EP3183497A1 - Heat shield element and method for the production thereof - Google Patents

Heat shield element and method for the production thereof

Info

Publication number
EP3183497A1
EP3183497A1 EP15778966.0A EP15778966A EP3183497A1 EP 3183497 A1 EP3183497 A1 EP 3183497A1 EP 15778966 A EP15778966 A EP 15778966A EP 3183497 A1 EP3183497 A1 EP 3183497A1
Authority
EP
European Patent Office
Prior art keywords
heat shield
shield element
wall
cooling air
cooling
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
EP15778966.0A
Other languages
German (de)
French (fr)
Other versions
EP3183497B1 (en
Inventor
Thomas Hauser
Andreas Kreutzer
Patrick Lapp
Sebastian Piegert
Simon Purschke
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
Publication of EP3183497A1 publication Critical patent/EP3183497A1/en
Application granted granted Critical
Publication of EP3183497B1 publication Critical patent/EP3183497B1/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
    • F23R3/002—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
    • F23M5/00—Casings; Linings; Walls
    • F23M5/08—Cooling thereof; Tube walls
    • F23M5/085—Cooling thereof; Tube walls using air or other gas as the cooling medium
    • 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
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • 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
    • F23M2900/05004—Special materials for walls or lining
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow

Definitions

  • the invention relates to a heat shield element, in particular for lining a combustion chamber wall with integrated cooling air ducts according to the preamble of claim 1.
  • Impact cooling of the wall to be cooled but this is not an optimum with regard to the cooling air consumption nor to the achievable effect. Impact cooling essentially acts locally and the cooling of the hot gas acted parts takes place only on the back.
  • WO 2006/064038 proposes the AI before a heat shield element, which includes within its wall cooling air channels on ⁇ . This allows a nearly optimal cooling of the heat shield element with low cooling air consumption. The cooling takes place in the cooling channels and causes a Tempe ⁇ raturverring réelle in the wall of the heat shield element to be cooled itself.
  • the edge region of the heat shield element can be insufficiently cooled by the inner cooling air ducts.
  • the object of the invention is to provide a heat shield element of the type mentioned that allows the same to minimize the consumption of cooling air in an advantageous cooling and at the same time as simple and kos ⁇ -effectively to manufacture and to assemble. Furthermore, it is an object of the invention to provide a method for
  • the generic heat shield element is intended for use in a combustion chamber, which is in particular the combustion chamber in a gas turbine.
  • the heat shield element initially comprises a wall which has a hot side which can be acted upon by a hot medium and a cold side which is opposite to the hot side.
  • Surrounding the wall is an edge, which differs from the
  • Hot side over which extends beyond the plane of the cold side.
  • a fastening device which extends from the wall away from the hot side and out past the cold side.
  • the fastening device has a passage opening, so that a fastening means can be attached to the fastening device when passed through the passage opening.
  • cooling air inlets are arranged in the cooling air ducts, where ⁇ be arranged at cooling air outlets from the cooling air ducts in the region of the edge.
  • ERS te cooling air outlets on the outside of the rim angeord ⁇ net, so that there is an exit of the cooling air into the gap between adjacent heat shield elements.
  • the coolant flows through all parts of the heat ⁇ shield element in the order fastener, wall, edge and thus cools in all areas before the cooling air is discharged at the edge in the gap between two heat shield elements in the combustion chamber and blocks advantageous against the gap Induction of hot gas from the combustion chamber.
  • third cooling air outlets are arranged on the hot side of the wall in the region of the edge, so that an outlet of the cooling air takes place immediately adjacent to the gap into the combustion chamber. This allows for additional film cooling of the heat shield element.
  • the hot side of the heat shield element can thus be kept homogeneously at a constant temperature, since a protective de boundary layer between the hot combustion chamber gases and the heat shield element is formed.
  • cooling air inlets are provided on an outer side of the fastening device.
  • the fastening device is arranged centrally on the wall of the heat shield element ⁇ and is therefore the ideal place for the supply of cooling air into the cooling air ducts.
  • second cooling air outlets are provided on the inside of the fastening device.
  • the cooling function can be extended to the fastening means of the heat shield element.
  • internally cooled mounting screws are used for the attachment of heat shield elements.
  • fourth cooling air outlets are provided on the hot side in the region of its mountings ⁇ constriction device. This allows additional film cooling of the heat shield element in the region of the fastening, so that a protective boundary layer is formed between the hot combustion chamber gases and the fastening means.
  • the second cooling air outlets and / or the fourth cooling air outlets are supplied by the cooling air ducts leading to the edge or if further cooling air ducts lead from the fastening device to the second and / or fourth cooling air outlets. It is advantageous if the through-opening its mountings ⁇ constriction device has a bearing surface for a screw head, so that the screw is sunk ⁇ zeschildelement in the installed state in the hit, so that it is not subjected to exponier ⁇ th position with hot gas.
  • the heat shield member is substantially metal ⁇ lisch, ie it consists essentially of a metal or a metal alloy, such as high temperature resistant alloy coins ⁇ stanchions on iron, chromium, nickel or cobalt base. Compared to ceramics metals have a lower brittleness ⁇ as a more favorable thermal and thermal conductivity.
  • the heat shield element is used as protection and for cooling a hot gas leading combustion chamber, preferably an annular combustor of a gas turbine comprising a support structure attached to the heat shield elements are such ⁇ introduced.
  • the heat shield element is preferably provided with a loading attachment means, such as a screw, arranged on the supporting structure ⁇ .
  • a loading attachment means such as a screw
  • a metallic material with a suitable local distribution in powder form is remelted in layers on a substrate by means of laser radiation, so that in solidification of the molten powder in each case forms a further solid layer.
  • a three-dimensional CAD model is created in a first step, which is decomposed into a two- ⁇ th step in layers.
  • the actual manufacturing of the heat shield element is in the following Schrit ⁇ th, whereby a layer of powder is applied to a Un ⁇ terlage in the third step, the fourth step, the applied powder is irradiated by a laser or remelted and in the fifth step, the base to the layer thickness is lowered from the second step.
  • Schrit ⁇ th whereby a layer of powder is applied to a Un ⁇ terlage in the third step, the fourth step, the applied powder is irradiated by a laser or remelted and in the fifth step, the base to the layer thickness is lowered from the second step.
  • Steps are repeated until the heat shield element is completely made.
  • heat shield elements with comparatively small numbers of pieces are to be produced sensibly using this method. Also quickly to the needs reacts ⁇ the so system downtimes are reduced servicing.
  • FIG. 1 shows a half section through a gas turbine with combustion chambers
  • FIG. 2 shows a heat shield element according to the prior art
  • Figure 3 shows an embodiment of an inventive
  • Figure 4 shows an embodiment with an extension of
  • FIG. 3 shows an embodiment of an inventive
  • Figure 7 shows a section of the combustion chamber with film-cooled
  • FIG. 1 shows a gas turbine 21, which is shown partly in longitudinal section.
  • the gas turbine 21 has a compressor, an annular combustion chamber (20) with a plurality of burners for a liquid or gaseous fuel, a turbine for driving the compressor and a generator not shown in FIG.
  • the combustion chamber wall is lined with heat shield elements 1, or the heat shield elements 1 are attached to a support structure 22 on the combustion chamber wall.
  • air is sucked in from the environment.
  • the compressor the air compressed and thereby partially heated.
  • a small portion of the air is removed from the compressor and supplied as a coolant to the heat shield elements 1, the greater part of the air is supplied to the burners for combustion.
  • the combustion chamber 20 the greater part of the air from the compressor is combined with the liquid or gaseous fuel and burnt. This creates a hot gas that drives the gas turbine 21.
  • a relaxation and Ab ⁇ cooling of the hot gas In the turbine, a relaxation and Ab ⁇ cooling of the hot gas.
  • FIG. 2 schematically shows a heat shield element 30 according to the prior art.
  • the heat shield element 30 has a wall 2, which 2 has a hot side 3 (in FIG. 2 on the opposite side) which can be acted upon by a hot medium and a cold side 4 opposite the hot side 3, as well as an encircling wall bordering the wall 2, extending over the wall Furthermore, an attachment device 8, which extends substantially perpendicularly away from the wall 2, is arranged substantially in the middle of the cold side 4 of the wall 2, at the level of the cold side 4.
  • the heat shield element 30 is fixed by the fixing device 8 through a screw or bolt to the support structure 22nd
  • FIG. 3 a first exemplary embodiment of a heat shield element 1 according to the first embodiment of the invention is schematically shown, are arranged in the wall 2 to the edge 5 cooling channels 9 in which, starting from its mountings ⁇ constriction device. 8
  • cooling air entries 10 on one
  • FIG. 5 shows dung an exemplary embodiment of a heat shield element 1 according to the second embodiment of the inventions, which third cooling air outlets 15 are provided on the hot side 3 in the region of the edge. 5
  • the hot side of the Hitzeschildele ⁇ ment 1 is kept homogeneous at a constant temperature.
  • a protective boundary layer forms between the hot combustion chamber gases and the heat shield element 1.
  • the arrangement of the third cooling air openings 15 in the region of the edge 5 also protects the gap between adjacent heat shield elements 1 before a hot gas intake.
  • FIG. 6 shows a further exemplary embodiment of a heat shield element 1 according to the invention. This is initially designed analogously to the example from FIG. 3 and has a cooling air channel 9 extending from the fastening device 8 via the wall 2 to the edge 5. For this purpose, within the heat shield element in alternation with the
  • Cooling air ducts 9 further cooling air ducts 29 are arranged, wel ⁇ che also extending starting from the outside of the fastening ⁇ generating device 8 to the wall 2 extend. There, the further cooling air channels 29 open into fourth cooling air outlets 25, which are arranged near the fastening device 8 on the hot side 3 of the wall 2.
  • Figures 2 to 6 show the attachment device 8, 8 extends from the wall 2 of the heat shielding member 1 via the cold side 4 addition, and has a substantially perpendicular ⁇ rights oriented to the wall 2 through opening 16, which is adapted 16 to 16 a fastener 17 can accommodate. Furthermore, in FIGS. 3 to 6, it can be seen that bar, that the passage opening 16 has a contact surface 18 for a screw head 19.
  • FIG. 7 shows a section of a combustion chamber with heat shield elements 1 according to the invention.
  • the hot side 3 with the third cooling air outlets 15 for film cooling and the fastening of the heat shield elements 1 by fastening means 17, for example, can be seen

