[go: up one dir, main page]
More Web Proxy on the site http://driver.im/

EP2024684A1 - Armor-plated machine components and gas turbines - Google Patents

Armor-plated machine components and gas turbines

Info

Publication number
EP2024684A1
EP2024684A1 EP07728485A EP07728485A EP2024684A1 EP 2024684 A1 EP2024684 A1 EP 2024684A1 EP 07728485 A EP07728485 A EP 07728485A EP 07728485 A EP07728485 A EP 07728485A EP 2024684 A1 EP2024684 A1 EP 2024684A1
Authority
EP
European Patent Office
Prior art keywords
armor
machine
machine component
segments
base body
Prior art date
Legal status (The legal status 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 status listed.)
Granted
Application number
EP07728485A
Other languages
German (de)
French (fr)
Other versions
EP2024684B1 (en
Inventor
Birgit Grüger
Martin Stapper
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
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
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP07728485A priority Critical patent/EP2024684B1/en
Publication of EP2024684A1 publication Critical patent/EP2024684A1/en
Application granted granted Critical
Publication of EP2024684B1 publication Critical patent/EP2024684B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/005—Combined with pressure or heat exchangers
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05001—Preventing corrosion by using special lining materials or other techniques

Definitions

  • the invention relates to a machine component with a base body made of a base material, which is provided in a portion of its surface with an armor made of a coating material with a hardness greater than the Grundmate ⁇ rial. It further relates to a gas turbine with a number of machine components of this type.
  • Turbines in particular gas turbines, are used in many areas to drive generators or work machines.
  • the energy content of a fuel is used to generate a rotational movement of a turbine shaft.
  • the fuel is combusted in a combustion chamber, fed by an air compressor, compressed air is ⁇ leads.
  • the working medium produced in the combustion chamber by the combustion of the fuel, under high pressure and at high temperature, is guided via a turbine unit arranged downstream of the combustion chamber, where it relaxes to perform work.
  • a turbine of this type comprises a plurality of components or machine components which are positioned in the turbine in accordance with predetermined dimensions, shapes and / or tolerances. In many cases, it may be desirable to avoid contact between adjacent machine components or components. To minimize parts with each other, so as to keep wear of the affected components particularly low. Nevertheless, it may in the operation of the turbine, for example, ⁇ follow thermal expansions or due to operationally caused vibrations occurring or the like, coming back to actually unwanted contact between such components, so that a certain amount of wear of such components occurs. For example, as derar ⁇ term machine components in the combustion chamber of the gas turbine usually a so-called flame tube, a
  • the machine components can be made in so-called armored embodiment, the regions most affected by the expected wear or the expected contacts with neighboring components tion with as Panze ⁇ protective coating designated are coated.
  • Such armor may consist of a coating material ge ⁇ forms its having a greater than the basic material of the component JE - thermal hardness so that a contact occurring due to wear can be reduced by such a suitable choice of material already.
  • a Maschi nenkomponente ⁇ indicate the type mentioned above, which is particularly suitable for use in a thermally relatively highly belaste- th area of a work machine. Furthermore, a gas turbine with a number of such machine components is to be specified.
  • segmented armor leads out ⁇ and is formed from a number of cladding segments.
  • the invention is based on the consideration that the machine-component should be provided for a fundamental applicability un ⁇ ter compliance with low-wear working conditions with a suitable armor.
  • the lateral extent of the armor should be kept particularly low.
  • individual zones of the armor should be executed decoupled from one another, in order thus to allow sufficient resilience to thermal deformation and the like.
  • the armor should be executed segment by segment.
  • the armor segments may be applied by suitable techniques on the base of the machine component.
  • the armor segments are applied by build-up welding on the base body, so that a particularly intimate connection to the base body and thus a high stability of the machine component as a whole he ⁇ is enough.
  • the armor segments can be applied to an outer surface of the base body, so that the resulting entste ⁇ rising contour has a plurality of given by the armor segments bulges on the surface of the rail component substantially.
  • the armor segments are vorteilhaf ⁇ tate introduced or embedded in associated recesses in the body.
  • a virtually even overall surface of the machine component can advantageously be achieved overall, with the outer surface of the armor segments in particular and the outer surface of the webs of the base body extending between the armor segments forming a continuous surface.
  • come machine components of the said type in a gas turbine in particular a flame tube of a combustion chamber as a mixing housing a burner and / or as in ⁇ nengeratiuse a combustor used.
  • a flame tube of a combustion chamber as a mixing housing a burner and / or as in ⁇ nengeratiuse a combustor used.
  • the reinforced portion advantageously the upper ⁇ surface of a first machine component adjacent to Gepan ⁇ zerten portion of the surface of a second machine component is arranged.
  • the coating material of the first Maschi ⁇ nenkomponente a different hardness than the coating material of the second machine component.
  • the advantages achieved by the invention are in particular that the segmented design of the Panze ⁇ tion of the machine component even with only small tolerance ranges attaching the armor on the body in the first place is possible, especially with regard to the segmented execution of the armor a distortion of the body due to the high operating temperatures during buildup welding can be largely avoided.
  • the segmented design of the armor also crack ⁇ education in the application of armor is avoided, which could occur with continuous welding of the armor.
  • a subsequent bending of the component is made possible without the order material would be too stressed.
  • deformations and connection welds during installation and operation are comparatively easy to carry out, without any critical effects on the component to be feared.
  • the surface of the machine component can be homogenized in retrospect, with a possible supernatant after the deposition welding can also be subsequently removed.
  • the compliance with externally-giving ⁇ ner dimensions can be ensured particularly for matched component geometry.
  • the segmented application of the armor also reduces the load on the component during manufacture, assembly and operation.
  • FIG 2 shows a section through a combustion chamber in gas ⁇ turbines according to FIG 1,
  • the gas turbine 1 comprises a compressor 2 for combustion air, a combustion chamber 4 and a turbine 6 to drive the compressor 2 and a Gene ⁇ rators not shown or a work machine.
  • the Turbi ⁇ are ne 6 and the compressor 2 arranged on a common, also referred to as the turbine rotor turbine shaft 8, is connected to the generator or the driven machine, and which is mounted rotatably about its central axis.
  • the combustion chamber 4 is equipped with a number of burners 10 for combustion of a liquid or gaseous fuel. It is also provided on its inner wall with heat shield elements not shown.
  • the turbine 6 has a number of rotatable blades 12 connected to the turbine shaft 8.
  • the runners 12 are arranged in a ring shape on the turbine shaft 8 and thus form a number of blade rows.
  • the turbine 6 comprises a number of fixed Leit ⁇ blades 14, which also wreath-shaped to form Guide vanes are attached to an inner housing 16 of the turbine 6.
  • the blades 12 serve to drive the turbine shaft 8 by momentum transfer from a tur ⁇ bine 6 flowing through the working medium M.
  • the vanes 14, however, serve to flow the working medium M between two seen in the flow direction of the working medium M consecutive blade rows or blade rings.
  • a successive pair of a ring of vanes 14 or a row of vanes and a ring of vanes 12 or a blade row is also referred to as a turbine stage.
  • Each vane 14 has a platform 18, which is arranged to fix the respective vane 14 on the inner housing 16 of the turbine 6 as a wall element.
  • the plate ⁇ form 18 is a thermally comparatively heavily belas ⁇ tetes component that forms the outer boundary of a hot gas channel for the turbine 6 flowing through the working medium M.
  • Each blade 12 is attached to the turbine shaft 8 in an analogous manner via a platform 20, also referred to as a blade root.
  • each guide ⁇ rings 21 is also the hot, exposed through the turbine 6 ⁇ flowing working medium M, and in the radial direction from the outer end 22 of the opposite him running blades 12 of a rotor blade row by a gap 24th
  • each of the combustion chamber 4 is in its inflow area to which a number of unspecified supply lines for media, such as fuel and combustion air is ⁇ included are equipped in its interior with a so-called flame tube 30 within which the combustion of the fuel takes place.
  • a so-called flame tube 30 within which the combustion of the fuel takes place.
  • the flame tube 30 is connected on the output side to a mixing housing 34 of the combustion chamber. 4
  • the flame tube 30, the transition piece 34 and the réellegenosu ⁇ se 36 are connected in the nature of nested tubes with ⁇ each other, so that a reliable media flow management is ensured by the flame tube 30 in the inner housing 36 of the combustion chamber 4.
  • the respectively inserted tube ends are thereby positio ⁇ niert as possible contact-free from each other in compliance with the predetermined dimensions and tolerances, so that wear due to coming in contact with each other components and rubbing together components as possible avoided.
  • it can drive caused during operation of the gas turbine 1, a constantly recurring ⁇ contact of these components do not avoid each other, so that in any case likely to be a residual wear ⁇ . To account for this wear, regular inspection and replacement of these components is required as part of maintenance and inspection work.
  • each of the engine components flame tube 30, transition piece 34 and inner housing 36 is constructed of a base body 40 made of base material, which in an in each case in Figures 3 to 6 Darge ⁇ presented portion of its surface with an armor 42nd is provided from a job material.
  • the application material is chosen such that it has a greater hardness compared to the base material, so that he he ⁇ increased resistance to mechanical and thermal stress is given.
  • the application material is applied to the base body 40 in each case by build-up welding.
  • the armor 42 is executed segmented the respective machine component.
  • the armor 42 comprises a plurality of armor segments 44, wherein the dimensioning with respect to the dimensioning of the actual machine component and the materials used is chosen such that the laterally limited extent the respective armor segments 44 too large impairment ⁇ tion of the base body 40 through different thermal expansion behavior and the like is avoided.
  • FIG 3 which are approximately Panze ⁇ segments 44 each in associated recesses in the base body 40 is introduced.
  • the recesses may have been introduced by suitable machining methods, such as by milling, turning or grinding.
  • the dimensions can in principle be carried out in such a way here that the cladding segments 44 are applied to a planar surface of the base body 40 and corresponding ⁇ speaking their thickness corresponding recesses are formed between them.
  • the preparation can also, as shown in Figures 3 to 6, carried out such that the outer surface of the armor segments 44 with the outer surface of extending between the outer armor segments 44 webs 46 of Base body 40 form a continuous and thus planar surface.
  • a finished machine component thereby creates a component which largely corresponds to an originally provided component in terms of its shape, dimensioning and dimensional stability and in particular has a correspondingly smooth and planar surface.
  • FIG. 4 shows that a bent cooling air ring 50 can also be embodied as an at least partially armored machine component of the type mentioned.
  • the cooling air ring 50 is also provided on its surface with Panzerssegmen ⁇ th 44 which are incorporated into corresponding recesses of the cooling air ring 50 forming body 40.
  • cooling air channels 52 are additionally provided, which are formed by corresponding holes.
  • FIG 5 it is shown that components such as armored machines ⁇ particular, the transition piece 34 and the flame tube 30 of the gas turbine 1 in their overlapping area are executed.
  • Armor 42 of these machine components are provided in each case on the facing surface segments.
  • the material for the armor 42 of the flame tube 30 of ge ⁇ ringerer hardness to choose as the material for the Panze ⁇ tion 42 of the transition piece 34th

