EP1816401A2 - Turbomachine - Google Patents
Turbomachine Download PDFInfo
- Publication number
- EP1816401A2 EP1816401A2 EP07100491A EP07100491A EP1816401A2 EP 1816401 A2 EP1816401 A2 EP 1816401A2 EP 07100491 A EP07100491 A EP 07100491A EP 07100491 A EP07100491 A EP 07100491A EP 1816401 A2 EP1816401 A2 EP 1816401A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- shell
- turbomachine
- lower half
- rotor
- front plate
- 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
Links
- 238000002485 combustion reaction Methods 0.000 claims abstract description 20
- 238000012423 maintenance Methods 0.000 claims abstract description 20
- 238000000034 method Methods 0.000 claims abstract description 10
- 238000006073 displacement reaction Methods 0.000 claims description 4
- 239000000969 carrier Substances 0.000 abstract 2
- 210000002105 tongue Anatomy 0.000 abstract 1
- 239000011248 coating agent Substances 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 230000000295 complement effect Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
Images
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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
Definitions
- the present invention relates to a turbomachine with a combustion chamber, in particular a gas turbine.
- the invention also relates to a method for disassembling an element of the turbomachine.
- Turbomachines such as gas turbines
- Turbomachines are now widely used in power plant engineering, and particularly economically, when running continuously.
- Longer downtimes and frequent startup or shutdown of the turbine have a negative effect on the service life of the turbine, since the material load is particularly high during startup and shutdown, on the other hand require longer downtime, for example by maintenance, high costs or Revenue loss.
- the material load is particularly high during startup and shutdown, on the other hand require longer downtime, for example by maintenance, high costs or Revenue loss.
- the costs as low as possible, it is anxious to use the turbomachinery in continuous operation.
- a temporary shutdown of the turbomachine due to maintenance to be performed can not be avoided, but these downtime should be as short as possible.
- the invention deals with the problem of specifying for a turbomachine of the type mentioned an embodiment which is characterized by a high ease of maintenance, in particular with regard to the combustion chamber components, and thus significantly reduced downtime and as a result reduced maintenance costs.
- the invention is based on the general idea constructively construct a turbomachine with a combustion chamber so that in the case of maintenance on the components can be easily and quickly accessed for the purpose of viewing, maintenance, the replacement or replacement of the components.
- a closable maintenance opening is provided on the housing at least in the region of the combustion chamber, which can be opened easily and quickly and, in the opened state, provides access to an outer support, an inner support and a front panel.
- the outer support, the inner support and the front panel together limit the combustion chamber and are thus exposed to high temperatures. These Temperature load in turn requires an interval maintenance, in which the functioning of said parts is checked and the parts may be renewed or replaced.
- the outer support, the inner support and the front panel are formed as annular shell elements, each having a lower half-shell and an upper half-shell connectable therewith.
- these In order to mount the outer support, the inner support and the front panel easy and accurate, these have axially acting connection contours, which allow a simple and quick release or connection of the said parts by moving in the axial direction.
- the annular shell elements By dividing the annular shell elements in each case a lower and thus connectable upper half-shell, the half-shells can be assembled and disassembled by the example mounted on the top maintenance opening, whereby the maintenance can be significantly reduced.
- At least one of the connecting contours is designed as an axially open circumferential groove or as a peripheral spring interacting with this circumferential groove.
- the tongue and groove effect achieved on the one hand facilitates the disassembly or assembling of the turbomachine and on the other hand ensures a precisely fitting joining of the combustion chamber delimiting shell elements.
- other connecting contours in particular in the form of mutually complementary projections or recesses conceivable, which also offer the advantages just mentioned.
- the upper half shells are formed so that they are axially displaceable for disassembly with respect to a rotor of the turbomachine and then radially removable.
- the upper half shells For disassembly of the upper half shells thus releasing the same from the corresponding lower half-shell or from a housing is required, whereupon the upper Half shells axially displaced and thus the connection contours can be detached from each other.
- the upper half shells for example by means of a lifting tool, can be removed radially with respect to the rotor.
- the assembly of the upper half shells takes place in the reverse order, so that they are initially approximated radially to the rotor and are moved parallel to the rotor before reaching their final installation position such that the connecting contours engage one another positively or rest against each other.
- a simple dismantling of the upper half-shell is made possible, which facilitates in particular maintenance.
- the lower half-shells are designed so that they are axially displaceable for their disassembly by means of an auxiliary tool, which is rotatably connected to the rotor, and rotatable about the rotor axis or with the rotor upwards.
- an auxiliary tool which is rotatably connected to the rotor, and rotatable about the rotor axis or with the rotor upwards.
- the lower half shell After loosening any existing connection means with which the lower half shell is attached to the housing and / or another lower half shell, the lower half shell can be moved for example by means of two movably arranged on the auxiliary tool carriage parallel to the rotor and thus out of the connection contour.
- the auxiliary tool By turning the rotor axis again by 180 °, the auxiliary tool can be turned upwards again and removed after loosening the connecting means between the auxiliary tool and the rotor of the latter.
- the half shells mentioned can be half shells of the front panel, the outdoor wearer or be the interior carrier. Overall, this greatly simplifies the assembly and disassembly process of the two half-shells.
- a combustion chamber 1 of a turbomachine 2 not shown otherwise, an outer support 3, a front plate 4 and an inner support 5 on. Both the outer support 3 and the front plate 4 and the inner support 5 are provided to the combustion chamber 1 out with a heat-resistant coating 6 and limit the combustion chamber 1.
- the inner support 5 and the front panel 4 in mounted Condition via axially releasable connection contours 7 and 7 'with each other and / or connected to a housing 8.
- the connecting contours 7 are symbolized by circles and can be formed, for example, as axially open circumferential grooves 9 and as cooperating with this peripheral groove 9 circumferential spring 10.
- Axial means parallel to a rotor 11.