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention relates to a heat shield element (1) comprising a wall (2) having a hot side (3) and an opposing cold side (4), a peripheral edge (5) having an inner side (6) and an outer side (7), and a securing device (8) arranged substantially in the middle of the cold side (4) of the wall (2), said securing device extending substantially perpendicularly away from the wall (2), wherein cooling channels (9) are arranged in the securing device (8), wall (2) and edge (5), extending over at least two of the three. The invention also relates to a combustion chamber (20) and a gas turbine plant (24). The invention further relates to a method for producing a heat shield element (1) of this type.

Description

Beschreibung description
Hitzeschildelement und Verfahren zu seiner Herstellung Die Erfindung betrifft ein Hitzeschildelement, insbesondere zur Auskleidung einer Brennkammerwand mit integrierten Kühl- luftkanälen nach dem Oberbegriff des Anspruchs 1. The invention relates to a heat shield element, in particular for lining a combustion chamber wall with integrated cooling air ducts according to the preamble of claim 1.
Im Hinblick auf eine stetige Erhöhung der Wirkungsgrade von Gasturbinen wird unter anderem versucht, eine möglichst hohe Temperatur des Heißgases und ggf. auch einen erhöhten Massen¬ strom zu erreichen und gleichzeitig Luft für die Kühlung der mit diesem Heißgas beaufschlagten Bauteile einzusparen. D.h., Bauteile, wie beispielsweise Hitzeschilde in den Brennkam- mern, sollen bei geringerem Verbrauch von Kühlluft höheren Temperaturen standhalten können. Erschwerend kommt hinzu, dass Rohlinge für metallische Hitzeschildelemente, die typi¬ scherweise mittels Gussverfahren hergestellt werden, aufgrund der Vielfalt an verschieden geformten Hitzeschildelemente für eine Ringbrennkammer sowie hoher Anforderungen an die Form oft entweder verhältnismäßig teuer sind oder hinsichtlich der Qualität nicht den Anforderungen genügen. In view of a steady increase in the efficiencies of gas turbines is trying, inter alia, to achieve the highest possible temperature of the hot gas and possibly also an increased mass ¬ stream while saving air for cooling the acted upon with this hot gas components. That is, components, such as heat shields in the combustion chambers, should be able to withstand higher temperatures with less consumption of cooling air. To make matters worse, that blanks for metallic heat shield elements, which are typically produced ¬ cally by casting, due to the variety of differently shaped heat shield elements for an annular combustion chamber and high demands on the shape often either relatively expensive or in terms of quality do not meet the requirements.
Die meisten bestehenden Kühlkonzepte basieren auf einer Most existing cooling concepts are based on one
Prallkühlung der zu kühlenden Wand, was aber weder im Hinblick auf den Kühlluftverbrauch noch auf die erzielbare Wirkung ein Optimum darstellt. Prallkühlung wirkt im Wesentlichen lokal und die Kühlung der mit Heißgas beaufschlagten Teile erfolgt erst auf deren Rückseite. Impact cooling of the wall to be cooled, but this is not an optimum with regard to the cooling air consumption nor to the achievable effect. Impact cooling essentially acts locally and the cooling of the hot gas acted parts takes place only on the back.
Problematisch hinsichtlich der Kühlung ist insbesondere der Randbereich zwischen zwei Hitzeschildelemente, wo die Gefahr des Heißgaseinzugs hinter das Hitzeschild besteht. Hierzu sind aus dem Stand der Technik, beispielsweise aus der DE 10 2012 204 103 AI, Hitzeschildelemente bekannt, welche an einem umlaufenden Rand eine Mehrzahl von Durchgangsbohrungen aufweisen, durch die Kühlluft in den Spalt zwischen zwei Hitze¬ schildelemente geblasen werden kann. Wenngleich mit vorheriger Ausführung ein Heißgaseinzug weitgehend vermieden werden kann, so besteht unvermindert die Forderung die Kühlung des Hitzeschildelements bei verminder- tem Kühlluftverbrauch zu verbessern. In particular, the edge area between two heat shield elements where the risk of hot gas intake behind the heat shield is problematic with regard to the cooling. For this purpose, known from the prior art, for example from DE 10 2012 204 103 AI, heat shield elements, which have at a peripheral edge a plurality of through holes, can be blown through the cooling air into the gap between two heat ¬ shield elements. Although a hot gas intake can be largely avoided with the previous embodiment, there is a continuing demand to improve the cooling of the heat shield element with reduced cooling air consumption.
Hierzu schlägt die WO 2006/064038 AI ein Hitzeschildelement vor, welches innerhalb dessen Wandung Kühlluftkanäle auf¬ weist. Dieses ermöglicht eine nahezu optimale Kühlung des Hitzeschildelements bei geringem Kühlluftverbrauch. Die Kühlung findet in den Kühlkanälen statt und bewirkt eine Tempe¬ raturverringerung in der Wand des zu kühlenden Hitzeschildelements selbst. Jedoch hat es sich als nachteilig herausgestellt, dass der Randbereich des Hitzeschildelements unzureichend durch die inneren Kühlluftkanäle gekühlt werden kann. For this purpose, WO 2006/064038 proposes the AI before a heat shield element, which includes within its wall cooling air channels on ¬. This allows a nearly optimal cooling of the heat shield element with low cooling air consumption. The cooling takes place in the cooling channels and causes a Tempe ¬ raturverringerung in the wall of the heat shield element to be cooled itself. However, it has proved to be disadvantageous that the edge region of the heat shield element can be insufficiently cooled by the inner cooling air ducts.
Aufgabe der Erfindung ist es, ein Hitzeschildelement der ein- gangs genannten Art bereitzustellen, das einen möglichst geringen Verbrauch an Kühlluft bei vorteilhafter Kühlung desselben ermöglicht und das zugleich möglichst einfach und kos¬ tengünstig herzustellen und zu montieren ist. Ferner ist es eine Aufgabe der Erfindung ein Verfahren zurThe object of the invention is to provide a heat shield element of the type mentioned that allows the same to minimize the consumption of cooling air in an advantageous cooling and at the same time as simple and kos ¬-effectively to manufacture and to assemble. Furthermore, it is an object of the invention to provide a method for
Herstellung eines Hitzeschildelements nach der Erfindung anzugeben . To provide a heat shield element according to the invention.