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Organic Chemistry (AREA)
  • Metallurgy (AREA)
  • Materials Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laser Beam Processing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)

Abstract

The machine component useful in gas turbine for driving a generator or work machine, comprises a base body (40), which is made of a base material and is provided with a plating (42) from a plating material with larger hardness compared to the base material. The plating is segmently implemented and is formed by plating segments (44), which are applied on the base body by build-up welding and are brought into assigned recesses in the base body. The outside surface of the plating segments and an outside surface of a stage (46) running between the plating segments form a constant surface. An independent claim is included for a gas turbine with a number of machine components.

Description

Beschreibungdescription
GEPANZERTE MASCHINENKOMPONENTE UND GASTURBINEARMORED MACHINE COMPONENT AND GUESTURBINE
Die Erfindung bezieht sich auf eine Maschinenkomponente mit einem aus einem Grundmaterial gefertigten Grundkörper, der in einem Teilbereich seiner Oberfläche mit einer Panzerung aus einem Auftragsmaterial mit einer im Vergleich zum Grundmate¬ rial größeren Härte versehen ist. Sie betrifft weiterhin eine Gasturbine mit einer Anzahl von Maschinenkomponenten dieser Art.The invention relates to a machine component with a base body made of a base material, which is provided in a portion of its surface with an armor made of a coating material with a hardness greater than the Grundmate ¬ rial. It further relates to a gas turbine with a number of machine components of this type.
Turbinen, insbesondere Gasturbinen, werden in vielen Bereichen zum Antrieb von Generatoren oder von Arbeitsmaschinen eingesetzt. Dabei wird der Energieinhalt eines Brennstoffs zur Erzeugung einer Rotationsbewegung einer Turbinenwelle genutzt. Der Brennstoff wird dazu in einer Brennkammer verbrannt, wobei von einem Luftverdichter verdichtete Luft zuge¬ führt wird. Das in der Brennkammer durch die Verbrennung des Brennstoffs erzeugte, unter hohem Druck und unter hoher Temperatur stehende Arbeitsmedium wird dabei über eine der Brennkammer nachgeschaltete Turbineneinheit geführt, wo es sich arbeitsleistend entspannt.Turbines, in particular gas turbines, are used in many areas to drive generators or work machines. In this case, the energy content of a fuel is used to generate a rotational movement of a turbine shaft. The fuel is combusted in a combustion chamber, fed by an air compressor, compressed air is ¬ leads. The working medium produced in the combustion chamber by the combustion of the fuel, under high pressure and at high temperature, is guided via a turbine unit arranged downstream of the combustion chamber, where it relaxes to perform work.
Zur Erzeugung der Rotationsbewegung der Turbinenwelle sind dabei an dieser eine Anzahl von üblicherweise zu Schaufel¬ gruppen oder Schaufelreihen zusammengefassten Laufschaufeln angeordnet, die über einen Impulsübertrag aus dem Arbeitsme¬ dium die Turbinenwelle antreiben. Zur Führung des Arbeitsme- diums in der Turbineneinheit sind zudem üblicherweise zwi¬ schen benachbarten Laufschaufelreihen mit dem Turbinengehäuse verbundene Leitschaufelreihen angeordnet.For generating the rotational movement of the turbine shaft are in this group, a number of commonly ¬ blade or blade rows disposed summarized blades which dium over a momentum transfer from the Arbeitsme ¬ drive the turbine shaft. To guide the Arbeitsme- dium in the turbine unit also usually between ¬ adjacent blade rows are connected to the turbine housing associated vane rows.
Eine Turbine dieser Art umfasst eine Vielzahl von Bauteilen oder Maschinenkomponenten, die unter Einhaltung vorgegebener Maße, Formen und/oder Toleranzen geeignet in der Turbine positioniert sind. In vielen Fällen kann es dabei wünschenswert sein, den Kontakt benachbarter Maschinenkomponenten oder Bau- teile miteinander zu minimieren, um solchermaßen einen Verschleiß der betroffenen Bauteile besonders gering zu halten. Dennoch kann es beim Betrieb der Turbine, beispielsweise in¬ folge thermischer Ausdehnungen oder auch infolge von be- triebsbedingt auftretenden Schwingungen oder dergleichen, immer wieder zu eigentlich unerwünschtem Kontakt zwischen derartigen Bauteilen kommen, so dass ein gewisser Verschleiß derartiger Bauteile auftritt. Beispielsweise sind als derar¬ tige Maschinenkomponenten im Bereich der Brennkammer der Gasturbine üblicherweise ein so genanntes Flammrohr, einA turbine of this type comprises a plurality of components or machine components which are positioned in the turbine in accordance with predetermined dimensions, shapes and / or tolerances. In many cases, it may be desirable to avoid contact between adjacent machine components or components. To minimize parts with each other, so as to keep wear of the affected components particularly low. Nevertheless, it may in the operation of the turbine, for example, ¬ follow thermal expansions or due to operationally caused vibrations occurring or the like, coming back to actually unwanted contact between such components, so that a certain amount of wear of such components occurs. For example, as derar ¬ term machine components in the combustion chamber of the gas turbine usually a so-called flame tube, a
Mischgehäuse und ein Innengehäuse benachbart zueinander an¬ geordnet. Diese weisen bauartbedingt derart große Verformun¬ gen und kritische Toleranzen auf, dass im Betrieb der Gasturbine ein Kontakt dieser Bauteile stellenweise unver- meidlich ist. Durch diesen Kontakt entsteht ein unerwünschter und insbesondere bei langer Betriebsdauer möglicherweise auch kritischer Verschleiß, so dass die genannten Bauteile in regelmäßigen Abständen inspiziert und bei Bedarf ausgetauscht/repariert werden müssen.Mixed housing and an inner housing adjacent to each other ¬ ordered. This type of construction have such large Verformun ¬ gen and critical tolerances that contact of these components is at times unavoidable in the operation of the gas turbine. As a result of this contact, unwanted and, in particular during long periods of operation, possibly also critical wear occurs, so that the components mentioned must be inspected at regular intervals and, if necessary, replaced / repaired.
Um in derartigen Situationen den Verschleiß der betroffenen Bauteile oder Maschinenkomponenten besonders gering zu halten, können die Maschinenkomponenten in so genannter gepanzerter Ausführung gefertigt sein, wobei die vom erwarteten Verschleiß oder den erwarteten Kontakten mit Nachbarkomponenten besonders betroffenen Bereiche mit einer auch als Panze¬ rung bezeichneten Schutzbeschichtung überzogen sind. Eine derartige Panzerung kann dabei aus einem Auftragsmaterial ge¬ bildet sein, das eine im Vergleich zum Grundmaterial der je- weiligen Komponente größere mechanische Härte aufweist, so dass bereits durch eine derartig geeignete Materialwahl ein kontaktbedingt auftretender Verschleiß verringert werden kann .In order to keep especially low wear of the affected parts or machine components in such situations, the machine components can be made in so-called armored embodiment, the regions most affected by the expected wear or the expected contacts with neighboring components tion with as Panze ¬ protective coating designated are coated. Such armor may consist of a coating material ge ¬ forms its having a greater than the basic material of the component JE weiligen mechanical hardness so that a contact occurring due to wear can be reduced by such a suitable choice of material already.
