential direction.
  • the introduced components 32b brace with the first components 32a and thereby form the shroud which is made up of individual elements.
  • FIG. 4 shows an embodiment of two components 32a, b fastened on the base element 38 or the disk 44 with connecting elements 40a, b, which are not in the radial end position r 2 , but alternatively or additionally in the radial position r z between adjacent components 32a, b are arranged.
  • the statements made above with regard to the contact surfaces 41 of the connecting elements 40a, b arranged with respect to one another apply unchanged.
  • 3B, C in particular, a plurality of connecting elements 40a, b between the radial positions and r 2 are provided. Adjacent components may have connecting elements in different radial positions. In other words, connecting elements to the adjacent components, not shown in FIG. 4, can be formed in the same radial position r z or different radial position r z1 , r z2 .
  • the method 50 for operating a turbomachine has a component of the turbomachine, produced by the steps of providing 52 at least one first component 32a with a first connecting element 40a, providing 54 at least one second component 32b with a second connecting element 40b, Provision 56 of a base element 38, fastening 58 of at least one of the at least one first component 32a on the base element 38, fastening 60 of one of the at least one second component 32b on the base element 38, the second component 32b next to the first component 32b or between two first components 32a arranged.
  • the respective connecting elements 40a, b of the first component 32a and the second component 32b are non-positively and / or positively connected in a respective operating state 61 of the turbomachine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

La présente invention concerne un procédé (50) pour faire fonctionner une turbomachine, en particulier d'un moteur d'avion, la turbomachine présentant une pièce, fabriquée par les étapes de fourniture (52) d'au moins un premier composant (32a) comprenant un premier élément de connexion (40a), fourniture (54) d'au moins un deuxième composant (32b) comprenant un deuxième élément de connexion (40b), fourniture (56) d'un élément de socle (38), fixation (58) d'au moins un de l'au moins un premier composant (32a) sur l'élément de socle (38), fixation (60) d'un de l'au moins un deuxième composant (32b) sur l'élément de socle (38), le deuxième composant (32b) étant fixé à côté de l'un premier composant (32b) ou entre deux premiers composants (32a), et, durant le fonctionnement (62) de la turbomachine, des éléments de connexion (40a,b) du premier composant (32a) et du deuxième composant (32b) étant en connexion par adhérence et/ou par complémentarité de forme dans un état de fonctionnement (62) respectif de la turbomachine. La présente invention concerne en outre un procédé pour la fabrication d'une pièce correspondante, une pièce correspondante ainsi qu'un moteur de turbine à gaz.
PCT/EP2019/080225 2018-11-15 2019-11-05 Procédé de fabrication d'un composant pour une turbomachine WO2020099184A1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
DE102018219590.0A DE102018219590A1 (de) 2018-11-15 2018-11-15 Verfahren zur Herstellung eines Bauteils für eine Turbomaschine
DE102018219591.9A DE102018219591A1 (de) 2018-11-15 2018-11-15 Verfahren zur Herstellung eines Bauteils für eine Turbomaschine
DE102018219591.9 2018-11-15
DE102018219590.0 2018-11-15

Publications (1)

Publication Number Publication Date
WO2020099184A1 true WO2020099184A1 (fr) 2020-05-22

Family

ID=68503092

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2019/080225 WO2020099184A1 (fr) 2018-11-15 2019-11-05 Procédé de fabrication d'un composant pour une turbomachine

Country Status (1)

Country Link
WO (1) WO2020099184A1 (fr)

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2772854A (en) * 1951-02-27 1956-12-04 Rateau Soc Vibration damping means for bladings of turbo-machines
US3837761A (en) * 1971-08-20 1974-09-24 Westinghouse Electric Corp Guide vanes for supersonic turbine blades
US5511948A (en) * 1994-02-18 1996-04-30 Kabushiki Kaisha Toshiba Rotor blade damping structure for axial-flow turbine
JPH10317105A (ja) * 1997-05-20 1998-12-02 Hitachi Ltd 高強度鋼，蒸気タービン長翼及び蒸気タービン
US20030012655A1 (en) * 2002-06-07 2003-01-16 Tomoyoshi Sasaki Turbine rotor blades assembly and method for assembling the same
DE102008057190A1 (de) * 2008-11-13 2010-05-20 Mtu Aero Engines Gmbh Schaufelcluster mit versetztem axialem Montagefuß
DE102009052305A1 (de) * 2009-11-07 2011-05-12 Mtu Aero Engines Gmbh Blisk, Gasturbine und Verfahren zur Herstellung einer derartigen Blisk
DE102016119681A1 (de) * 2016-10-14 2018-04-19 Abb Turbo Systems Ag Integral gegossene Strömungsmaschinenanordung und Verfahren zum Herstellen einer Strömungsmaschinenanordnung