- the other connecting contours 7 are formed as stage 12. All connecting contours 7 have in common that they provide an axial connection between the outer support 3, the inner support 5 and the front panel 4 and the housing 8.
- Both the outer support 3, and the inner support 5 and the front plate 4 are inventively designed as annular shell elements 13, each having a lower half-shell 14 and an upper half-shell 15 connectable thereto (see FIGS. 2 to 6).
- the upper half shells 15 are formed so that they are for disassembly with respect to the rotor 11 of Turbomachine 2 axially displaceable and then radially removable.
- the lower half-shells 14 are formed so that they are for their disassembly by means of an auxiliary tool 16 (see FIG. 4), which is rotatably connected to the rotor 11, axially displaceable and rotatable with the rotor 11 upwards.
- FIG. 2 is an axial front view of a turbomachine 2 is shown, which is circumferentially closed by the housing 8.
- the housing 8 is initially opened in the region of the combustion chamber 1 according to FIG. 3, so that access to the outer support 3 or its upper half shell 15 is released.
- the rotor axis 11 or the rotor 11 is in FIGS. 2 to 6 perpendicular to the image plane.
- the upper half shell 15 can be detached from the lower half shell 14, and axially, that is, as shown in FIGS. 2 to 6 be moved out of the picture plane or into the picture plane.
- the axial displacement causes a moving apart of the connecting contours 7, which release the upper half-shell 15 in the radial direction. After this release takes place a decrease in a substantially radial direction.
- auxiliary tool 16 rotatably connected via corresponding connecting means 17 to the rotor 11 of the turbomachine 2.
- the auxiliary tool 16 is connected via axially displaceable adapter slides 18 arranged therein with the lower half shell 15 in such a way that they are displaced axially, ie out of the image plane or into the image plane can.
- this axial displacement of the lower half shell 14 it is released from the axial connecting contours 7, which are shown in FIG.
- the lower half shell 14 is rotated with the rotor 11 by approximately 180 °, until the lower half shell 14 substantially assumes the position of the removed upper half shell 15 according to FIG.
- the rotation process is shown in Fig. 5.
- the turning operation is completed and the lower half-shell 14 has assumed the position of the previously removed upper half-shell 15.
- the upwardly twisted lower half shell 14 can be released from the auxiliary tool 16 and radially outward, for example, by a lifting tool in the form of a crane, removed.
- the turbomachine 2 according to the invention or the method according to the invention for dismantling the outer carrier 3 and / or the inner carrier 5 or the front plate 4 have several fundamental advantages.
- the housing 8 must have only a maintenance opening in the region of the combustion chamber 1 or be designed such that an upper housing part 8 'can be removed. As a result, the access to the upper half-shells 15 of the outer support 3, the inner support 5 and the front panel 4 is freed.
- a removal of a lower housing half 8 " can be omitted as well as the removal of the rotor 11th
- the inventive turbomachine 2 or the method according to the invention considerably simplifies maintenance, that is disassembly or replacement and reassembly of the outer support 3, the front panel 4 and the inner support 5, thereby reducing maintenance and thus also maintenance costs and associated downtimes the turbomachine 2 can be significantly reduced.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Die vorliegende Erfindung betrifft eine Strömungsmaschine mit einer Brennkammer, insbesondere eine Gasturbine. Die Erfindung betrifft außerdem ein Verfahren zur Demontage eines Elementes der Strömungsmaschine.The present invention relates to a turbomachine with a combustion chamber, in particular a gas turbine. The invention also relates to a method for disassembling an element of the turbomachine.
Strömungsmaschinen, wie beispielsweise Gasturbinen, sind heutzutage in der Kraftwerkstechnik weit verbreitet und insbesondere dann wirtschaftlich, wenn sie kontinuierlich laufen. Längere Stillstandszeiten sowie ein häufiges Hoch- bzw. Herunterfahren der Turbine wirken sich zum einen negativ auf die Lebensdauer der Turbine aus, da die Materialbelastung insbesondere beim Hoch- und Herunterfahren besonders hoch ist, zum anderen bedingen längere Stillstandszeiten, beispielsweise durch Wartungsarbeiten, hohe Kosten bzw. Einnahmenausfall. Um einerseits also die Materialbelastung und andererseits die Kosten so gering wie möglich zu halten, ist man bestrebt, die Strömungsmaschinen im Dauerbetrieb einzusetzen. Selbstverständlich lässt sich ein temporäres Stilllegen der Strömungsmaschine aufgrund von durchzuführenden Wartungsarbeiten nicht vermeiden, wobei jedoch diese Stillstandszeiten so kurz wie möglich sein sollten.Turbomachines, such as gas turbines, are now widely used in power plant engineering, and particularly economically, when running continuously. Longer downtimes and frequent startup or shutdown of the turbine have a negative effect on the service life of the turbine, since the material load is particularly high during startup and shutdown, on the other hand require longer downtime, for example by maintenance, high costs or Revenue loss. On the one hand so as to keep the material load and on the other hand, the costs as low as possible, it is anxious to use the turbomachinery in continuous operation. Of course, a temporary shutdown of the turbomachine due to maintenance to be performed can not be avoided, but these downtime should be as short as possible.
Auf die Länge der Stillstandszeiten hat insbesondere Einfluss, wie wartungsfreundlich die Strömungsmaschine aufgebaut ist, das heißt, wie einfach und schnell sie gewartet werden kann. Dabei verlängern komplizierte und aufwändige Konstruktionen die Stillstandszeit und verteuern die Wartung.On the length of downtime in particular affects how easy maintenance the turbomachine is built, that is, how easy and fast it can be maintained. At the same time, complicated and time-consuming designs extend downtime and make maintenance more expensive.