Aufgrund der üblicherweise für derartige Einsatzzwecke größe¬ ren Härte des Auftragsmaterials ist dieses aber auch spröder als das jeweilige Grundmaterial des Grundkörpers der Maschi¬ nenkomponente. Eine Weiterverarbeitung des mit dem Auftrags- material versehenen Grundkörpers, beispielsweise durch Biegen oder dergleichen, ist somit nur noch eingeschränkt möglich. Des Weiteren kann es bei einer thermischen Ausdehnung des Grundkörpers in dem mit dem Auftragsmaterial versehenen Be- reich aufgrund des unterschiedlichen thermischen Ausdehnungsverhaltens zu Rissbildungen und anderen Beschädigungen kommen. Gerade zum Einsatz in thermisch vergleichsweise hoch belasteten Regionen, wie beispielsweise im Innenbereich der Brennkammer einer Gasturbine, sind derartig gepanzerte Ma- schinenkomponenten daher nur bedingt geeignet.Due to the customarily used for such purposes ¬ ren hardness size of the application material that is also more brittle than nenkomponente top of the basic material of the body of the Maschi ¬. Further processing of the product material provided basic body, for example by bending or the like, is thus only possible to a limited extent. Furthermore, thermal expansion of the main body in the area provided with the application material may lead to cracking and other damage due to the different thermal expansion behavior. Especially for use in thermally comparatively highly loaded regions, such as, for example, in the interior of the combustion chamber of a gas turbine, such armored machine components are therefore only of limited suitability.
Der Erfindung liegt daher die Aufgabe zugrunde, eine Maschi¬ nenkomponente der oben genannten Art anzugeben, die auch für den Einsatz in einem thermisch vergleichsweise hoch belaste- ten Bereich einer Arbeitsmaschine besonders geeignet ist. Des Weiteren soll eine Gasturbine mit einer Anzahl derartiger Maschinenkomponenten angegeben werden.The invention is therefore based on the object, a Maschi nenkomponente ¬ indicate the type mentioned above, which is particularly suitable for use in a thermally relatively highly belaste- th area of a work machine. Furthermore, a gas turbine with a number of such machine components is to be specified.
Hinsichtlich der Maschinenkomponente wird diese Aufgabe er- findungsgemäß gelöst, indem die Panzerung segmentiert ausge¬ führt und von einer Anzahl von Panzerungssegmenten gebildet ist .With respect to the machine component this object is achieved according to the invention ER- by segmented armor leads out ¬ and is formed from a number of cladding segments.
Die Erfindung geht dabei von der Überlegung aus, dass die Ma- schinenkomponente für eine grundsätzliche Einsetzbarkeit un¬ ter Einhaltung verschleißarmer Arbeitsbedingungen mit einer geeigneten Panzerung versehen sein sollte. Um die damit einhergehenden Nachteile insbesondere hinsichtlich der Weiter- verarbeitbarkeit und auch der Stabilität gegenüber thermi- scher Beanspruchung zu vermeiden, sollte die laterale Ausdehnung der Panzerung besonders gering gehalten werden. Um dabei dennoch einen ausreichend großen Teilbereich der Oberfläche abdecken zu können, sollten einzelne Zonen der Panzerung voneinander entkoppelt ausgeführt werden, um somit ausreichende Nachgiebigkeit gegenüber thermischer Verformung und dergleichen zu ermöglichen. Dazu sollte die Panzerung segmentweise ausgeführt sein. Die Panzerungssegmente können durch geeignete Techniken auf dem Grundkörper der Maschinenkomponente aufgebracht sein. Vorteilhafterweise sind die Panzerungssegmente jedoch durch Auftragsschweißen auf den Grundkörper aufgebracht, so dass eine besonders innige Verbindung zum Grundkörper und somit eine hohe Stabilität der Maschinenkomponente insgesamt er¬ reicht ist.The invention is based on the consideration that the machine-component should be provided for a fundamental applicability un ¬ ter compliance with low-wear working conditions with a suitable armor. In order to avoid the associated disadvantages, in particular with regard to further processability and also the stability against thermal stress, the lateral extent of the armor should be kept particularly low. In order nevertheless to be able to cover a sufficiently large subarea of the surface, individual zones of the armor should be executed decoupled from one another, in order thus to allow sufficient resilience to thermal deformation and the like. For this, the armor should be executed segment by segment. The armor segments may be applied by suitable techniques on the base of the machine component. Advantageously, however, the armor segments are applied by build-up welding on the base body, so that a particularly intimate connection to the base body and thus a high stability of the machine component as a whole he ¬ is enough.
Die Panzerungssegmente können auf eine äußere Oberfläche des Grundkörpers aufgebracht sein, so dass die hierdurch entste¬ hende Kontur im Wesentlichen eine Mehrzahl von durch die Panzerungssegmente gegebene Ausbuchtungen auf der Oberfläche der Schienenkomponente aufweist. Um jedoch für das Bauteil oder die Maschinenkomponente die Einhaltung geforderter Maße oder auch die Bereitstellung einer nach außen hin glatten Oberfläche zu ermöglichen, sind die Panzerungssegmente vorteilhaf¬ terweise jeweils in zugeordnete Vertiefungen in den Grundkörper eingebracht oder eingebettet. Dadurch ist vorteilhafterweise insgesamt eine nahezu ebene Gesamtoberfläche der Ma- schinenkomponente erreichbar, wobei insbesondere die äußere Oberfläche der Panzerungssegmente und die äußere Oberfläche der zwischen den Panzerungssegmenten verlaufenden Stege des Grundkörpers eine durchgängige Oberfläche bilden.The armor segments can be applied to an outer surface of the base body, so that the resulting entste ¬ rising contour has a plurality of given by the armor segments bulges on the surface of the rail component substantially. However, in order to allow for the component or the machine component compliance with required dimensions or the provision of an outwardly smooth surface, the armor segments are vorteilhaf ¬ terweise introduced or embedded in associated recesses in the body. As a result, a virtually even overall surface of the machine component can advantageously be achieved overall, with the outer surface of the armor segments in particular and the outer surface of the webs of the base body extending between the armor segments forming a continuous surface.
Vorteilhafterweise kommen Maschinenkomponenten der genannten Art in einer Gasturbine, insbesondere als Flammrohr einer Brennkammer, als Mischgehäuse eines Brenners und/oder als In¬ nengehäuse einer Brennkammer zum Einsatz. Dabei können insbesondere auch benachbart zueinander positionierte Bauteile oder Maschinenkomponenten derartig gepanzert ausgeführt sein, wobei vorteilhafterweise der gepanzerte Teilbereich der Ober¬ fläche einer ersten Maschinenkomponente benachbart zum gepan¬ zerten Teilbereich der Oberfläche einer zweiten Maschinenkomponente angeordnet ist. In besonders vorteilhafter Ausge- staltung weist dabei das Auftragsmaterial der ersten Maschi¬ nenkomponente eine andere Härte auf als das Auftragsmaterial der zweiten Maschinenkomponente. Durch geeignete Materialwahl ist es somit möglich, bei auftretendem Kontakt der beiden Ma- schinenkomponenten miteinander den Verschleiß gezielt auf eine der beiden Maschinenkomponenten - nämlich diejenige mit der Panzerung geringerer Härte - zu fokussieren, wobei dazu insbesondere die leichter austauschbare oder reparierbare Maschinenkomponente gewählt werden kann.Advantageously, come machine components of the said type in a gas turbine, in particular a flame tube of a combustion chamber as a mixing housing a burner and / or as in ¬ nengehäuse a combustor used. In this case can be designed such armored particular also adjacent to each other positioned components or machine components, wherein the reinforced portion, advantageously the upper ¬ surface of a first machine component adjacent to Gepan ¬ zerten portion of the surface of a second machine component is arranged. In a particularly advantageous excluded staltung this, the coating material of the first Maschi ¬ nenkomponente a different hardness than the coating material of the second machine component. By a suitable choice of material, it is thus possible, in the event of contact between the two Machine components with each other specifically to focus the wear on one of the two machine components - namely the one with the armor of lesser hardness - in particular the more easily replaceable or repairable machine component can be selected.