Das gattungsgemäße Hitzeschildelement ist bestimmt zur Ver- wendung bei einer Brennkammer, wobei es sich insbesondere um die Brennkammer bei einer Gasturbine handelt. Hierbei umfasst das Hitzeschildelement zunächst einmal eine Wand, welche eine mit einem heißen Medium beaufschlagbare Heißseite und eine der Heißseite gegenüberliegende Kaltseite aufweist. Umlaufend um die Wand befindet sich ein Rand, welcher sich von derThe generic heat shield element is intended for use in a combustion chamber, which is in particular the combustion chamber in a gas turbine. In this case, the heat shield element initially comprises a wall which has a hot side which can be acted upon by a hot medium and a cold side which is opposite to the hot side. Surrounding the wall is an edge, which differs from the
Heißseite bis über die über die Ebene der Kaltseite hinaus erstreckt. Dabei weist der Rand eine an die Kaltseite angren¬ zende Innenseite und eine gegenüberliegende an die Heißseite angrenzende Außenseite auf. Im Wesentlichen in der Mitte der Wand ist eine Befestigungsvorrichtung angeordnet, welche sich von der Wand von der Heißseite wegweisend über die Kaltseite hinaus erstreckt. Hierbei weist die Befestigungsvorrichtung eine Durchgangsöffnung auf, so dass an der Befestigungsvorrichtung bei Durchgriff durch die Durchgangsöffnung ein Befestigungsmittel angebracht werden kann. Hot side over which extends beyond the plane of the cold side. Here, the edge of a angren ¬ collapsing to the cold side inner side and an opposite side of the hot adjoining outside. Arranged substantially in the middle of the wall is a fastening device which extends from the wall away from the hot side and out past the cold side. In this case, the fastening device has a passage opening, so that a fastening means can be attached to the fastening device when passed through the passage opening.
Zur Verbesserung der Kühlung eines gattungsgemäßen Hitze- schildelements über dessen Fläche sowie im Randbereich werden erfindungsgemäß eine Mehrzahl Kühlkanäle in das Hitzeschild¬ element eingebracht, welche die Wand des Hitzeschildelements vom der Befestigungsvorrichtung bis zum Rand durchziehen. Hierbei ist vorgesehen, dass bei der Befestigungsvorrichtung Kühllufteintritte in die Kühlluftkanäle angeordnet sind, wo¬ bei Kühlluftaustritte aus den Kühlluftkanälen im Bereich des Randes angeordnet werden. To improve the cooling of a generic heat shield element on its surface and in the edge region a plurality of cooling channels in the heat shield ¬ element are introduced according to the invention, which traverse the wall of the heat shield element from the fastening device to the brim. It is provided that in the fastening device cooling air inlets are arranged in the cooling air ducts, where ¬ be arranged at cooling air outlets from the cooling air ducts in the region of the edge.
In einer ersten erfindungsgemäßen Ausführungsform werden ers- te Kühlluftaustritte auf der Außenseite des Randes angeord¬ net, so dass ein Austritt der Kühlluft in den Spalt zwischen benachbarten Hitzeschildelementen erfolgt. In dieser Konfiguration strömt das Kühlmittel durch alle Teile des Hitze¬ schildelements in der Reihenfolge Befestigungselement, Wand, Rand und kühlt somit in allen Bereichen, bevor die Kühlluft am Rand in den Spalt zwischen zwei Hitzeschildelementen in die Brennkammer abgegeben wird und sperrt vorteilhaft den Spalt gegen Einzug von Heißgas aus der Brennkammer. In einer zweiten alternativen oder ergänzenden erfindungsgemäßen Ausführungsform werden dritte Kühlluftaustritte auf der Heißseite der Wand im Bereich des Randes angeordnet, so dass ein Austritt der Kühlluft unmittelbar benachbart zum Spalt in die Brennkammer hinein erfolgt. Hiermit wird eine zusätzliche Filmkühlung des Hitzeschildelements ermöglicht. Die heiße Seite des Hitzeschildelements kann damit homogen auf einer konstanten Temperatur gehalten werden, da sich eine schützen- de Grenzschicht zwischen den heißen Brennkammergasen und dem Hitzeschildelement ausbildet. In a first embodiment of the invention are ERS te cooling air outlets on the outside of the rim angeord ¬ net, so that there is an exit of the cooling air into the gap between adjacent heat shield elements. In this configuration, the coolant flows through all parts of the heat ¬ shield element in the order fastener, wall, edge and thus cools in all areas before the cooling air is discharged at the edge in the gap between two heat shield elements in the combustion chamber and blocks advantageous against the gap Induction of hot gas from the combustion chamber. In a second alternative or supplementary embodiment according to the invention, third cooling air outlets are arranged on the hot side of the wall in the region of the edge, so that an outlet of the cooling air takes place immediately adjacent to the gap into the combustion chamber. This allows for additional film cooling of the heat shield element. The hot side of the heat shield element can thus be kept homogeneously at a constant temperature, since a protective de boundary layer between the hot combustion chamber gases and the heat shield element is formed.
Bei der bekannten Ausführungsform mit integrierten Kühlluftkanälen führt die Rückführung des Kühlluftstroms auf die Un¬ terseite der Hitzeschildelemente dazu, dass nun der aufge¬ heizte Luftstrom abzuführen ist, was wiederum ein Folgeproblem hin sichtlich der Kühlluft verursacht. Durch die erfindungsgemäße Anordnung der ersten und/oder dritten Kühlluftaustritte am Rand des Hitzeschildelements mit einem Ausströ¬ men der aufgeheizten Kühlluft in den Spalt und/oder in die Brennkammer hinein wird die Wärme vom Hitzeschildelement ab¬ transportiert, ohne dass die Wärme das Innere, d.h. die Kalt seite, des Hitzeschildelements erreicht. Mit derselben Luft¬ menge ist also eine weitere Verringerung der Temperatur im Innenraum des Hitzeschildelements erreichbar (bzw. dieselbe Temperatur mit weniger Kühlluft) . Eine Temperaturverringerun wirkt sich positiv auf weitere Bauteile des Hitzeschildele¬ ments aus, die weniger thermisch belastet werden. In the known embodiment with integrated cooling air channels and recirculation of the cooling air flow leads to the Un ¬ underside of the heat shield elements to the fact that now the up ¬ heated air flow to be dissipated, which in turn causes a further problem towards clearly the cooling air. The inventive arrangement of the first and / or third cooling air outlets at the edge of the heat shield element with a Ausströ ¬ men of the heated cooling air into the gap and / or into the combustion chamber into the heat from the heat shield element is transported ¬ , without the heat inside, ie the cold side, reaches the heat shield element. Thus, with the same air volume ¬ a further reduction of temperature in the interior of the heat shield element is accessible (or at the same temperature with less cooling air). A Temperaturverringerun has a positive effect on other components of Hitzeschildele ¬ ment, which are less thermally stressed.