Hier setzt die Erfindung an. Die Erfindung, wie sie in den Ansprüchen gekennzeichnet ist, beschäftigt sich mit dem Problem, für eine Strömungsmaschine der eingangs erwähnten Art eine Ausführungsform anzugeben, die sich durch eine hohe Wartungsfreundlichkeit, insbesondere hinsichtlich der Brennkammerkomponenten, auszeichnet und damit erheblich reduzierte Stillstandszeiten und in deren Folge reduzierte Wartungskosten ermöglicht.This is where the invention starts. The invention, as characterized in the claims, deals with the problem of specifying for a turbomachine of the type mentioned an embodiment which is characterized by a high ease of maintenance, in particular with regard to the combustion chamber components, and thus significantly reduced downtime and as a result reduced maintenance costs.
Dieses Problem wird durch die Gegenstände der unabhängigen Ansprüche gelöst. Vorteilhafte Ausführungsformen sind Gegenstand der abhängigen Ansprüche.This problem is solved by the subject matters of the independent claims. Advantageous embodiments are the subject of the dependent claims.
Die Erfindung beruht auf dem allgemeinen Gedanken, eine Strömungsmaschine mit einer Brennkammer konstruktiv so aufzubauen, dass im Wartungsfalle auf deren Komponenten einfach und schnell zugegriffen werden kann zum Zwecke der Besichtigung, der Wartung, des Aus- oder des Wiedereinbaus der Komponenten. Hierzu ist am Gehäuse zumindest im Bereich der Brennkammer eine verschließbare Wartungsöffnung vorgesehen, welche einfach und schnell zu öffnen ist und in geöffnetem Zustand einen Zugang zu einem Außenträger, einem Innenträger und einer Frontplatte freigibt. Der Außenträger, der Innenträger und die Frontplatte begrenzen zusammen die Brennkammer und sind dadurch hohen Temperaturen ausgesetzt. Diese Temperaturbelastung wiederum bedingt eine intervallmäßige Wartung, bei der die Funktionstüchtigkeit der genannten Teile überprüft wird und die Teile ggf. erneuert oder ausgetauscht werden. Der Außenträger, der Innenträger und die Frontplatte sind als ringförmige Schalenelemente ausgebildet, die jeweils eine untere Halbschale und eine damit verbindbare obere Halbschale aufweisen. Um den Außenträger, den Innenträger und die Frontplatte einfach und passgenau montieren zu können, weisen diese axial wirkende Verbindungskonturen auf, welche ein einfaches und schnelles Lösen bzw. Verbinden der genannten Teile durch Verschieben in axialer Richtung erlauben. Durch die Aufteilung der ringförmigen Schalenelemente in jeweils eine untere und eine damit verbindbare obere Halbschale lassen sich die Halbschalen durch die z.B. an der Oberseite angebrachte Wartungsöffnung montieren und demontieren, wodurch der Wartungsaufwand erheblich gesenkt werden kann.The invention is based on the general idea constructively construct a turbomachine with a combustion chamber so that in the case of maintenance on the components can be easily and quickly accessed for the purpose of viewing, maintenance, the replacement or replacement of the components. For this purpose, a closable maintenance opening is provided on the housing at least in the region of the combustion chamber, which can be opened easily and quickly and, in the opened state, provides access to an outer support, an inner support and a front panel. The outer support, the inner support and the front panel together limit the combustion chamber and are thus exposed to high temperatures. These Temperature load in turn requires an interval maintenance, in which the functioning of said parts is checked and the parts may be renewed or replaced. The outer support, the inner support and the front panel are formed as annular shell elements, each having a lower half-shell and an upper half-shell connectable therewith. In order to mount the outer support, the inner support and the front panel easy and accurate, these have axially acting connection contours, which allow a simple and quick release or connection of the said parts by moving in the axial direction. By dividing the annular shell elements in each case a lower and thus connectable upper half-shell, the half-shells can be assembled and disassembled by the example mounted on the top maintenance opening, whereby the maintenance can be significantly reduced.
Bei einer bevorzugten Ausführungsform der erfindungsgemäßen Lösung ist zumindest eine der Verbindungskonturen als axial offene Umfangsnut oder als mit dieser Umfangsnut zusammenwirkende Umfangsfeder ausgebildet. Die so erzielte Nut- und Federwirkung erleichtert einerseits das Auseinanderbauen bzw. das Zusammenbauen der Strömungsmaschine und gewährleistet andererseits ein passgenaues Aneinanderfügen der die Brennkammer begrenzenden Schalenelemente. Darüber hinaus sind auch andere Verbindungskonturen, insbesondere in Form von komplementär zueinander ausgebildeten Vorsprüngen bzw. Ausnehmungen denkbar, welche ebenfalls die eben genannten Vorteile bieten.In a preferred embodiment of the solution according to the invention, at least one of the connecting contours is designed as an axially open circumferential groove or as a peripheral spring interacting with this circumferential groove. The tongue and groove effect achieved on the one hand facilitates the disassembly or assembling of the turbomachine and on the other hand ensures a precisely fitting joining of the combustion chamber delimiting shell elements. In addition, other connecting contours, in particular in the form of mutually complementary projections or recesses conceivable, which also offer the advantages just mentioned.
Vorzugsweise sind die oberen Halbschalen so ausgebildet, dass sie zur Demontage bezüglich eines Rotors der Strömungsmaschine axial verschiebbar und anschließend radial abnehmbar sind. Zur Demontage der oberen Halbschalen ist somit ein Lösen derselben von der entsprechenden unteren Halbschale bzw. von einem Gehäuse erforderlich, woraufhin die oberen Halbschalen axial verschoben und somit die Verbindungskonturen voneinander gelöst werden können. Nach dem Lösen der axialen Verbindungskonturen können die oberen Halbschalen, beispielsweise mittels eines Hebewerkzeuges, radial bezüglich des Rotors abgenommen werden. Die Montage der oberen Halbschalen erfolgt dabei in umgekehrter Reihenfolge, so dass diese zunächst radial an den Rotor angenähert werden und vor Erreichen ihrer endgültigen Einbauposition parallel zum Rotor derart verschoben werden, dass die Verbindungskonturen formschlüssig ineinander greifen bzw. aneinander anliegen. Hierdurch wird ein einfaches Abbauen der oberen Halbschale ermöglicht, was insbesondere Wartungsarbeiten erleichtert.Preferably, the upper half shells are formed so that they are axially displaceable for disassembly with respect to a rotor of the turbomachine and then radially removable. For disassembly of the upper half shells thus releasing the same from the corresponding lower half-shell or from a housing is required, whereupon the upper Half shells axially displaced and thus the connection contours can be detached from each other. After loosening the axial connection contours, the upper half shells, for example by means of a lifting tool, can be removed radially with respect to the rotor. The assembly of the upper half shells takes place in the reverse order, so that they are initially approximated radially to the rotor and are moved parallel to the rotor before reaching their final installation position such that the connecting contours engage one another positively or rest against each other. As a result, a simple dismantling of the upper half-shell is made possible, which facilitates in particular maintenance.