Die mit der Erfindung erzielten Vorteile bestehen insbesondere darin, dass durch die segmentierte Ausführung der Panze¬ rung der Maschinenkomponente auch bei nur kleinen Toleranzbe- reichen eine Anbringung der Panzerung auf den Grundkörper überhaupt erst ermöglicht wird, wobei gerade im Hinblick auf die segmentierte Ausführung der Panzerung ein Verzug des Grundkörpers infolge der hohen Arbeitstemperaturen beim Auftragsschweißen weitgehend vermieden werden kann. Durch die segmentierte Ausführung der Panzerung wird zudem eine Riss¬ bildung bei der Aufbringung der Panzerung vermieden, die bei durchgehender Schweißung der Panzerung auftreten könnte. Zudem wird ein nachträgliches Biegen des Bauteils ermöglicht, ohne dass das Auftragsmaterial dabei zu stark beansprucht würde. Des Weiteren sind Verformungen und Verbindungsschweis- sungen während der Montage und im Betrieb vergleichsweise einfach durchzuführen, ohne dass kritische Auswirkungen auf das Bauteil zu befürchten sind.The advantages achieved by the invention are in particular that the segmented design of the Panze ¬ tion of the machine component even with only small tolerance ranges attaching the armor on the body in the first place is possible, especially with regard to the segmented execution of the armor a distortion of the body due to the high operating temperatures during buildup welding can be largely avoided. Through the segmented design of the armor also crack ¬ education in the application of armor is avoided, which could occur with continuous welding of the armor. In addition, a subsequent bending of the component is made possible without the order material would be too stressed. Furthermore, deformations and connection welds during installation and operation are comparatively easy to carry out, without any critical effects on the component to be feared.
Durch die Anbringung der Panzerungssegmente in in den Grund¬ körper eingearbeitete Vertiefungen kann die Oberfläche der Maschinenkomponente im Nachhinein homogenisiert werden, wobei ein möglicher Überstand nach dem Auftragsschweißen auch nachträglich entfernt werden kann. Dabei kann insbesondere bei angepasster Bauteilgeometrie die Einhaltung extern vorgegebe¬ ner Maße sichergestellt werden. Die segmentierte Aufbringung der Panzerung reduziert zudem die Belastung des Bauteils bei der Fertigung, Montage und im Betrieb.By attaching the armor segments in the basic ¬ body incorporated recesses, the surface of the machine component can be homogenized in retrospect, with a possible supernatant after the deposition welding can also be subsequently removed. The compliance with externally-giving ¬ ner dimensions can be ensured particularly for matched component geometry. The segmented application of the armor also reduces the load on the component during manufacture, assembly and operation.
Gerade bei der Anwendung bei Turbinen, insbesondere Gasturbi¬ nen, kann zudem durch geeignete Materialwahl bei der paarweisen Panzerung von Komponentenpaaren durch geeignete Wahl unterschiedlicher Härten der Verschleiß auf eine der beiden ge- paarten Komponenten fokussiert werden, so dass eine nachträg¬ liche Wartung und ein Austausch betroffener Komponenten bedeutend erleichtert werden kann.Especially in the application to turbines, in particular NEN Gasturbi ¬, can also overall by suitable material choice for the pairwise armoring component couples through a suitable choice of different hardnesses, the wear on one of the two coupled components are focussed, so that a nachträg ¬ Liche maintenance and replacement of affected components can be significantly facilitated.
Ein Ausführungsbeispiel der Erfindung wird anhand einer Zeichnung näher erläutert. Darin zeigen:An embodiment of the invention will be explained in more detail with reference to a drawing. Show:
FIG 1 einen Längsschnitt durch eine Gasturbine,1 shows a longitudinal section through a gas turbine,
FIG 2 einen Schnitt durch eine Brennkammer bei Gas¬ turbinen nach FIG 1, und2 shows a section through a combustion chamber in gas ¬ turbines according to FIG 1, and
FIG 3 bis 5 jeweils Maschinenkomponenten der Gasturbine nach FIG 1.3 to 5 respectively machine components of the gas turbine according to FIG. 1
Gleiche Teile sind in allen Figuren mit denselben Bezugszei¬ chen versehen.Identical parts are provided in all figures with the same Bezugszei ¬ chen.
Die Gasturbine 1 gemäß FIG 1 weist einen Verdichter 2 für Verbrennungsluft, eine Brennkammer 4 sowie eine Turbine 6 zum Antrieb des Verdichters 2 und eines nicht dargestellten Gene¬ rators oder einer Arbeitsmaschine auf. Dazu sind die Turbi¬ ne 6 und der Verdichter 2 auf einer gemeinsamen, auch als Turbinenläufer bezeichneten Turbinenwelle 8 angeordnet, mit der auch der Generator bzw. die Arbeitsmaschine verbunden ist, und die um ihre Mittelachse 9 drehbar gelagert ist.The gas turbine 1 according to FIG 1 comprises a compressor 2 for combustion air, a combustion chamber 4 and a turbine 6 to drive the compressor 2 and a Gene ¬ rators not shown or a work machine. For this purpose the Turbi ¬ are ne 6 and the compressor 2 arranged on a common, also referred to as the turbine rotor turbine shaft 8, is connected to the generator or the driven machine, and which is mounted rotatably about its central axis. 9
Die Brennkammer 4 ist mit einer Anzahl von Brennern 10 zur Verbrennung eines flüssigen oder gasförmigen Brennstoffs be- stückt. Sie ist weiterhin an ihrer Innenwand mit nicht näher dargestellten Hitzeschildelementen versehen.The combustion chamber 4 is equipped with a number of burners 10 for combustion of a liquid or gaseous fuel. It is also provided on its inner wall with heat shield elements not shown.
Die Turbine 6 weist eine Anzahl von mit der Turbinenwelle 8 verbundenen rotierbaren Laufschaufeln 12 auf. Die Laufschau- fein 12 sind kranzförmig an der Turbinenwelle 8 angeordnet und bilden somit eine Anzahl von Laufschaufelreihen . Weiterhin umfasst die Turbine 6 eine Anzahl von feststehenden Leit¬ schaufeln 14, die ebenfalls kranzförmig unter Bildung von Leitschaufelreihen an einem Innengehäuse 16 der Turbine 6 befestigt sind. Die Laufschaufeln 12 dienen dabei zum Antrieb der Turbinenwelle 8 durch Impulsübertrag von einem die Tur¬ bine 6 durchströmenden Arbeitsmedium M. Die Leitschaufeln 14 dienen hingegen zur Strömungsführung des Arbeitsmediums M zwischen jeweils zwei in Strömungsrichtung des Arbeitsmediums M gesehen aufeinander folgenden Laufschaufelreihen oder Laufschaufelkränzen. Ein aufeinander folgendes Paar aus einem Kranz von Leitschaufeln 14 oder einer Leitschaufelreihe und aus einem Kranz von Leitschaufeln 12 oder einer Laufschaufelreihe wird dabei auch als Turbinenstufe bezeichnet.The turbine 6 has a number of rotatable blades 12 connected to the turbine shaft 8. The runners 12 are arranged in a ring shape on the turbine shaft 8 and thus form a number of blade rows. Furthermore, the turbine 6 comprises a number of fixed Leit ¬ blades 14, which also wreath-shaped to form Guide vanes are attached to an inner housing 16 of the turbine 6. The blades 12 serve to drive the turbine shaft 8 by momentum transfer from a tur ¬ bine 6 flowing through the working medium M. The vanes 14, however, serve to flow the working medium M between two seen in the flow direction of the working medium M consecutive blade rows or blade rings. A successive pair of a ring of vanes 14 or a row of vanes and a ring of vanes 12 or a blade row is also referred to as a turbine stage.