Vorzugsweise sind Kühllufteintritte auf einer Außenseite der Befestigungsvorrichtung vorgesehen. Die Befestigungsvorrichtung ist zentral auf der Wand des Hitzeschildelements ange¬ ordnet und ist daher der ideale Ort für die Einspeisung der Kühlluft in die Kühlluftkanäle. Preferably, cooling air inlets are provided on an outer side of the fastening device. The fastening device is arranged centrally on the wall of the heat shield element ¬ and is therefore the ideal place for the supply of cooling air into the cooling air ducts.
In einer bevorzugten Ausführungsform sind zweite Kühlluftaustritte auf der Innenseite der Befestigungsvorrichtung vorgesehen. Damit kann die Kühlfunktion auf das Befestigungsmittel des Hitzeschildelements ausgedehnt werden. Typischerweise kommen zur Befestigung von Hitzeschildelementen innengekühlte Befestigungsschrauben zum Einsatz. Erfolgt nun eine Kühlung der Befestigungsvorrichtung selbst, können einfachere Befestigungsschrauben ohne Innenkühlung verwendet werden, die entsprechend kostengünstiger und aufgrund des einfacheren De¬ signs auch zuverlässiger sind. In einer anderen bevorzugten Ausführungsform sind vierte Kühlluftaustritte auf der Heißseite im Bereich der Befesti¬ gungsvorrichtung vorgesehen. Hiermit wird eine zusätzliche Filmkühlung des Hitzeschildelements im Bereich der Befesti- gung ermöglicht, so dass sich eine schützende Grenzschicht zwischen den heißen Brennkammergasen und dem Befestigungsmittel ausbildet. In a preferred embodiment, second cooling air outlets are provided on the inside of the fastening device. Thus, the cooling function can be extended to the fastening means of the heat shield element. Typically, for the attachment of heat shield elements internally cooled mounting screws are used. Now, if a cooling of the fastening device itself, simpler screws without internal cooling can be used, which are correspondingly cheaper and more reliable due to the simpler De ¬ signs. In another preferred embodiment, fourth cooling air outlets are provided on the hot side in the region of its mountings ¬ constriction device. This allows additional film cooling of the heat shield element in the region of the fastening, so that a protective boundary layer is formed between the hot combustion chamber gases and the fastening means.
Es ist zunächst unerheblich, ob die zweiten Kühlluftaustritte und/oder die vierten Kühlluftaustritte von den zum Rand führenden Kühlluftkanälen versorgt werden oder weitere Kühlluftkanäle ausgehend von der Befestigungsvorrichtung zu den zweiten und/oder vierten Kühlluftaustritten führen. Es ist zweckmäßig, wenn die Durchgangsöffnung der Befesti¬ gungsvorrichtung eine Anlagefläche für einen Schraubenkopf aufweist, so dass die Schraube im eingebauten Zustand im Hit¬ zeschildelement versenkt ist, so dass sie nicht an exponier¬ ter Stelle mit Heißgas beaufschlagt wird. It is irrelevant at first whether the second cooling air outlets and / or the fourth cooling air outlets are supplied by the cooling air ducts leading to the edge or if further cooling air ducts lead from the fastening device to the second and / or fourth cooling air outlets. It is advantageous if the through-opening its mountings ¬ constriction device has a bearing surface for a screw head, so that the screw is sunk ¬ zeschildelement in the installed state in the hit, so that it is not subjected to exponier ¬ th position with hot gas.
Bevorzugt ist das Hitzeschildelement im Wesentlichen metal¬ lisch, d.h. es besteht im Wesentlichen aus einem Metall oder einer Metalllegierung, z.B. hochtemperaturresistente Legie¬ rungen auf Eisen-, Chrom-, Nickel- oder Kobaltbasis. Gegen- über Keramiken weisen Metalle eine geringere Sprödigkeit so¬ wie eine günstigere Wärme- und Temperaturleitfähigkeit auf. Preferably, the heat shield member is substantially metal ¬ lisch, ie it consists essentially of a metal or a metal alloy, such as high temperature resistant alloy coins ¬ stanchions on iron, chromium, nickel or cobalt base. Compared to ceramics metals have a lower brittleness ¬ as a more favorable thermal and thermal conductivity.
Das Hitzeschildelement wird als Schutz und zur Kühlung einer heißgasführenden Brennkammer benutzt, vorzugsweise einer ringförmigen Brennkammer einer Gasturbine, die eine Tragstruktur aufweist, an der solche Hitzeschildelemente ange¬ bracht sind. The heat shield element is used as protection and for cooling a hot gas leading combustion chamber, preferably an annular combustor of a gas turbine comprising a support structure attached to the heat shield elements are such ¬ introduced.
Das Hitzeschildelement ist dabei vorzugsweise mit einem Be- festigungsmittel , beispielsweise einer Schraube, an der Trag¬ struktur angeordnet. Im vorteilhaften Verfahren zum Herstellen eines Hitzeschildelements mit einer Wand, welche eine mit einem heißen Medium beaufschlagbare Heißseite und eine der Heißseite gegenüber¬ liegende Kaltseite aufweist, und mit einem an die Wand an- grenzenden, umlaufenden, sich über die Ebene der Kaltseite hinaus erstreckenden Rand mit einer Innen- und einer Außenseite und mit einer im Wesentlichen in der Mitte der Kaltseite der Wand angeordneten Befestigungsvorrichtung, welche sich im Wesentlichen senkrecht von der Wand weg erstreckt, wobei in Befestigungsvorrichtung, Wand und Rand Kühlkanäle angeord¬ net sind, die sich über mindestens zwei der drei erstrecken, wird ein metallischer Werkstoff mit geeigneter örtlicher Verteilung in Pulverform in Schichten auf einer Unterlage mittels Laserstrahlung umgeschmolzen, so dass sich beim Erstar- ren des geschmolzenen Pulvers jeweils eine weitere feste Schicht ausbildet. The heat shield element is preferably provided with a loading attachment means, such as a screw, arranged on the supporting structure ¬. In the advantageous process for producing a heat shield member having a wall having a pressurizable with a hot medium hot side and a hot side opposite ¬ lying cold side, and with an on adjoining the wall, encircling and extending above the plane of the cold side out edge with an inner and an outer side and with a substantially in the middle of the cold side of the wall arranged fastening device which extends substantially perpendicularly away from the wall, wherein in fastening device, wall and edge cooling channels are angeord ¬ net, extending over at least two of the three extend, a metallic material with a suitable local distribution in powder form is remelted in layers on a substrate by means of laser radiation, so that in solidification of the molten powder in each case forms a further solid layer.