Bei einer weiteren vorteilhaften Ausführungsform der erfindungsgemäßen Lösung sind die unteren Halbschalen so ausgebildet, dass sie zu ihrer Demontage mittels eines Hilfswerkzeugs, welches drehfest mit dem Rotor verbindbar ist, axial verschiebbar und um die Rotorachse bzw. mit dem Rotor nach oben verdrehbar sind. Nach der Demontage der oberen Halbschale ist der Zugang zur unteren Halbschale frei, woraufhin besagtes Hilfswerkzeug einerseits drehfest mit dem Rotor und andererseits fest mit der unteren Halbschale verbunden werden kann. Nach dem Lösen von etwa vorhandenen Verbindungsmitteln, mit welchen die untere Halbschale am Gehäuse und/oder an einer anderen unteren Halbschale befestigt ist, kann die untere Halbschale z.B. mittels zweier beweglich am Hilfswerkzeug angeordneter Schlitten parallel zum Rotor und damit aus der Verbindungskontur heraus verschoben werden. Nach dem Verschieben kann die untere Halbschale mit dem Rotor um ca. 180° nach oben gedreht werden und dann einfach mit einem Hebewerkzeug, beispielsweise einem Kran, abgenommen werden. Durch nochmaliges Drehen der Rotorachse um 180° kann auch das Hilfswerkzeug wiederum nach oben gedreht werden und nach dem Lösen der Verbindungsmittel zwischen Hilfswerkzeug und Rotor von letzterem abgenommen werden. Die erwähnten Halbschalen können dabei Halbschalen der Frontplatte, des Außenträgers oder des Innenträgers sein. Ingesamt wird dadurch der Montage- bzw. Demontageprozess der beiden Halbschalen stark vereinfacht.In a further advantageous embodiment of the solution according to the invention, the lower half-shells are designed so that they are axially displaceable for their disassembly by means of an auxiliary tool, which is rotatably connected to the rotor, and rotatable about the rotor axis or with the rotor upwards. After disassembly of the upper half-shell access to the lower half-shell is free, whereupon said auxiliary tool on the one hand rotatably connected to the rotor and on the other hand firmly connected to the lower half-shell. After loosening any existing connection means with which the lower half shell is attached to the housing and / or another lower half shell, the lower half shell can be moved for example by means of two movably arranged on the auxiliary tool carriage parallel to the rotor and thus out of the connection contour. After moving the lower half-shell with the rotor can be rotated by about 180 ° upwards and then easily with a lifting tool, such as a crane, removed. By turning the rotor axis again by 180 °, the auxiliary tool can be turned upwards again and removed after loosening the connecting means between the auxiliary tool and the rotor of the latter. The half shells mentioned can be half shells of the front panel, the outdoor wearer or be the interior carrier. Overall, this greatly simplifies the assembly and disassembly process of the two half-shells.
Weitere wichtige Merkmale und Vorteile der erfindungsgemäßen Strömungsmaschine ergeben sich aus den Unteransprüchen, aus den Zeichnungen und aus der zugehörigen Figurenbeschreibung anhand der Zeichnungen.Other important features and advantages of the turbomachine according to the invention will become apparent from the subclaims, from the drawings and from the associated description of the figures with reference to the drawings.
Bevorzugte Ausführungsbeispiele der Erfindung sind in den Zeichnungen dargestellt und werden in der nachfolgenden Beschreibung näher erläutert, wobei sich gleiche Bezugszeichen auf gleiche oder ähnliche oder funktional gleiche Komponenten beziehen.Preferred embodiments of the invention are illustrated in the drawings and will be described in more detail in the following description, wherein like reference numerals refer to the same or similar or functionally identical components.
Es zeigen, jeweils stark schematisiert,
- Fig. 1
- einen Querschnitt durch eine Brennkammer,
- Fig. 2
- eine Axialansicht auf eine Strömungsmaschine bei geschlossenem Gehäuse,
- Fig. 3
- eine Darstellung wie in Fig. 2, jedoch bei geöffnetem Gehäuse im Bereich der Brennkammer und sichtbarer oberer Halbschale des Außenträgers,
- Fig. 4
- eine Darstellung wie in Fig. 3, jedoch bei entfernter oberer Halbschale des Außenträgers und am Rotor angeordnetem Hilfswerkzeug,
- Fig. 5
- eine Darstellung wie in Fig. 4, jedoch bei leicht verdrehtem Rotor,
- Fig. 6
- eine Darstellung wie in Fig. 4, jedoch bei um 180° gedrehten Rotor.
- Fig. 1
- a cross section through a combustion chamber,
- Fig. 2
- an axial view of a turbomachine with the housing closed,
- Fig. 3
- 2, but with the housing open in the region of the combustion chamber and visible upper half shell of the outer support,
- Fig. 4
- a representation as in FIG. 3, but with the upper half shell of the outer support removed and the auxiliary tool arranged on the rotor,
- Fig. 5
- a representation as in Fig. 4, but with a slightly twisted rotor,
- Fig. 6
- a representation as in Fig. 4, but with rotated by 180 ° rotor.