Jede Leitschaufel 14 weist eine Plattform 18 auf, die zur Fixierung der jeweiligen Leitschaufel 14 am Innengehäuse 16 der Turbine 6 als Wandelement angeordnet ist. Die Platt¬ form 18 ist dabei ein thermisch vergleichsweise stark belas¬ tetes Bauteil, das die äußere Begrenzung eines Heißgaskanals für das die Turbine 6 durchströmende Arbeitmedium M bildet. Jede Laufschaufel 12 ist in analoger Weise über eine auch als Schaufelfuß bezeichnete Plattform 20 an der Turbinenwelle 8 befestigt .Each vane 14 has a platform 18, which is arranged to fix the respective vane 14 on the inner housing 16 of the turbine 6 as a wall element. The plate ¬ form 18 is a thermally comparatively heavily belas ¬ tetes component that forms the outer boundary of a hot gas channel for the turbine 6 flowing through the working medium M. Each blade 12 is attached to the turbine shaft 8 in an analogous manner via a platform 20, also referred to as a blade root.
Zwischen den beabstandet voneinander angeordneten Plattformen 18 der Leitschaufeln 14 zweier benachbarter Leitschaufel- reihen ist jeweils ein Führungsring 21 am Innengehäuse 16 der Turbine 6 angeordnet. Die innere Oberfläche jedes Führungs¬ rings 21 ist dabei ebenfalls dem heißen, die Turbine 6 durch¬ strömenden Arbeitsmedium M ausgesetzt und in radialer Richtung vom äußeren Ende 22 der ihm gegenüberliegenden Lauf- schaufeln 12 einer Laufschaufelreihe durch einen Spalt 24 beabstandet .Between the spaced-apart platforms 18 of the guide vanes 14 of two adjacent Leitschaufel- rows each having a guide ring 21 on the inner housing 16 of the turbine 6 is arranged. The inner surface of each guide ¬ rings 21 is also the hot, exposed through the turbine 6 ¬ flowing working medium M, and in the radial direction from the outer end 22 of the opposite him running blades 12 of a rotor blade row by a gap 24th
Wie der vergrößerten Darstellung in FIG 2 entnehmbar ist, ist jeder der Brennkammer 4 in seinem Einströmbereich, an dem eine Anzahl von nicht näher spezifizierten Zuführungsleitungen für Medien, wie Brennstoff und Verbrennungsluft ange¬ schlossen sind, in seinem Inneren mit einem so genannten Flammrohr 30 ausgerüstet, innerhalb dessen die Verbrennung des Brennstoffs stattfindet. Über ein ebenfalls innerhalb des Gehäuses 32 des jeweiligen Brenners 10 angeordnetes, auch als Mischgehäuse bezeichnetes Übergangsstück 34 ist das Flammrohr 30 ausgangsseitig verbunden mit einem Mischgehäuse 34 der Brennkammer 4.As the enlarged view is removable in FIG 2, each of the combustion chamber 4 is in its inflow area to which a number of unspecified supply lines for media, such as fuel and combustion air is ¬ included are equipped in its interior with a so-called flame tube 30 within which the combustion of the fuel takes place. Via a likewise arranged within the housing 32 of the respective burner 10, also referred to as mixing housing transition piece 34, the flame tube 30 is connected on the output side to a mixing housing 34 of the combustion chamber. 4
Das Flammrohr 30, das Übergangsstück 34 und das Innengehäu¬ se 36 sind dabei in der Art ineinander gesteckter Rohre mit¬ einander verbunden, so dass eine zuverlässige Medienstrom- führung vom Flammrohr 30 in das Innengehäuse 36 der Brennkammer 4 gewährleistet ist. Die jeweils ineinander gesteckten Rohrenden sind dabei unter Einhaltung der vorgegebenen Maße und Toleranzen möglichst berührungsfrei voneinander positio¬ niert, so dass ein Verschleiß aufgrund von in Kontakt mitein- ander geratenden Komponenten und aneinander reibenden Komponenten möglichst vermieden ist. Allerdings lässt sich be¬ triebsbedingt beim Betrieb der Gasturbine 1 ein immer wieder¬ kehrender Kontakt dieser Komponenten miteinander nicht vermeiden, so dass in jedem Fall mit einem Restverschleiß zu rechnen ist. Um diesem Verschleiß Rechnung zu tragen, ist im Rahmen von Wartungs- und Inspektionsarbeiten eine regelmäßige Überprüfung und gegebenenfalls ein Austausch dieser Komponenten erforderlich.The flame tube 30, the transition piece 34 and the Innengehäu ¬ se 36 are connected in the nature of nested tubes with ¬ each other, so that a reliable media flow management is ensured by the flame tube 30 in the inner housing 36 of the combustion chamber 4. The respectively inserted tube ends are thereby positio ¬ niert as possible contact-free from each other in compliance with the predetermined dimensions and tolerances, so that wear due to coming in contact with each other components and rubbing together components as possible avoided. However, it can drive caused during operation of the gas turbine 1, a constantly recurring ¬ contact of these components do not avoid each other, so that in any case likely to be a residual wear ¬. To account for this wear, regular inspection and replacement of these components is required as part of maintenance and inspection work.
Um den betrieblichen Aufwand der Gasturbine 1 besonders ge¬ ring zu halten und die erforderlichen Inspektions- und Wartungsarbeiten weitgehend zu vereinfachen, sind die Komponenten der Gasturbine 1 möglichst verschleißarm ausgelegt. Um dabei dem durch Kontakt der Maschinenkomponenten Flamm- röhr 30, Übergangsstück 34 und Innengehäuse 36 bedingten Verschleiß Rechnung zu tragen und gerade diesen Verschleiß bei auftretenden Kontakten der Komponenten miteinander besonders gering zu halten, sind die genannten Maschinenkomponenten als gepanzerte Komponenten ausgeführt. Dazu ist jede der Maschi- nenkomponenten Flammrohr 30, Übergangsstück 34 und Innengehäuse 36 aus einem aus Grundmaterial gefertigten Grundkörper 40 aufgebaut, der in einem jeweils in den FIG 3 bis 6 darge¬ stellten Teilbereich seiner Oberfläche mit einer Panzerung 42 aus einem Auftragsmaterial versehen ist. Das Auftragsmaterial ist dabei derart gewählt, dass es im Vergleich zum Grundmaterial eine größere Härte aufweist, so dass eine er¬ höhte Widerstandsfähigkeit gegenüber mechanischer und auch thermischer Belastung gegeben ist. Das Auftragsmaterial ist dabei jeweils durch Auftragsschweißen auf den Grundkörper 40 aufgebracht .In order to keep the operating costs of the gas turbine 1 particularly low and to simplify the required inspection and maintenance work to a large extent, the components of the gas turbine 1 are designed to be as wear-resistant as possible. In order to take into account the wear caused by contact of the machine components flame tube 30, transition piece 34 and inner housing 36, and to keep this wear particularly small when contacts of the components occur, the machine components mentioned are designed as armored components. For this purpose, each of the engine components flame tube 30, transition piece 34 and inner housing 36 is constructed of a base body 40 made of base material, which in an in each case in Figures 3 to 6 Darge ¬ presented portion of its surface with an armor 42nd is provided from a job material. The application material is chosen such that it has a greater hardness compared to the base material, so that he he ¬ increased resistance to mechanical and thermal stress is given. The application material is applied to the base body 40 in each case by build-up welding.