Die Verwendung des sogenannten „Selektiven Laserschmelzens" zur vergleichsweise einfachen, aber präzisen Herstellung der Hitzeschildelemente ermöglicht das Einbringen komplexer In¬ nenkonturen zur verbesserten Kühlung des gesamten Bauteils mit der Folge eines geringeren Verschleißes. Die im Betrieb notwendige Kühlluftmenge und somit auch die Stickoxid- Emissionen können gesenkt werden. Auf eine aufwändige Prall- kühlung kann verzichtet werden. The use of the so-called "selective laser melting" for comparatively simple but precise manufacture of the heat shield elements allows the introduction of complex In ¬ nenkonturen for improved cooling of the entire component with the consequence of a lower wear. The necessary quantity of cooling air and thus the nitrogen oxide emissions during operation An elaborate impingement cooling can be dispensed with.
Zu Beginn des Verfahrens wird in einem ersten Schritt ein dreidimensionales CAD-Modell erstellt, welches in einem zwei¬ ten Schritt in Schichten zerlegt wird. Die eigentliche Ferti- gung des Hitzeschildelements erfolgt in den folgenden Schrit¬ ten, wobei im dritten Schritt eine Pulverschicht auf eine Un¬ terlage aufgetragen wird, im vierten Schritt das aufgetragene Pulver durch einen Laser belichtet bzw. umgeschmolzen wird und im fünften Schritt die Unterlage um die Schichtdicke aus dem zweiten Schritt abgesenkt wird. Die dritten bis fünftenAt the beginning of the process a three-dimensional CAD model is created in a first step, which is decomposed into a two-¬ th step in layers. The actual manufacturing of the heat shield element is in the following Schrit ¬ th, whereby a layer of powder is applied to a Un ¬ terlage in the third step, the fourth step, the applied powder is irradiated by a laser or remelted and in the fifth step, the base to the layer thickness is lowered from the second step. The third to fifth
Schritte werden so oft wiederholt, bis das Hitzeschildelement vollständig hergestellt ist. Insbesondere Hitzeschildelemente mit vergleichsweise geringen Stückzahlen sind über dieses Verfahren sinnvoll herzustellen. Auch kann im Servicefall schnell auf den Bedarf reagiert wer¬ den, so dass Ausfallzeiten der Anlagen verringert werden. Steps are repeated until the heat shield element is completely made. In particular, heat shield elements with comparatively small numbers of pieces are to be produced sensibly using this method. Also quickly to the needs reacts ¬ the so system downtimes are reduced servicing.
Die Erfindung wird beispielhaft anhand der Zeichnungen näher erläutert. Es zeigen schematisch und nicht maßstäblich: The invention will be explained in more detail by way of example with reference to the drawings. Shown schematically and not to scale:
Figur 1 einen Halbschnitt durch eine Gasturbine mit Brenn- kämmer, FIG. 1 shows a half section through a gas turbine with combustion chambers,
Figur 2 eine Hitzeschildelement nach dem Stand der Technik, FIG. 2 shows a heat shield element according to the prior art,
Figur 3 ein Ausführungsbeispiel für ein erfindungsgemäßes Figure 3 shows an embodiment of an inventive
Hitzeschildelement in erster Ausführungsform,  Heat shield element in the first embodiment,
Figur 4 ein Ausführungsbeispiel mit einer Erweiterung der Figure 4 shows an embodiment with an extension of
Ausführung aus Fig. 3, Figur 5 ein Ausführungsbeispiel für ein erfindungsgemäßes  Embodiment of FIG. 3, Figure 5 shows an embodiment of an inventive
Hitzeschildelement in zweiter Ausführungsform,  Heat shield element in the second embodiment,
Figur 6 ein weiteres Ausführungsbeispiel mit einer Erweite¬ rung der Ausführung aus Fig. 3, 6 shows a further embodiment with a Extension C ¬ tion of the embodiment of Fig. 3,
Figur 7 einen Ausschnitt der Brennkammer mit filmgekühlten Figure 7 shows a section of the combustion chamber with film-cooled
HitzeSchildelementen .  Heat sign elements.
Die Figur 1 zeigt eine Gasturbine 21, die 21 teilweise längs aufgeschnitten dargestellt ist. Die Gasturbine 21 weist einen Verdichter, eine Ringbrennkammer (20) mit einer Mehrzahl von Brennern für einen flüssigen oder gasförmigen Brennstoff, eine Turbine zum Antrieb des Verdichters und eines in FIG 1 nicht dargestellten Generators auf. Dabei ist die Brennkam- merwand mit Hitzeschildelementen 1 ausgekleidet, bzw. die Hitzeschildelemente 1 sind an einer Tragstruktur 22 an der Brennkammerwand angebracht. Im Betrieb der Gasturbine 21 wird Luft aus der Umgebung angesaugt. Im Verdichter wird die Luft verdichtet und dadurch teilweise erwärmt. Ein kleiner Teil der Luft wird dem Verdichter entnommen und als Kühlmittel den Hitzeschildelementen 1 zugeführt, der größere Teil der Luft wird den Brennern zur Verbrennung zugeführt. In der Brennkam- mer 20 wird der größere Teil der Luft aus dem Verdichter mit dem flüssigen oder gasförmigen Brennstoff zusammengebracht und verbrannt. Dabei entsteht ein Heißgas, das die Gasturbine 21 antreibt. In der Turbine erfolgt eine Entspannung und Ab¬ kühlung des Heißgases. FIG. 1 shows a gas turbine 21, which is shown partly in longitudinal section. The gas turbine 21 has a compressor, an annular combustion chamber (20) with a plurality of burners for a liquid or gaseous fuel, a turbine for driving the compressor and a generator not shown in FIG. In this case, the combustion chamber wall is lined with heat shield elements 1, or the heat shield elements 1 are attached to a support structure 22 on the combustion chamber wall. During operation of the gas turbine 21, air is sucked in from the environment. In the compressor, the air compressed and thereby partially heated. A small portion of the air is removed from the compressor and supplied as a coolant to the heat shield elements 1, the greater part of the air is supplied to the burners for combustion. In the combustion chamber 20, the greater part of the air from the compressor is combined with the liquid or gaseous fuel and burnt. This creates a hot gas that drives the gas turbine 21. In the turbine, a relaxation and Ab ¬ cooling of the hot gas.