Entsprechend Fig. 1 weist eine Brennkammer 1 einer im übrigen nicht dargestellten Strömungsmaschine 2 einen Außenträger 3, eine Frontplatte 4 sowie einen Innenträger 5 auf. Sowohl der Außenträger 3 als auch die Frontplatte 4 und der Innenträger 5 sind zur Brennkammer 1 hin mit einer hitzebeständigen Beschichtung 6 versehen und begrenzen die Brennkammer 1. In den mit Kreisen markierten Bereichen sind der Außenträger 3, der Innenträger 5 und die Frontplatte 4 im montierten Zustand über axial voneinander lösbare Verbindungskonturen 7 bzw. 7' miteinander und/oder mit einem Gehäuse 8 verbunden. Die Verbindungskonturen 7 sind durch Kreise symbolisiert und können dabei beispielsweise als axial offene Umfangsnuten 9 und als mit dieser Umfangsnut 9 zusammenwirkende Umfangsfeder 10 ausgebildet sein. Axial bedeutet parallel zu einem Rotor 11. Neben einer Ausbildung der einen Verbindungskonturen 7 als Nuten und Federn ist auch denkbar, dass die anderen Verbindungskonturen 7, z.B. als Stufe 12 ausgebildet sind. Alle Verbindungskonturen 7 haben dabei gemein, dass sie eine axiale Verbindungsmöglichkeit zwischen dem Außenträger 3, dem Innenträger 5 und der Frontplatte 4 bzw. dem Gehäuse 8 schaffen.1, a
Sowohl der Außenträger 3, als auch der Innenträger 5 und die Frontplatte 4 sind erfindungsgemäß als ringförmige Schalenelemente 13 ausgebildet, welche jeweils eine untere Halbschale 14 und eine damit verbindbare obere Halbschale 15 aufweisen (vergleiche Fig. 2 bis 6). Die oberen Halbschalen 15 sind dabei so ausgebildet, dass sie zur Demontage bezüglich des Rotors 11 der Strömungsmaschine 2 axial verschiebbar und anschließend radial abnehmbar sind. Demgegenüber sind die unteren Halbschalen 14 so ausgebildet, dass sie zu ihrer Demontage mittels eines Hilfswerkzeugs 16 (vergleiche Fig. 4), welches drehfest mit dem Rotor 11 verbindbar ist, axial verschiebbar und mit dem Rotor 11 nach oben verdrehbar sind.Both the
Im Folgenden soll anhand der Fig. 2 bis 6 ein Verfahren zur Demontage eines Elementes einer Strömungsmaschine 2 näher erläutert werden.In the following, a method for dismantling an element of a
In Fig. 2 ist eine axiale Frontansicht auf eine Strömungsmaschine 2 gezeigt, welche umlaufend durch das Gehäuse 8 verschlossen ist. Zur Demontage des Außenträgers 3 wird zunächst gemäß Fig. 3 das Gehäuse 8 im Bereich der Brennkammer 1 geöffnet, so dass ein Zugang zum Außenträger 3 bzw. dessen oberer Halbschale 15 freigegeben wird. Die Rotorachse 11 bzw. der Rotor 11 steht in den Fig. 2 bis 6 senkrecht zur Bildebene. Nachdem der Zugang zum Außenträger 3 durch Entfernen einer oberen Gehäusehälfte 8' bzw. durch Öffnen einer nicht dargestellten verschließbaren Wartungsöffnung freigeben ist, kann die obere Halbschale 15 von der unteren Halbschale 14 gelöst werden, und axial, das heißt gemäß den Fig. 2 bis 6 aus der Bildebene heraus bzw. in die Bildebene hinein verschoben werden. Das axiale Verschieben bewirkt dabei ein Auseinanderfahren der Verbindungskonturen 7, welche die obere Halbschale 15 in radialer Richtung freigeben. Nach dieser Freigabe erfolgt ein Abnehmen in im wesentlichen radialer Richtung.In Fig. 2 is an axial front view of a
In Fig. 4 ist die obere Halbschale 15 des Außenträgers 3 bereits abgenommen und ein Hilfswerkzeug 16 drehfest über entsprechende Verbindungsmittel 17 mit dem Rotor 11 der Strömungsmaschine 2 verbunden. Gleichzeitig wird das Hilfswerkzeug 16 über darin angeordnete axial verschiebbare Adapterschlitten 18 mit der unteren Halbschale 15 derart verbunden, dass diese axial, das heißt aus der Bildebene heraus bzw. in die Bildebene hinein, verschoben werden kann. Durch diese axiale Verschiebung der unteren Halbschale 14 erfolgt ein Lösen derselben aus den axialen Verbindungskonturen 7, welche in Fig. 1 dargestellt sind.In Fig. 4, the upper half-
Im nächsten Demontageschritt erfolgt ein Verdrehen der unteren Halbschale 14 mit dem Rotor 11 um ca. 180°, bis die untere Halbschale 14 im wesentlichen die Position der entfernten oberen Halbschale 15 gemäß Fig. 3 einnimmt. Der Drehvorgang wird dabei in Fig. 5 dargestellt. Gemäß Fig. 6 ist der Drehvorgang abgeschlossen und die untere Halbschale 14 hat die Position der zuvor entfernten oberen Halbschale 15 eingenommen. Nun kann die nach oben verdrehte untere Halbschale 14 vom Hilfswerkzeug 16 gelöst werden und radial nach außen, beispielsweise durch ein Hebewerkzeug in Form eines Krans, abgenommen werden.In the next disassembly step, the