Um eine Beeinträchtigung der Fertigung, der Montage und auch des Betriebs der jeweiligen Maschinenkomponenten durch die Panzerung 42 zu vermeiden, wie sie beispielsweise durch das unterschiedliche thermische Ausdehnungsverhalten und damit verbundene Rissbildung beim eigentlichen Schweißvorgang oder auch beim Betrieb bei erhöhter thermischer Belastung auftre- ten könnte, ist die Panzerung 42 der jeweiligen Maschinenkomponente segmentiert ausgeführt. Dazu umfasst die Panzerung 42 eine Mehrzahl von Panzerungssegmenten 44, wobei die Dimensionierung im Hinblick auf die Dimensionierung der eigentlichen Maschinenkomponente und die verwendeten Materialien derart gewählt ist, dass durch die lateral begrenzte Ausdehnung die jeweiligen Panzerungssegmente 44 eine zu große Beeinträchti¬ gung des Grundkörpers 40 durch unterschiedliches thermisches Ausdehnungsverhalten und dergleichen vermieden ist.In order to avoid an impairment of the manufacture, assembly and also of the operation of the respective machine components by the armor 42, as might occur, for example, due to the different thermal expansion behavior and associated crack formation in the actual welding operation or also during operation under increased thermal load, the armor 42 is executed segmented the respective machine component. For this purpose, the armor 42 comprises a plurality of armor segments 44, wherein the dimensioning with respect to the dimensioning of the actual machine component and the materials used is chosen such that the laterally limited extent the respective armor segments 44 too large impairment ¬ tion of the base body 40 through different thermal expansion behavior and the like is avoided.
Wie der Darstellung in FIG 3 entnehmbar ist, sind die Panze¬ rungssegmente 44 jeweils in zugeordnete Vertiefungen im Grundkörper 40 eingebracht. Die Vertiefungen können dabei durch geeignete Bearbeitungsverfahren, wie beispielsweise durch Fräsen, Drehen oder Schleifen eingebracht worden sein. Die Dimensionierung kann dabei grundsätzlich derart vorgenommen werden, dass auf eine plane Oberfläche des Grundkörpers 40 die Panzerungssegmente 44 aufgebracht werden und dement¬ sprechend ihrer Dicke entsprechende Vertiefungen zwischen ihnen entstehen. Bei der Anbringung der Panzerungssegmente 44 kann die Anfertigung jedoch auch, wie dies in den FIG 3 bis 6 gezeigt ist, derart erfolgen, dass die äußere Oberfläche der Panzerungssegmente 44 mit der äußeren Oberfläche der zwischen den äußeren Panzerungssegmenten 44 verlaufenden Stege 46 des Grundkörpers 40 eine durchgängige und somit plane Oberfläche bilden. Als fertige Maschinenkomponente entsteht dabei ein Bauteil, das hinsichtlich seiner Formgebung, Dimensionierung und Maßhaltigkeit einem ursprünglich vorgesehenen Bauteil weitestgehend entspricht und insbesondere eine entsprechend glatte und planare Oberfläche aufweist.As the display is removed in FIG 3, which are approximately Panze ¬ segments 44 each in associated recesses in the base body 40 is introduced. The recesses may have been introduced by suitable machining methods, such as by milling, turning or grinding. The dimensions can in principle be carried out in such a way here that the cladding segments 44 are applied to a planar surface of the base body 40 and corresponding ¬ speaking their thickness corresponding recesses are formed between them. When attaching the armor segments 44, however, the preparation can also, as shown in Figures 3 to 6, carried out such that the outer surface of the armor segments 44 with the outer surface of extending between the outer armor segments 44 webs 46 of Base body 40 form a continuous and thus planar surface. As a finished machine component thereby creates a component which largely corresponds to an originally provided component in terms of its shape, dimensioning and dimensional stability and in particular has a correspondingly smooth and planar surface.
In FIG 4 ist gezeigt, dass auch ein gebogener Kühlluftring 50 als zumindest teilweise gepanzerte Maschinenkomponente der genannten Art ausgeführt sein kann. Der Kühlluftring 50 ist dabei an seiner Oberfläche ebenfalls mit Panzerungssegmen¬ ten 44 versehen, die in entsprechende Vertiefungen des den Kühlluftring 50 bildenden Grundkörpers 40 eingearbeitet sind. Im Grundkörper 40 des Kühlluftrings 50 sind dabei zusätzlich noch Kühlluftkanäle 52 vorgesehen, die durch entsprechende Bohrungen gebildet sind. Durch die Ausformung der auch als Taschen bezeichneten Vertiefungen, in denen die Panzerungssegmente 44 dabei angeordnet sind, kann die gewünschte Geo¬ metrie des Kühlluftrings 50 beibehalten werden. Dennoch wird auch bei Verwendung der Panzerungssegmente 44 eine nahezu ebene Oberfläche und ein ebener Übergang zum Grundkörper 40 geschaffen. Dadurch ist eine verstärkte Verschleißreduktion und eine verbesserte Bindung zwischen den verwendeten Materialien gewährleistet.FIG. 4 shows that a bent cooling air ring 50 can also be embodied as an at least partially armored machine component of the type mentioned. The cooling air ring 50 is also provided on its surface with Panzerssegmen ¬ th 44 which are incorporated into corresponding recesses of the cooling air ring 50 forming body 40. In the main body 40 of the cooling air ring 50 cooling air channels 52 are additionally provided, which are formed by corresponding holes. By forming the recesses, also called pockets, in which the cladding segments 44 are thereby arranged, the desired Geo ¬ be maintained geometry 50 of the cooling air ring. Nevertheless, an almost even surface and a smooth transition to the base body 40 is created even when using the armor segments 44. This ensures increased wear reduction and improved bonding between the materials used.
In FIG 5 ist gezeigt, dass als derartig gepanzerte Maschinen¬ komponenten insbesondere das Übergangsstück 34 und das Flammrohr 30 der Gasturbine 1 in ihrem überlappenden Bereich ausgeführt sind. Panzerungen 42 dieser Maschinenkomponenten sind dabei jeweils auf den einander zugewandten Oberflächensegmenten vorgesehen. Bei einer derartigen benachbarten Anordnung zweier derartig gepanzerter Maschinenkomponenten ist zudem, wie dies vorliegend für das Übergangsstück 34 und das Flamm¬ rohr 30 vorgesehen ist, durch eine geeignete Materialwahl für die Panzerungen 42 eine gezielte Fokussierung des Verschleißes auf eine der beiden Maschinenkomponenten, insbesondere auf die leichter austauschbare Maschinenkomponente, ermöglicht. Dazu ist vorliegend gezielt vorgesehen, das Auf- tragsmaterial für die Panzerung 42 des Flammrohres 30 von ge¬ ringerer Härte zu wählen als das Material für die Panze¬ rung 42 des Übergangsstücks 34. In FIG 5 it is shown that components such as armored machines ¬ particular, the transition piece 34 and the flame tube 30 of the gas turbine 1 in their overlapping area are executed. Armor 42 of these machine components are provided in each case on the facing surface segments. In such an adjacent arrangement of two such armored machine components is also, as is provided here for the transition piece 34 and the flame ¬ tube 30, by a suitable choice of material for the armor 42 targeted focusing of wear on one of the two machine components, in particular on the easily replaceable machine component, allows. For this purpose, it is purposefully provided in the present case The material for the armor 42 of the flame tube 30 of ge ¬ ringerer hardness to choose as the material for the Panze ¬ tion 42 of the transition piece 34th