In der Figur 2 ist ein Hitzeschildelement 30 nach dem Stand der Technik schematisch dargestellt. Das Hitzeschildelement 30 hat eine Wand 2, welche 2 eine mit einem heißen Medium beaufschlagbare Heißseite 3 (in Figur 2 auf der abgewandten Seite) und eine der Heißseite 3 gegenüberliegende Kaltseite 4 aufweist, sowie einen an die Wand 2 angrenzenden, umlaufenden, sich über die Ebene der Kaltseite 4 hinaus erstreckenden Rand 5 mit einer Innen- 6 und einer Außenseite 7. Ferner ist im Wesentlichen in der Mitte der Kaltseite 4 der Wand 2 eine Befestigungsvorrichtung 8 angeordnet, welche 8 sich im Wesentlichen senkrecht von der Wand 2 weg erstreckt. Das Hitze¬ schildelement 30 wird durch die Befestigungsvorrichtung 8 hindurch mit einer Schraube oder einem Bolzen an der Tragstruktur 22 befestigt. FIG. 2 schematically shows a heat shield element 30 according to the prior art. The heat shield element 30 has a wall 2, which 2 has a hot side 3 (in FIG. 2 on the opposite side) which can be acted upon by a hot medium and a cold side 4 opposite the hot side 3, as well as an encircling wall bordering the wall 2, extending over the wall Furthermore, an attachment device 8, which extends substantially perpendicularly away from the wall 2, is arranged substantially in the middle of the cold side 4 of the wall 2, at the level of the cold side 4. The heat shield element 30 is fixed by the fixing device 8 through a screw or bolt to the support structure 22nd
In der Figur 3 ist schematisch ein erste Ausführungsbeispiel für ein Hitzeschildelement 1 nach der ersten Ausführungsform der Erfindung gezeigt, bei dem ausgehend von der Befesti¬ gungsvorrichtung 8 in der Wand 2 bis zum Rand 5 Kühlkanäle 9 angeordnet sind. Dabei sind Kühllufteintritte 10 auf einerIn the figure 3 a first exemplary embodiment of a heat shield element 1 according to the first embodiment of the invention is schematically shown, are arranged in the wall 2 to the edge 5 cooling channels 9 in which, starting from its mountings ¬ constriction device. 8 Here are cooling air entries 10 on one
Außenseite 11 der Befestigungsvorrichtung 8 und entsprechende erste Kühlluftaustritte 12 auf der Außenseite 7 des Randes 5 vorgesehen . In der Figur 4 ist eine Ausführungsform des Hitzeschildele¬ mentes 1 aus Fig.l gezeigt, welches 1 weiterhin zweite Kühl- luftaustritte 13 aufweist. Zur Verbesserung der Kühlfunktion für das Befestigungsmittel (nicht gezeigt) , beispielsweise eine Schraube oder ein Bolzen, sind in diesem Beispiel auf der Innenseite 14 der Befestigungsvorrichtung 8 die zweiten Kühlluftaustritte 13 vorgesehen. Hiermit kann eine aufwändi¬ gere, innengekühlte Befestigungsschraube durch eine einfache Schraube zur Befestigung des Hitzeschildelements 1 an der Tragstruktur 22 ersetzt werden. Outside 11 of the fastening device 8 and corresponding first cooling air outlets 12 on the outside 7 of the edge 5 is provided. In the figure 4 an embodiment of the Hitzeschildele ¬ mentes 1 shown in Fig.l, further comprising 1 second cooling air outlets. 13 To improve the cooling function for the fastener (not shown), for example a screw or a bolt, the second cooling air outlets 13 are provided in this example on the inside 14 of the fastening device 8. This can be a aufwändi ¬ gere, internally cooled fastening screw replaced by a simple screw for fixing the heat shield element 1 to the support structure 22.
Die Figur 5 zeigt ein Ausführungsbeispiel für ein Hitze¬ schildelementes 1 nach der zweiten Ausführungsform der Erfin- dung, wonach dritte Kühlluftaustritte 15 auf der Heißseite 3 im Bereich des Randes 5 vorgesehen sind. Durch den Einsatz einer Filmkühlung wird die heiße Seite des Hitzeschildele¬ ments 1 homogen auf einer konstanten Temperatur gehalten. Es bildet sich eine schützende Grenzschicht zwischen den heißen Brennkammergasen und dem Hitzeschildelement 1 aus. Weiterhin schützt die Anordnung der dritten Kühlluftöffnungen 15 im Bereich des Randes 5 ebenso den Spalt zwischen benachbarten Hitzeschildelementen 1 vor einem Heißgaseinzug. Die Figur 6 zeigt ein weiteres Ausführungsbeispiel für ein erfindungsgemäßes Hitzeschildelement 1. Dieses ist zunächst analog dem Beispiel aus Fig. 3 ausgeführt und weist einen sich von der Befestigungsvorrichtung 8 über die Wand 2 bis zum Rand 5 erstreckenden Kühlluftkanal 9 aufweist. Dazu wer- den innerhalb des Hitzeschildelements im Wechsel mit den5 shows dung an exemplary embodiment of a heat shield element 1 according to the second embodiment of the inventions, which third cooling air outlets 15 are provided on the hot side 3 in the region of the edge. 5 By using a film cooling, the hot side of the Hitzeschildele ¬ ment 1 is kept homogeneous at a constant temperature. A protective boundary layer forms between the hot combustion chamber gases and the heat shield element 1. Furthermore, the arrangement of the third cooling air openings 15 in the region of the edge 5 also protects the gap between adjacent heat shield elements 1 before a hot gas intake. FIG. 6 shows a further exemplary embodiment of a heat shield element 1 according to the invention. This is initially designed analogously to the example from FIG. 3 and has a cooling air channel 9 extending from the fastening device 8 via the wall 2 to the edge 5. For this purpose, within the heat shield element in alternation with the
Kühlluftkanälen 9 weitere Kühlluftkanäle 29 angeordnet, wel¬ che sich ebenfalls ausgehend von der Außenseite der Befesti¬ gungsvorrichtung 8 bis zur Wand 2 erstrecken. Dort münden die weiteren Kühlluftkanäle 29 in vierte Kühlluftaustritte 25, welche nahe der Befestigungsvorrichtung 8 auf der Heißseite 3 der Wand 2 angeordnet sind. Cooling air ducts 9 further cooling air ducts 29 are arranged, wel ¬ che also extending starting from the outside of the fastening ¬ generating device 8 to the wall 2 extend. There, the further cooling air channels 29 open into fourth cooling air outlets 25, which are arranged near the fastening device 8 on the hot side 3 of the wall 2.
Die Figuren 2 bis 6 zeigen die Befestigungsvorrichtung 8, die 8 sich von der Wand 2 des Hitzeschildelements 1 über die Kaltseite 4 hinaus erstreckt und eine im Wesentlichen senk¬ recht zur Wand 2 orientierte Durchgangsöffnung 16 aufweist, die 16 so ausgebildet ist, dass sie 16 ein Befestigungsmittel 17 aufnehmen kann. Ferner ist in den Figuren 3 bis 6 erkenn- bar, dass die Durchgangsöffnung 16 eine Anlagefläche 18 für einen Schraubenkopf 19 aufweist. Figures 2 to 6 show the attachment device 8, 8 extends from the wall 2 of the heat shielding member 1 via the cold side 4 addition, and has a substantially perpendicular ¬ rights oriented to the wall 2 through opening 16, which is adapted 16 to 16 a fastener 17 can accommodate. Furthermore, in FIGS. 3 to 6, it can be seen that bar, that the passage opening 16 has a contact surface 18 for a screw head 19.
Die Figur 7 zeigt einen Ausschnitt einer Brennkammer mit Hit- zeschildelementen 1 nach der Erfindung. Zu sehen ist insbesondere die Heißseite 3 mit den dritten Kühlluftaustritten 15 für eine Filmkühlung sowie die Befestigung der Hitzeschildelemente 1 durch Befestigungsmittel 17, beispielsweise FIG. 7 shows a section of a combustion chamber with heat shield elements 1 according to the invention. In particular, the hot side 3 with the third cooling air outlets 15 for film cooling and the fastening of the heat shield elements 1 by fastening means 17, for example, can be seen
Schrauben . Screws.