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2772854A (en) * 1951-02-27 1956-12-04 Rateau Soc Vibration damping means for bladings of turbo-machines
US3837761A (en) * 1971-08-20 1974-09-24 Westinghouse Electric Corp Guide vanes for supersonic turbine blades
US5511948A (en) * 1994-02-18 1996-04-30 Kabushiki Kaisha Toshiba Rotor blade damping structure for axial-flow turbine
JPH10317105A (ja) * 1997-05-20 1998-12-02 Hitachi Ltd 高強度鋼，蒸気タービン長翼及び蒸気タービン
US20030012655A1 (en) * 2002-06-07 2003-01-16 Tomoyoshi Sasaki Turbine rotor blades assembly and method for assembling the same
DE102008057190A1 (de) * 2008-11-13 2010-05-20 Mtu Aero Engines Gmbh Schaufelcluster mit versetztem axialem Montagefuß
DE102009052305A1 (de) * 2009-11-07 2011-05-12 Mtu Aero Engines Gmbh Blisk, Gasturbine und Verfahren zur Herstellung einer derartigen Blisk
DE102016119681A1 (de) * 2016-10-14 2018-04-19 Abb Turbo Systems Ag Integral gegossene Strömungsmaschinenanordung und Verfahren zum Herstellen einer Strömungsmaschinenanordnung

Similar Documents

Publication Publication Date Title
EP1656493B1 (fr) Turbine a gas
EP1898054B1 (fr) Turbine a gaz
EP3611387B1 (fr) Roue à aubes d'une turbomachine
EP3273001B1 (fr) Procédé de fabrication d'un élément d'aube en tandem
CH709048A2 (de) Laufschaufel mit einer Dämpferanordnung für eine Turbine.
EP3051068A1 (fr) Bague d'aube directrice pour une turbomachine et procédé de fabrication additive
CH703596A2 (de) Brennkammer für eine Verbrennungsturbine.
CH701537B1 (de) Spitzendeckplatte mit Dämpfungsrippen für eine Rotorschaufel, die in eine Rotorscheibe einer Turbinenanlage einsetzbar ist.
CH703588A2 (de) Brennkammer für eine Gasturbine.
EP3306068A1 (fr) Turbine à double flux pour un avion supersonique civil
EP3428393A1 (fr) Roue aubagée d'une turbomachine
WO2021004821A1 (fr) Composant de propulseur présentant une zone de modification pour influencer une propagation de fissure et procédé de fabrication
DE112015005131T5 (de) Kühlstruktur für Turbine, und Gasturbine
EP3287608A1 (fr) Bague intérieure d'une couronne d'aubes directrices d'une turbomachine
DE102018129045A1 (de) Strukturbaugruppe für ein Gasturbinentriebwerk
DE102018122535B4 (de) Planetengetriebevorrichtung und Gasturbinentriebwerk
EP3260664A1 (fr) Zone annulaire extérieure épaissie radialement d'une ailette d'étanchéité
WO2017133819A1 (fr) Chambre de combustion pour turbine à gaz, délimitée par une paroi
WO2020099184A1 (fr) Procédé de fabrication d'un composant pour une turbomachine
DE102018219591A1 (de) Verfahren zur Herstellung eines Bauteils für eine Turbomaschine
DE102015007128A1 (de) Verfahren zum Herstellen eines Laufzeugs für eine Strömungsmaschine, insbesondere für einen Energiewandler
WO2010099782A1 (fr) Procédé de fabrication d'un rotor aubagé monobloc
EP3056684A1 (fr) Bague intérieure séparée axialement pour une turbomachine, un stator et groupe motopropulseur
DE102018219590A1 (de) Verfahren zur Herstellung eines Bauteils für eine Turbomaschine
DE102018201295A1 (de) Modul für eine strömungsmaschine

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 19801254

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 19801254

Country of ref document: EP

Kind code of ref document: A1