Claims

Patentansprüche claims
1. Maschinenkomponente mit einem aus einem Grundmaterial ge¬ fertigten Grundkörper (40 ), der in einem Teilbereich seiner Oberfläche mit einer Panzerung (42) aus einem Auftragsma¬ terial mit einer im Vergleich zum Grundmaterial größeren Härte versehen ist, wobei die Panzerung (42) segmentiert ausgeführt und von einer Anzahl von Panzerungssegmenten (44) gebildet ist.1. Machine component comprising a ge of a base material ¬ produced base body (40) which is provided in a portion of its surface with a plating (42) consists of a Auftragsma ¬ material including greater than the basic material hardness, wherein the armor (42) segmented and formed by a number of armor segments (44).
2. Maschinenkomponente nach Anspruch 1, bei der die Panze¬ rungssegmente (44) durch Auftragsschweißen auf den Grundkörper (40) aufgebracht sind.2. Machine component according to claim 1, wherein the Panze ¬ tion segments (44) by deposition welding on the base body (40) are applied.
3. Maschinenkomponente nach Anspruch 1 oder 2, bei der die3. Machine component according to claim 1 or 2, wherein the
Panzerungssegmente (44) jeweils in zugeordnete Vertiefun¬ gen im Grundkörper (40) eingebracht sind.Armor segments (44) each in associated Vertiefun ¬ conditions in the base body (40) are introduced.
4. Maschinenkomponente nach Anspruch 3, bei der die äußere Oberfläche der Panzerungssegmente (44) und die äußere4. Machine component according to claim 3, wherein the outer surface of the armor segments (44) and the outer
Oberfläche der zwischen den Panzerungssegmenten (44) verlaufenden Stege (46) des Grundkörpers (40) eine durchgän¬ gige Oberfläche bilden.Surface of between the armor segments (44) extending webs (46) of the base body (40) form a durchgän ¬ gige surface.
5. Gasturbine (1) mit einer Anzahl von Maschinenkomponenten nach einem der Ansprüche 1 bis 4.5. Gas turbine (1) with a number of machine components according to one of claims 1 to 4.
6. Gasturbine (1) nach Anspruch 5, bei der der gepanzerte Teilbereich der Oberfläche einer ersten Maschinenkompo- nente benachbart zum gepanzerten Teilbereich der Oberfläche einer zweiten Maschinenkomponente angeordnet ist, wo¬ bei das Auftragsmaterial der ersten Maschinenkomponente eine andere Härte aufweist als das Auftragsmaterial der zweiten Maschinenkomponente.6. Gas turbine (1) according to claim 5, wherein the armored portion of the surface of a first machine component adjacent to the armored portion of the surface of a second machine component is arranged, where ¬ in the application material of the first machine component has a different hardness than the application material of second machine component.
7. Gasturbine nach Anspruch 5 oder 6, bei dem ein Flammrohr7. Gas turbine according to claim 5 or 6, wherein a flame tube
(30) einer Brennkammer (4), ein Mischgehäuse (34) einer Brennkammer (4) und/oder ein Innengehäuse einer Brennkam- mer (4) als Maschinenkomponenten nach einem der Ansprüche 1 bis 4 ausgestaltet sind. (30) a combustion chamber (4), a mixing housing (34) of a combustion chamber (4) and / or an inner housing of a combustion chamber (4) Mer (4) are designed as machine components according to one of claims 1 to 4.
EP07728485A 2006-06-06 2007-04-25 Gas turbine comprising armor-plated machine components Active EP2024684B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07728485A EP2024684B1 (en) 2006-06-06 2007-04-25 Gas turbine comprising armor-plated machine components

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP06011629A EP1865258A1 (en) 2006-06-06 2006-06-06 Armoured engine component and gas turbine
PCT/EP2007/054029 WO2007141091A1 (en) 2006-06-06 2007-04-25 Armor-plated machine components and gas turbines
EP07728485A EP2024684B1 (en) 2006-06-06 2007-04-25 Gas turbine comprising armor-plated machine components

Publications (2)

Publication Number Publication Date
EP2024684A1 true EP2024684A1 (en) 2009-02-18
EP2024684B1 EP2024684B1 (en) 2009-12-09

Family

ID=37560775

Family Applications (2)