Claims

Hitzeschildelement (1), insbesondere zur Auskleidung ei¬ ner Brennkammerwand, mit einer Wand Heat shield element (1), in particular for lining a combustion chamber wall, with a wall
(2), welche eine mit einem heißen Medium beaufschlagbare Heißseite (2), which has a hot side that can be acted upon with a hot medium
(3) und ei¬ ne gegenüberliegende Kaltseite (4) aufweist, und mit ei¬ nem umlaufenden sich von der Heißseite (03) über die Kaltseite (4) hinaus erstreckenden Rand (5), welcher (5) eine an der Kaltseite (04) angrenzende Innenseite (6) und eine an der Heißseite (03) angrenzende Außenseite (7) aufweist, und mit einer im Wesentlichen in der Mitte der Wand (2) angeordneten Befestigungsvorrichtung (8), welche(3) and an opposite cold side (4), and with a circumferential edge (5) extending from the hot side (03) beyond the cold side (4), which (5) has one on the cold side (04 ) has an adjacent inside (6) and an outside (7) adjacent to the hot side (03), and with a fastening device (8) arranged essentially in the middle of the wall (2), which
(8) sich von der Wand (2) weg über die Kaltseite (8) away from the wall (2) over the cold side
(4) hinaus erstreckt und eine Durchgangsöffnung (16) zur Aufnahme eines Befestigungsmittel (17) aufweist, (4) extends out and has a through opening (16) for receiving a fastening means (17),
dadurch gekennzeichnet, characterized,
dass eine Mehrzahl Kühlkanäle (9) von der Befestigungs¬ vorrichtung (8) durch die Wand (2) bis zum Rand (5) verlaufen, wobei erste Kühlluftaustritte (12) der Kühlkanälethat a plurality of cooling channels (9) run from the fastening device (8) through the wall (2) to the edge (5), with first cooling air outlets (12) of the cooling channels
(9) auf der Außenseite (7) des Randes (5) und/oder dritte Kühlluftaustritte (15) auf der Heißseite (3) am Rand (5) angeordnet sind. (9) are arranged on the outside (7) of the edge (5) and/or third cooling air outlets (15) on the hot side (3) on the edge (5).
Hitzeschildelement (1) nach einem der Ansprüche 1, dadurch gekennzeichnet, Heat shield element (1) according to one of claims 1, characterized in
dass die Kühllufteintritte (10) auf einer Außenseite (11) der Befestigungsvorrichtung (8) vorgesehen sind. that the cooling air inlets (10) are provided on an outside (11) of the fastening device (8).
Hitzeschildelement (1) nach Anspruch 1 oder 2, Heat shield element (1) according to claim 1 or 2,
dadurch gekennzeichnet, characterized,
dass zweite Kühlluftaustritte (13) auf einer Innenseite (14) der Befestigungsvorrichtung (8) vorgesehen sind. that second cooling air outlets (13) are provided on an inside (14) of the fastening device (8).
Hitzeschildelement (1) nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, Heat shield element (1) according to one of claims 1 to 3, characterized in
dass vierte Kühlluftaustritte (25) auf der Heißseite (3) im Bereich der mittigen Befestigungsvorrichtung (8) vorgesehen sind. that fourth cooling air outlets (25) are provided on the hot side (3) in the area of the central fastening device (8).
5. Hitzeschildelement (1) nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, 5. Heat shield element (1) according to one of claims 1 to 4, characterized in
dass die Durchgangsöffnung (16) eine Anlagefläche (18) für einen Schraubenkopf (19) aufweist. that the through opening (16) has a contact surface (18) for a screw head (19).
6. Hitzeschildelement (1) nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, 6. Heat shield element (1) according to one of claims 1 to 5, characterized in
dass das Hitzeschildelement (1) im Wesentlichen metal¬ lisch ist. that the heat shield element (1) is essentially metallic .
7. Brennkammer (20) einer Gasturbine (21) mit einer Tragstruktur (22) und mit mehreren (22) daran angebrachten Hitzeschildelementen (1) nach einem der vorhergehenden Ansprüche . 7. Combustion chamber (20) of a gas turbine (21) with a support structure (22) and with several (22) attached to it heat shield elements (1) according to one of the preceding claims.
8. Gasturbine (21) mit einer Brennkammer (20) nach Anspruch 7. 8. Gas turbine (21) with a combustion chamber (20) according to claim 7.
9. Verfahren zum Herstellen eines Hitzeschildelements (1) nach einem der vorhergehenden Ansprüche, 9. A method for producing a heat shield element (1) according to one of the preceding claims,
dadurch gekennzeichnet, characterized,
dass ein metallischer Werkstoff mit in Pulverform in Schichten auf einer Unterlage mittels Laserstrahlung umgeschmolzen wird, so dass sich beim Erstarren des geschmolzenen Pulvers jeweils eine weitere feste Schicht ausbildet . that a metallic material is melted in powder form in layers on a base using laser radiation, so that another solid layer is formed when the molten powder solidifies.
EP15778966.0A 2014-10-20 2015-10-13 Heat shield element and method for the production thereof Active EP3183497B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102014221225.1A DE102014221225A1 (en) 2014-10-20 2014-10-20 Heat shield element and method for its production
PCT/EP2015/073661 WO2016062581A1 (en) 2014-10-20 2015-10-13 Heat shield element and method for the production thereof

Publications (2)

Publication Number Publication Date
EP3183497A1 true EP3183497A1 (en) 2017-06-28
EP3183497B1 EP3183497B1 (en) 2018-07-18

Family

ID=54293259

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15778966.0A Active EP3183497B1 (en) 2014-10-20 2015-10-13 Heat shield element and method for the production thereof

Country Status (4)

Country Link
EP (1) EP3183497B1 (en)
CN (1) CN107076414B (en)
DE (1) DE102014221225A1 (en)
WO (1) WO2016062581A1 (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019028241A1 (en) * 2017-08-02 2019-02-07 United Technologies Corporation Minimization of low pressure vortex in the rail between two adjacent liner panels
EP3531020A1 (en) * 2018-02-22 2019-08-28 United Technologies Corporation Multi-direction hole for liner panel rail effusion
US10830435B2 (en) 2018-02-06 2020-11-10 Raytheon Technologies Corporation Diffusing hole for rail effusion
US11009230B2 (en) 2018-02-06 2021-05-18 Raytheon Technologies Corporation Undercut combustor panel rail
US11248791B2 (en) 2018-02-06 2022-02-15 Raytheon Technologies Corporation Pull-plane effusion combustor panel

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016224632A1 (en) 2016-12-09 2018-06-14 Rolls-Royce Deutschland Ltd & Co Kg Plate-shaped component of a gas turbine and method for its production
DE102018116682A1 (en) * 2018-07-10 2020-01-16 Elringklinger Ag Heat shielding device, in particular heat shielding device that can be adapted to locally different heat inputs per area
GB201813753D0 (en) * 2018-08-23 2018-10-10 Rolls Royce Plc A combustion chamber, a combustion chamber tile and a method of manufacturing a combustion chamber tile
DE102019212039A1 (en) * 2019-08-12 2021-02-18 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber assembly with segmented wall structure and relief channel in the area of a segmentation slot and manufacturing process
WO2021121862A1 (en) * 2019-12-17 2021-06-24 Siemens Energy Global GmbH & Co. KG Heat shield tile for a combustion chamber, and combustion chamber
SE544235C2 (en) * 2020-07-09 2022-03-08 Valmet Oy Cooling shield for a liquor injection pipe, a liquor gun system and a method for cooling a liquor injection pipe
CN112923398B (en) * 2021-03-04 2022-07-22 西北工业大学 Afterburning chamber antivibration heat screen
EP4372281A1 (en) * 2022-11-18 2024-05-22 ANSALDO ENERGIA S.p.A. Combustion chamber for a power plant gas turbine assembly comprising a plurality of metallic heat shielding tiles with improved air cooling feature