Die erfindungsgemäße Strömungsmaschine 2 bzw. das erfindungsgemäße Verfahren zum Demontieren des Außenträgers 3 und/oder des Innenträgers 5 bzw. der Frontplatte 4 weisen dabei mehrere grundlegende Vorteile auf. Das Gehäuse 8 muss im Bereich der Brennkammer 1 lediglich eine Wartungsöffnung aufweisen bzw. derart ausgebildet sein, dass ein oberes Gehäuseteil 8' abnehmbar ist. Hierdurch wird der Zugang zu den oberen Halbschalen 15 des Außenträgers 3, des Innenträgers 5 und der Frontplatte 4 freigebeben. Durch die Ausbildung eben genannter Elemente mit jeweils zwei Schalen, nämlich der unteren Halbschale 14 und der oberen Halbschale 15, kann ein stückweises Abnehmen der Halbschalen 14, 15 erfolgen. Die zunächst im unteren Gehäuseabschnitt 8" verbleibende untere Halbschale 14 kann durch Anordnen und drehfestes Verbinden des Hilfswerkzeugs 16 mit dem Rotor 11 nach oben verdreht werden und danach ebenfalls einfach mittels Hebewerkzeugen aus dem Gehäuse 8 entnommen werden. Durch die Ausbildung von Adapterschlitten 18 am Hilfswerkzeug 16, welche einfach und schnell mit der jeweiligen unteren Halbschale 14 des Außenträgers 3, der Frontplatte 4 und des Innenträgers 5 verbindbar sind, ist zusätzlich ein axiales Verschieben eben genannter Elemente und dadurch ein Lösen derselben aus deren Verbindungskonturen 7 problemlos möglich. Prinzipiell erfolgt dabei eine Demontage der Elemente der Strömungsmaschine 2 in der Reihenfolge Außenträger 3, Frontplatte 4 und Innenträger 5. Ein Entfernen einer unteren Gehäusehälfte 8" kann dabei ebenso entfallen wie das Entfernen des Rotors 11.The
Durch die erfindungsgemäße Strömungsmaschine 2 bzw. das erfindungsgemäße Verfahren vereinfacht sich die Wartung, das heißt ein Auseinanderbauen bzw. Austauschen und Wiederzusammenbauen des Außenträgers 3, der Frontplatte 4 und des Innenträgers 5, erheblich, wodurch der Wartungsaufwand und damit auch die Wartungskosten sowie damit verbundene Stillstandszeiten der Strömungsmaschine 2 deutlich reduziert werden können.The
- 11
- Brennkammercombustion chamber
- 22
- Strömungsmaschineflow machine
- 33
- Außenträgerbalconnet
- 44
- Frontplattefront panel
- 55
- Innenträgerinternal support
- 66
- Beschichtung / hitzebeständige SchichtCoating / heat-resistant layer
- 7, 7'7, 7 '
- Verbindungskonturconnection Silhouette
- 88th
- Gehäusecasing
- 8'8th'
- obere Gehäusehälfteupper half of the housing
- 8"8th"
- untere Gehäusehälftelower half of the housing
- 99
- Umfangsnutcircumferential groove
- 1010
- Umfangsfedercircumferential spring
- 1111
- Rotorrotor
- 11'11 '
- Rotorachserotor axis
- 1212
-
als Stufe ausgebildete Verbindungskontur 7formed as a
step connection contour 7 - 1313
- Schalenelementshell element
- 1414
- untere Halbschalelower half shell
- 1515
- obere Halbschaleupper half shell
- 1616
- Hilfswerkzeugauxiliary tool
- 1717
- Verbindungsmittelconnecting means
- 1818
- Adapterschlittenadapter sled
Claims (7)
dadurch gekennzeichnet,
dass zumindest eine der Verbindungskonturen (7) als axial offene Umfangsnut (9) oder als mit dieser Umfangsnut (9) zusammenwirkende Umfangsfeder (10) ausgebildet ist.Turbomachine according to claim 1,
characterized,
in that at least one of the connecting contours (7) is designed as an axially open circumferential groove (9) or as a circumferential spring (10) cooperating with this circumferential groove (9).
dadurch gekennzeichnet,
dass zumindest eine der Verbindungskonturen (7) als Stufe (12) ausgebildet ist.Turbomachine according to claim 1,
characterized,
in that at least one of the connecting contours (7) is designed as a step (12).
dadurch gekennzeichnet,
dass die oberen Halbschalen (15) so ausgebildet sind, dass sie zur Demontage bezüglich eines Rotors (11) der Strömungsmaschine (2) axial verschiebbar und anschließend radial abnehmbar sind.Turbomachine according to one of claims 1 to 3,
characterized,
in that the upper half-shells (15) are designed to be axially displaceable and subsequently radially removable for disassembly with respect to a rotor (11) of the turbomachine (2).
dadurch gekennzeichnet,
dass die unteren Halbschalen (14) so ausgebildet sind, dass sie zu ihrer Demontage mittels eines Hilfswerkzeugs (16), welches drehfest mit dem Rotor (11) verbindbar ist, axial verschiebbar und um die Rotorachse (11) nach oben verdrehbar sind.Turbomachine according to one of claims 1 to 4,
characterized,
in that the lower half-shells (14) are designed to be axially displaceable and to be rotatable upwards about the rotor axis (11) for disassembly by means of an auxiliary tool (16), which is connected in a rotationally fixed manner to the rotor (11).
dadurch gekennzeichnet,
dass der Innenträger (5), der Außenträger (3) und die Frontplatte (4) jeweils eine hitzebeständige Schicht (6) tragen.Turbomachine according to one of claims 1 to 5,
characterized,
that the inner carrier (5), the outer carrier (3) and the front panel (4) each having a heat-resistant layer (6) bear.
dadurch gekennzeichnet,
dass eine Demontage der Elemente (14, 15) der Strömungsmaschine (2) in der Reihenfolge Außenträger (3), Frontplatte (4), Innenträger (5) erfolgt.