Application Number Title Priority Date Filing Date
EP06011629A Withdrawn EP1865258A1 (en) 2006-06-06 2006-06-06 Armoured engine component and gas turbine
EP07728485A Active EP2024684B1 (en) 2006-06-06 2007-04-25 Gas turbine comprising armor-plated machine components

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP06011629A Withdrawn EP1865258A1 (en) 2006-06-06 2006-06-06 Armoured engine component and gas turbine

Country Status (7)

Country Link
US (1) US8091366B2 (en)
EP (2) EP1865258A1 (en)
CN (1) CN101473171B (en)
AT (1) ATE451581T1 (en)
DE (1) DE502007002275D1 (en)
RU (1) RU2451241C2 (en)
WO (1) WO2007141091A1 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2068082A1 (en) * 2007-12-04 2009-06-10 Siemens Aktiengesellschaft Machine components and gas turbines
EP2899464B1 (en) * 2014-01-22 2017-01-11 Siemens Aktiengesellschaft Silo combustion chamber for a gas turbine
DE102017207392A1 (en) 2017-05-03 2018-11-08 Siemens Aktiengesellschaft Silo combustion chamber and method for converting such

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3476283A (en) * 1968-07-05 1969-11-04 Universal Oil Prod Co Internally insulated and lined pressure vessel
GB1450894A (en) * 1972-11-01 1976-09-29 Lucas Industries Ltd Flame tubes
JPS55107310U (en) * 1979-01-23 1980-07-26
US4289447A (en) * 1979-10-12 1981-09-15 General Electric Company Metal-ceramic turbine shroud and method of making the same
US4688310A (en) * 1983-12-19 1987-08-25 General Electric Company Fabricated liner article and method
FR2572394B1 (en) * 1984-10-30 1986-12-19 Snecma METHOD FOR MANUFACTURING A CERAMIC TURBINE RING INTEGRATED WITH AN ANNULAR METAL SUPPORT
EP0224817B1 (en) * 1985-12-02 1989-07-12 Siemens Aktiengesellschaft Heat shield arrangement, especially for the structural components of a gas turbine plant
US4706453A (en) * 1986-11-12 1987-11-17 General Motors Corporation Support and seal assembly
US5024058A (en) * 1989-12-08 1991-06-18 Sundstrand Corporation Hot gas generator
ES2073182T3 (en) * 1990-11-29 1995-08-01 Siemens Ag CERAMIC THERMAL SHIELD IN A SUPPORTING STRUCTURE.
DE4238369C2 (en) * 1992-11-13 1996-09-26 Mtu Muenchen Gmbh Component made of a metallic base substrate with a ceramic coating
RU2088764C1 (en) * 1993-12-02 1997-08-27 Яков Петрович Гохштейн Turbine blade
US6190124B1 (en) * 1997-11-26 2001-02-20 United Technologies Corporation Columnar zirconium oxide abrasive coating for a gas turbine engine seal system
JP3801452B2 (en) * 2001-02-28 2006-07-26 三菱重工業株式会社 Abrasion resistant coating and its construction method
US6703137B2 (en) * 2001-08-02 2004-03-09 Siemens Westinghouse Power Corporation Segmented thermal barrier coating and method of manufacturing the same
DE10326541A1 (en) * 2003-06-12 2005-01-05 Mtu Aero Engines Gmbh A method for blade tip armor of the blades of a gas turbine engine and apparatus for performing the method
DE102004001722A1 (en) * 2004-01-13 2005-08-04 Mtu Aero Engines Gmbh Turbomachine blade and method of making blade tip armor on turbomachinery blades

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2007141091A1 *

Also Published As

Publication number Publication date
CN101473171A (en) 2009-07-01
US8091366B2 (en) 2012-01-10
EP2024684B1 (en) 2009-12-09
US20090180873A1 (en) 2009-07-16
RU2008152379A (en) 2010-07-20
WO2007141091A1 (en) 2007-12-13
CN101473171B (en) 2011-04-06
DE502007002275D1 (en) 2010-01-21
ATE451581T1 (en) 2009-12-15
EP1865258A1 (en) 2007-12-12
RU2451241C2 (en) 2012-05-20

Similar Documents

Publication Publication Date Title
EP1443275B1 (en) Combustion chamber
EP2260180B1 (en) Guide vane for a gas turbine
EP2084368B1 (en) Turbine blade
EP1947293A1 (en) Guide vane for a gas turbine
EP1904717B1 (en) Hot gas-conducting housing element, protective shaft jacket, and gas turbine system
EP1180197A1 (en) Sealing system for a rotor of a turbo engine
EP1409926A1 (en) Baffle cooling device
EP2411631B1 (en) Sealplate and rotor blade system
EP2507557B1 (en) Burner assembly
WO2009040286A1 (en) Gas turbine having welded combustion chamber shells
EP2024684B1 (en) Gas turbine comprising armor-plated machine components
EP2762782A1 (en) Holding element for holding a heat shield stone to a support structure
EP2362142A1 (en) Burner assembly
EP1429077B1 (en) Gas turbine
WO2010049195A1 (en) Gas turbine having cooling insert
EP1588102B1 (en) Heat shield element, combustion chamber and gas turbine
EP2215405B1 (en) Machine component and gas turbine
EP1914382B1 (en) Method for repairing a turbine blade
DE102012204777B4 (en) Method for producing a cladding element and cladding element
EP1486730A1 (en) Heatshield Element
EP1731715A1 (en) Transition between a combustion chamber and a turbine
EP1662090B1 (en) Gas turbine blade
EP1398462A1 (en) Gas turbine and transition piece
EP1624156B1 (en) Gas or steam turbine with a stress-resistant component
DE102020201448A1 (en) Additively manufactured turbine blade with anti-twist device and adjustment process

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20081111

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK RS

17Q First examination report despatched

Effective date: 20090318

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RTI1 Title (correction)

Free format text: GAS TURBINE COMPRISING ARMOR-PLATED MACHINE COMPONENTS

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

REF Corresponds to:

Ref document number: 502007002275

Country of ref document: DE

Date of ref document: 20100121

Kind code of ref document: P

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20091209

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20091209

LTIE Lt: invalidation of european patent or patent extension

Effective date: 20091209

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20091209

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20091209

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20091209

REG Reference to a national code

Ref country code: IE

Ref legal event code: FD4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100320

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100409

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20091209

Ref country code: IE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20091209

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20091209

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100409

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100309

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20091209

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20091209

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20091209

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100310

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20091209

BERE Be: lapsed

Owner name: SIEMENS A.G.

Effective date: 20100430

26N No opposition filed

Effective date: 20100910

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20100430

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20091209

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20100425

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20100430

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20091209

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20100425

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20100610

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20091209

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 451581

Country of ref document: AT

Kind code of ref document: T

Effective date: 20120425

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20120425

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 9

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20150415

Year of fee payment: 9

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20161230

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20160502

REG Reference to a national code

Ref country code: CH

Ref legal event code: PCOW

Free format text: NEW ADDRESS: WERNER-VON-SIEMENS-STRASSE 1, 80333 MUENCHEN (DE)

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502007002275

Country of ref document: DE

Owner name: SIEMENS ENERGY GLOBAL GMBH & CO. KG, DE

Free format text: FORMER OWNER: SIEMENS AKTIENGESELLSCHAFT, 80333 MUENCHEN, DE

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: CH

Payment date: 20210705

Year of fee payment: 15

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 20220408

Year of fee payment: 16

Ref country code: GB

Payment date: 20220519

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FI

Payment date: 20220421

Year of fee payment: 16

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20220811 AND 20220817

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220430

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220430

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20230425

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20230425

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20230426

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20230425

Ref country code: FI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20230425

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20240429

Year of fee payment: 18

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20240423

Year of fee payment: 18