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4820097A (en) * 1988-03-18 1989-04-11 United Technologies Corporation Fastener with airflow opening
EP1284390A1 (en) * 2001-06-27 2003-02-19 Siemens Aktiengesellschaft Thermal shield for a component carrying hot gases, especially for structural components of gas turbines
DE50310313D1 (en) * 2003-01-29 2008-09-25 Siemens Ag combustion chamber
EP1507116A1 (en) * 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Heat shield arrangement for a high temperature gas conveying component, in particular for a gas turbine combustion chamber
EP1533113A1 (en) * 2003-11-14 2005-05-25 Siemens Aktiengesellschaft High temperature layered system for heat dissipation and method for making it
EP1672281A1 (en) * 2004-12-16 2006-06-21 Siemens Aktiengesellschaft Thermal shield element
DE102005046731A1 (en) * 2005-04-19 2006-11-02 Siemens Ag Heat shield arrangement
EP1990328B1 (en) * 2007-05-07 2011-10-26 Siemens Aktiengesellschaft Ceramic powder, ceramic layer and layer system with two pyrochlorphases and oxides
GB0913580D0 (en) * 2009-08-05 2009-09-16 Rolls Royce Plc Combustor tile
EP2423596A1 (en) * 2010-08-27 2012-02-29 Siemens Aktiengesellschaft Heat shield element
EP2487006A1 (en) * 2011-02-14 2012-08-15 Siemens Aktiengesellschaft Multiple laser processing from various angles
EP2549063A1 (en) * 2011-07-21 2013-01-23 Siemens Aktiengesellschaft Heat shield element for a gas turbine
DE102012204103A1 (en) * 2012-03-15 2013-09-19 Siemens Aktiengesellschaft Heat shield element for a compressor air bypass around the combustion chamber
GB201303057D0 (en) * 2013-02-21 2013-04-03 Rolls Royce Plc A combustion chamber
WO2014137428A1 (en) * 2013-03-05 2014-09-12 Rolls-Royce Corporation Dual-wall impingement, convection, effusion combustor tile

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2019028241A1 (en) * 2017-08-02 2019-02-07 United Technologies Corporation Minimization of low pressure vortex in the rail between two adjacent liner panels
US10663168B2 (en) 2017-08-02 2020-05-26 Raytheon Technologies Corporation End rail mate-face low pressure vortex minimization
US10830435B2 (en) 2018-02-06 2020-11-10 Raytheon Technologies Corporation Diffusing hole for rail effusion
US11009230B2 (en) 2018-02-06 2021-05-18 Raytheon Technologies Corporation Undercut combustor panel rail
US11248791B2 (en) 2018-02-06 2022-02-15 Raytheon Technologies Corporation Pull-plane effusion combustor panel
EP3531020A1 (en) * 2018-02-22 2019-08-28 United Technologies Corporation Multi-direction hole for liner panel rail effusion
US11022307B2 (en) 2018-02-22 2021-06-01 Raytheon Technology Corporation Gas turbine combustor heat shield panel having multi-direction hole for rail effusion cooling
US11359812B2 (en) 2018-02-22 2022-06-14 Raytheon Technologies Corporation Multi-direction hole for rail effusion

Also Published As

Publication number Publication date
EP3183497B1 (en) 2018-07-18
DE102014221225A1 (en) 2016-04-21
WO2016062581A1 (en) 2016-04-28
CN107076414A (en) 2017-08-18
CN107076414B (en) 2019-06-14

Similar Documents

Publication Publication Date Title
EP3183497B1 (en) Heat shield element and method for the production thereof
DE60224339T2 (en) Cooling insert with tangential outflow
DE60317920T2 (en) EFFUSION COOLED TRANSITION CHANNEL WITH SHAPED COOLING HOLES
EP2340397B1 (en) Burner insert for a gas turbine combustion chamber and gas turbine
EP1904717B1 (en) Hot gas-conducting housing element, protective shaft jacket, and gas turbine system
WO2006064038A1 (en) Heat shield element
WO2005019730A1 (en) Heat shield arrangement for a hot gas-guiding component, particularly for a combustion chamber of a gas turbine
EP2423599A2 (en) Method for operating a burner arrangement and burner arrangement for implementing the method
DE102015225505A1 (en) Wall of a component to be cooled by means of cooling air, in particular a gas turbine combustion chamber wall
EP1275747A1 (en) Method and device for coating a high temperature resistant article with a thermal protection covering
EP2084368B1 (en) Turbine blade
DE60018706T2 (en) COOLING PROCESS FOR A COMBUSTION TURBINE
EP1884713B1 (en) Heat shield arrangement, particularly for a gas turbine
DE102005046731A1 (en) Heat shield arrangement
DE69002300T2 (en) Regulation for eccentric radial gaps in turbomachinery.
EP1510653B1 (en) Cooled turbine blade
DE10064271A1 (en) Device for impingement cooling of a component which is exposed to heat in a turbo engine and method therefor
DE19940556B4 (en) Device for cooling guide vanes or rotor blades in a gas turbine
EP1970540A2 (en) Hot gas duct with duct splitter
EP1512911A1 (en) Device for cooling high-thermally stressed parts
DE112014006619T5 (en) Gas turbine combustion chamber and provided with the same gas turbine
EP2159380A1 (en) Gas turbine assembly with a porous housing and fabrication method
EP3293356B1 (en) Blade for turbomachine comprising a movably supported impingement baffle and corresponding assembly method
EP2270397A1 (en) Gas turbine combustor and gas turbine
DE102018205721A1 (en) Blade for a turbomachine and use and manufacturing method thereof

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: 20170323

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

RIN1 Information on inventor provided before grant (corrected)

Inventor name: HAUSER, THOMAS

Inventor name: KREUTZER, ANDREAS

Inventor name: LAPP, PATRICK

Inventor name: PURSCHKE, SIMON

Inventor name: PIEGERT, SEBASTIAN

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

DAV Request for validation of the european patent (deleted)
DAX Request for extension of the european patent (deleted)
GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20180302

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): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM 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: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1019777

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180815

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502015005174

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20180718

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

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

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: 20180718

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: 20181019

Ref country code: NO

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: 20181018

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: 20180718

Ref country code: RS

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: 20180718

Ref country code: SE

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: 20180718

Ref country code: FI

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: 20180718

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: 20180718

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: 20181118

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: 20181018

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: 20180718

Ref country code: AL

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: 20180718

Ref country code: HR

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: 20180718

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502015005174

Country of ref document: DE

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

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: 20180718

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: 20180718

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: 20180718

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: 20180718

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: 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: 20180718

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: 20180718

Ref country code: SM

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: 20180718

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

26N No opposition filed

Effective date: 20190423

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20181031

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: 20181013

Ref country code: MC

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: 20180718

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

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

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: 20180718

Ref country code: BE

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

Effective date: 20181031

Ref country code: FR

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

Effective date: 20181031

Ref country code: LI

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

Effective date: 20181031

Ref country code: CH

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

Effective date: 20181031

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

Ref country code: IE

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

Effective date: 20181013

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: 20180718

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: 20180718

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

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: 20180718

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

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: 20180718

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; INVALID AB INITIO

Effective date: 20151013

Ref country code: MK

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

Effective date: 20180718

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

Effective date: 20191013

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: 20191013

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502015005174

Country of ref document: DE

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

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

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1019777

Country of ref document: AT

Kind code of ref document: T

Effective date: 20201013

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: 20201013

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

Ref country code: IT

Payment date: 20231024

Year of fee payment: 9

Ref country code: DE

Payment date: 20231027

Year of fee payment: 9