EP2092164A1 - Turbomachine, particularly a gas turbine - Google Patents

Turbomachine, particularly a gas turbine

Info

Publication number
EP2092164A1
EP2092164A1 EP07847789A EP07847789A EP2092164A1 EP 2092164 A1 EP2092164 A1 EP 2092164A1 EP 07847789 A EP07847789 A EP 07847789A EP 07847789 A EP07847789 A EP 07847789A EP 2092164 A1 EP2092164 A1 EP 2092164A1
Authority
EP
European Patent Office
Prior art keywords
rotor
blade
adjacent
seal
stator
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
EP07847789A
Other languages
German (de)
French (fr)
Other versions
EP2092164B1 (en
Inventor
Maxim Konter
Alexander Khanin
Alexander Burmistrov
Sergey Vorontsov
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP2092164A1 publication Critical patent/EP2092164A1/en
Application granted granted Critical
Publication of EP2092164B1 publication Critical patent/EP2092164B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades

Definitions

  • the present invention relates to a rotating turbomachine, in particular a gas turbine.
  • Rotary turbomachines usually have a rotor having at least two blade rows with multiple blades and at least one rotor heat shield with a plurality of shield elements, wherein the respective rotor heat shield is arranged axially between two adjacent blade rows. Furthermore, such a turbomachine usually comprises a stator which has at least one row of guide vanes arranged axially between two adjacent blade rows and having a plurality of guide vanes.
  • the invention aims to remedy this situation.
  • the invention as characterized in the claims, deals with the problem, for a turbomachine of the type mentioned, to provide an improved embodiment, which is characterized in particular by an increased efficiency.
  • the invention is based on the general idea of combining an axial seal, which is formed by the interaction of a stator seal structure with a rotor-seal structure, with a radial seal passing through from one blade via the shield element to the other blade. To this way, leaks in the axial direction and in the radial direction can be reduced, which increases the efficiency of the turbomachine or its efficiency.
  • the continuous radial seal is realized in the turbomachine according to the invention in that the protective shield elements and the rotor blades are coordinated so that the protective shield radial formed in the region of the shield elements passes uninterrupted into the blade radial seals formed in the region of the blades.
  • the radial seals can be realized by means of sealing elements, which are arranged in the shield shield elements in protective shield grooves and in the region of the blades in blade grooves.
  • the shield elements between their axial ends each have a radially inwardly recessed recess in which the rotor seal structure is arranged.
  • said recess is dimensioned so that the axial seal is formed within this recess and is arranged offset radially inwardly relative to the blade radial seals of the adjacent blades.
  • This design ensures that the axial seal is located in a region which is virtually outside a gas flow flowing in the gas path of the turbomachine, which improves the effectiveness of the axial seal. Through the depression, virtually a dead water zone is formed within the gas path, in which the axial seal achieves an improved sealing effect.
  • FIGURE shows a simplified longitudinal section through a portion of a turbomachine. Ways to carry out the invention
  • a rotating turbomachine 1 which is shown only partially, comprises a rotor 2 and a stator 3.
  • the turbomachine 1 which is preferably a gas turbine, but which is also a compressor or a steam turbine can act
  • the rotor 2 rotates about a rotor axis 4, which simultaneously defines the axial direction of the turbomachine 1.
  • the rotor 2 has at least two rows of blades 5, each having a plurality of circumferentially adjacent to each other blades 6.
  • the rotor 2 has at least one rotor heat shield 7, which is arranged in each case axially between two adjacent rotor blade rows 5. In the illustrated section of the turbomachine 1, two rotor heat shields 7 can be seen.
  • the stator 3 may have a plurality of stator blade rows 8, of which at least one is arranged axially between two adjacent blade rows 5.
  • Each vane row 8 has a plurality of circumferentially adjacent vanes 9.
  • the at least one vane row 8 arranged axially between two adjacent rows of rotor blades 5 is regularly meant.
  • the guide vanes 9 of at least one of these guide blade rows 8 have radially inward a stator seal structure 10, which can be designed to be closed in the circumferential direction.
  • a stator seal structure 10 which can be designed to be closed in the circumferential direction.
  • each vane 9 radially inwardly at its blade tip a flat, circumferentially and axially extending platform 11, which may be configured in the manner of a shroud.
  • the stator seal structure 10 is disposed on these vane platforms 11.
  • the respective rotor heat shield 7 generally includes a plurality of circumferentially adjacent shield members 12 which form the respective rotor heat shield 7 in the manner of ring segments.