characterized,
that a disassembly of the elements (14, 15) of the turbomachine (2) in the order outer carrier (3), front plate (4), inner carrier (5).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102006004785A DE102006004785A1 (en) | 2006-02-02 | 2006-02-02 | flow machine |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1816401A2 true EP1816401A2 (en) | 2007-08-08 |
EP1816401A3 EP1816401A3 (en) | 2014-01-15 |
EP1816401B1 EP1816401B1 (en) | 2014-09-03 |
Family
ID=38051776
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07100491.5A Active EP1816401B1 (en) | 2006-02-02 | 2007-01-12 | Turbomachine |
Country Status (3)
Country | Link |
---|---|
US (1) | US7726022B2 (en) |
EP (1) | EP1816401B1 (en) |
DE (1) | DE102006004785A1 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2009054050A1 (en) | 2007-10-23 | 2009-04-30 | Mitsubishi Heavy Industries, Ltd. | Method for demounting blade ring and member for demounting blade ring |
ITMI20101285A1 (en) * | 2010-07-13 | 2012-01-14 | Ansaldo Energia Spa | METHOD AND TOOL FOR MAINTENANCE OF A GAS TURBINE COMBUSTION CHAMBER |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8595930B2 (en) * | 2010-03-24 | 2013-12-03 | Dresser-Rand Company | Press-fitting corrosion resistant liners in nozzles and casings |
US8834114B2 (en) | 2011-09-29 | 2014-09-16 | General Electric Company | Turbine drum rotor retrofit |
US9097123B2 (en) | 2012-07-26 | 2015-08-04 | General Electric Company | Method and system for assembling and disassembling turbomachines |
EP2706199B1 (en) | 2012-09-10 | 2018-12-12 | Ansaldo Energia Switzerland AG | Method and guide for removing an inner casing from a turbomachine |
US9279342B2 (en) | 2012-11-21 | 2016-03-08 | General Electric Company | Turbine casing with service wedge |
US9260281B2 (en) | 2013-03-13 | 2016-02-16 | General Electric Company | Lift efficiency improvement mechanism for turbine casing service wedge |
CN112885759B (en) * | 2021-01-14 | 2024-05-28 | 上海新昇半导体科技有限公司 | Dismantling device and method for top connecting piece of round conveying box |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1211313A (en) * | 1968-06-24 | 1970-11-04 | Westinghouse Electric Corp | Bladed elastic fluid handling machine |
GB2263733A (en) * | 1992-01-28 | 1993-08-04 | Snecma | Turbomachine with removable combustion chamber. |
US5906473A (en) * | 1995-03-31 | 1999-05-25 | General Electric Co. | Removable inner turbine shell with bucket tip clearance control |
DE19821889A1 (en) * | 1998-05-15 | 1999-11-18 | Asea Brown Boveri | Access system for repair of gas turbine engine |
WO2002088601A1 (en) * | 2001-04-27 | 2002-11-07 | Siemens Aktiengesellschaft | Combustion chamber, in particular of a gas turbine |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2748567A (en) * | 1949-10-13 | 1956-06-05 | Gen Motors Corp | Gas turbine combustion chamber with telescoping casing and liner sections |
US3031844A (en) * | 1960-08-12 | 1962-05-01 | William A Tomolonius | Split combustion liner |
US3628884A (en) * | 1970-06-26 | 1971-12-21 | Westinghouse Electric Corp | Method and apparatus for supporting an inner casing structure |
US3741680A (en) * | 1972-04-05 | 1973-06-26 | Avco Corp | Split housing piloting device |
US6224332B1 (en) * | 1999-05-14 | 2001-05-01 | General Electric Co. | Apparatus and methods for installing, removing and adjusting an inner turbine shell section relative to an outer turbine shell section |
US6352405B1 (en) * | 2000-08-09 | 2002-03-05 | General Electric Company | Interchangeable turbine diaphragm halves and related support system |
US6752589B2 (en) * | 2002-10-15 | 2004-06-22 | General Electric Company | Method and apparatus for retrofitting a steam turbine and a retrofitted steam turbine |
US7617602B2 (en) * | 2005-08-18 | 2009-11-17 | General Electric Company | Method of servicing a turbine |
-
2006
- 2006-02-02 DE DE102006004785A patent/DE102006004785A1/en not_active Withdrawn
-
2007
- 2007-01-12 EP EP07100491.5A patent/EP1816401B1/en active Active
- 2007-01-17 US US11/623,778 patent/US7726022B2/en active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1211313A (en) * | 1968-06-24 | 1970-11-04 | Westinghouse Electric Corp | Bladed elastic fluid handling machine |
GB2263733A (en) * | 1992-01-28 | 1993-08-04 | Snecma | Turbomachine with removable combustion chamber. |
US5906473A (en) * | 1995-03-31 | 1999-05-25 | General Electric Co. | Removable inner turbine shell with bucket tip clearance control |
DE19821889A1 (en) * | 1998-05-15 | 1999-11-18 | Asea Brown Boveri | Access system for repair of gas turbine engine |
WO2002088601A1 (en) * | 2001-04-27 | 2002-11-07 | Siemens Aktiengesellschaft | Combustion chamber, in particular of a gas turbine |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2009054050A1 (en) | 2007-10-23 | 2009-04-30 | Mitsubishi Heavy Industries, Ltd. | Method for demounting blade ring and member for demounting blade ring |
EP2213846A1 (en) * | 2007-10-23 | 2010-08-04 | Mitsubishi Heavy Industries, Ltd. | Method for demounting blade ring and member for demounting blade ring |
EP2213846A4 (en) * | 2007-10-23 | 2013-10-23 | Mitsubishi Heavy Ind Ltd | Method for demounting blade ring and member for demounting blade ring |
ITMI20101285A1 (en) * | 2010-07-13 | 2012-01-14 | Ansaldo Energia Spa | METHOD AND TOOL FOR MAINTENANCE OF A GAS TURBINE COMBUSTION CHAMBER |
Also Published As
Publication number | Publication date |
---|---|
EP1816401B1 (en) | 2014-09-03 |
US20070175221A1 (en) | 2007-08-02 |
US7726022B2 (en) | 2010-06-01 |
DE102006004785A1 (en) | 2007-08-30 |
EP1816401A3 (en) | 2014-01-15 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1816401B1 (en) | Turbomachine | |
DE3514652C2 (en) | Axial gas turbine engine | |
EP2960438B1 (en) | Variable guide vane device for a gas turbine and gas turbine equipped with such a device | |
EP2798163B1 (en) | Method for pulling and/or inserting a turbine bearing and device for performing the method | |
DE602004002049T2 (en) | Low-pressure turbine of a turbomachine | |
DE102011054468B4 (en) | Variable turbine nozzle system | |
EP2655808B1 (en) | Method for pulling a bearing body off the rotor of a gas turbine and tubular shaft extension | |
DE602005000974T2 (en) | Turbomachine with counter-rotating fan | |
EP2379846B1 (en) | Guide vane support system for a turbomachine | |
EP0834645B1 (en) | Compressor wheel mounting for a turbocharger | |
EP2520767B1 (en) | Gas turbine rotor balance weight | |
DE60123907T2 (en) | Replaceable, adjustable guide vane for gas turbines | |
DE2633727A1 (en) | GAS TURBINE | |
WO2002090724A1 (en) | Casing ring | |
WO2016165950A1 (en) | Guide vane adjusting device and turbomachine | |
WO2015149732A2 (en) | Vane ring, inner ring, and turbomachine | |
EP2342425B1 (en) | Gas turbine with securing plate between blade base and disk | |
EP3287608B1 (en) | Internal ring for a guide- blade rim of a turbomachine | |
DE102017212575A1 (en) | Method for increasing the power of a gas turbine | |
EP2025867A1 (en) | Rotor for an axial flow engine | |
EP3176386B1 (en) | Inner shroud assembly, corresponding inner shroud, inner casing and turbomachine | |
EP3425172A1 (en) | Turbomachine sealing ring, turbomaching with such a seal ring and method of manufacturing such a seal ring | |
EP3156588B1 (en) | Repair method for seal segments | |
EP3628030A1 (en) | Method for maintaining a turbomachine | |
DE19643336A1 (en) | Method for disassembling the front bearing housing or LP compressor shaft part of an aircraft engine |
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 |
|
AK | Designated contracting states |
Kind code of ref document: A2 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 NL PL PT RO SE SI SK TR |
|
AX | Request for extension of the european patent |
Extension state: AL BA HR MK YU |
|
PUAL | Search report despatched |
Free format text: ORIGINAL CODE: 0009013 |
|
AK | Designated contracting states |
Kind code of ref document: A3 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 NL PL PT RO SE SI SK TR |
|
AX | Request for extension of the european patent |
Extension state: AL BA HR MK RS |
|
RIC1 | Information provided on ipc code assigned before grant |
Ipc: F01D 25/24 20060101ALI20131210BHEP Ipc: F23R 3/60 20060101ALI20131210BHEP Ipc: F23R 3/50 20060101AFI20131210BHEP |
|
17P | Request for examination filed |
Effective date: 20140220 |
|
RBV | Designated contracting states (corrected) |
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 NL PL PT RO SE SI SK TR |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
INTG | Intention to grant announced |
Effective date: 20140424 |
|
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 NL PL PT RO SE SI SK TR |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R081 Ref document number: 502007013410 Country of ref document: DE Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH Ref country code: DE Ref legal event code: R081 Ref document number: 502007013410 Country of ref document: DE Owner name: ANSALDO ENERGIA SWITZERLAND AG, CH Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: REF Ref document number: 685823 Country of ref document: AT Kind code of ref document: T Effective date: 20140915 Ref country code: CH Ref legal event code: EP |
|
AKX | Designation fees paid |
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 NL PL PT RO SE SI SK TR |
|
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: DE Ref legal event code: R096 Ref document number: 502007013410 Country of ref document: DE Effective date: 20141009 |
|
REG | Reference to a national code |
Ref country code: SE Ref legal event code: TRGR |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
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: 20140903 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: 20140903 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: 20141204 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: 20140903 |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: VDEP Effective date: 20140903 |
|
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: 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: 20140903 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: 20140903 |
|
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: 20140903 |
|
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: 20150105 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: 20140903 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: 20150103 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: 20140903 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: 20140903 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: 20140903 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
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: 20140903 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 502007013410 Country of ref document: DE |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: BE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20150131 |
|
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: 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: 20140903 |
|
26N | No opposition filed |
Effective date: 20150604 |
|
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: LU 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: 20150112 |
|
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 FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20140903 |
|
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: 20150131 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20150131 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: ST Effective date: 20150930 |
|
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: 20140903 Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20150202 |
|
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: 20150112 |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MM01 Ref document number: 685823 Country of ref document: AT Kind code of ref document: T Effective date: 20150112 |
|
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: 20150112 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R081 Ref document number: 502007013410 Country of ref document: DE Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH Ref country code: DE Ref legal event code: R081 Ref document number: 502007013410 Country of ref document: DE Owner name: ANSALDO ENERGIA SWITZERLAND AG, CH Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: SE Payment date: 20170119 Year of fee payment: 11 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
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: 20140903 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: 20070112 |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: 732E Free format text: REGISTERED BETWEEN 20170727 AND 20170802 |
|
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: 20140903 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R081 Ref document number: 502007013410 Country of ref document: DE Owner name: ANSALDO ENERGIA SWITZERLAND AG, CH Free format text: FORMER OWNER: GENERAL ELECTRIC TECHNOLOGY GMBH, BADEN, CH |
|
REG | Reference to a national code |
Ref country code: SE Ref legal event code: EUG |
|
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: 20180113 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20230228 Year of fee payment: 17 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: IT Payment date: 20230328 Year of fee payment: 17 Ref country code: DE Payment date: 20230525 Year of fee payment: 17 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R119 Ref document number: 502007013410 Country of ref document: DE |