  • the individual shield elements 12 have radially outside a rotor seal structure 13 which extends closed in the circumferential direction.
  • the rotor-seal structure 13 and the stator-seal structure 10 are arranged radially adjacent thereto and cooperate to form an axial seal 14.
  • the section plane selected in FIG. 1 lies in the circumferential direction between two adjacent rotor blades 6 and between two shield elements 12 adjacent in the circumferential direction.
  • the sectional plane thus lies in a longitudinal gap, which forms in each case between two rotor blades 6 or protective shield elements 12 which are adjacent in the circumferential direction.
  • a blade radial seal 15 is formed on each side between two adjacent moving blades 6 of the same blade row 5, while on the other hand, a respective protective shield radial seal 16 is formed between two adjacent shielding elements 12.
  • Both the respective blade radial seal 15 and the respective protective shield radial seal 16 separate in the radial direction a gas path 17, the turbomachine 1 from the rotor 2 and from a cooling gas path 18 which is formed radially between the rotor 2 and the respective radial seal 15, 16.
  • the respective working gas such as a hot gas
  • a corresponding gas flow is symbolized by arrows 19.
  • the blades 6 and the vanes 9 each extend through the gas path 17.
  • a cooling gas flow which is indicated by arrows 20.
  • the shield elements 12 and the blades 6 of the rotor heat shield 7 adjacent blade rows 5 are so each other matched so that the shield radial seal 16 passes without interruption both in the upstream blade radial seal 15 and in the downstream blade radial seal 15.
  • This uninterrupted transition between the shield radial seal 16 and the two blade radial seals 15 is realized so that it can form a radial seal 21, which in the longitudinal direction of the one blade 6 via the respective shield member 12 to the other blade 6 quasi seamless or continuous is designed. It is noteworthy that both in an upstream transition 22 and at a downstream transition 23 between the shield element 12 and the respective blade 6, a continuous radial seal 21 can be realized.
  • the respective blade radial seal 15 comprises in the region of blade roots 24 of the circumferentially adjacent blades 6 each a circumferentially open blade groove 25.
  • the two blade grooves 25 of the respective blade radial seal 15 are aligned with their open sides facing each other, so that in these blade grooves 25 a plate-shaped or band-shaped sealing element 26 can be inserted.
  • the shield radial seal 16 is constructed in a corresponding manner and has in regions 27 which adjoin the rotor seal structure 13, in the circumferentially adjacent shield elements 12 in each case one in the circumferential direction open Schutzschildnut 28.
  • the protective shield grooves 28 of the two shielding elements 12 adjacent to one another in the circumferential direction are aligned with one another in the circumferential direction, so that a plate-shaped or band-shaped sealing element 26 can likewise be inserted into the protective shield grooves 28.
  • the shield grooves 28 and the blade grooves 25 are suitably matched to one another so that in the transition regions 22, 23 axial longitudinal ends 29 of the shield grooves 28 axially aligned axially adjacent axial longitudinal ends 30 of the blade grooves 25.
  • sealing element 26 which extends in the respective grooves 25, 28 from the one blade row 5 on the rotor heat shield 7 to the other blade row 5.
  • a plurality of sealing elements 26 may be provided, in particular adjacent sealing elements 26 axially abutting one another between the axial longitudinal ends 29 of the protective shield grooves 28 and / or between the axial longitudinal ends 30 of the respective blade grooves 25.
  • comparatively small sealing elements 26, which are arranged only in the respective transitional region 22 or 23 for bridging the annular axial gap there, extending on the one hand into the protective shield grooves 28 and on the other hand into the blade grooves 25.
  • the shield elements 12 may according to the embodiment shown here between their axial ends, ie between the transition regions 22, 23 have a radially inwardly recessed recess 31.
  • the rotor seal structure 13 is arranged.
  • the guide vanes 9 are here dimensioned so that the stator seal structure 10 is disposed within this recess 31.
  • the recess 31 may be dimensioned so that the formed by the interaction of the rotor seal structure 13 with the stator seal structure 10 axial seal 14 is formed within the recess 31.
  • the axial seal 14 is arranged offset radially inwardly relative to the blade radial seals 15 of the adjacent blades 6. As a result, the axial seal 14 is located radially outside the gas flow 19 in the gas path 17 and in particular in a dead water region of the gas flow 19.
  • the stator seal structure 10 may be configured so as to be grindable.
  • the stator-seal structure 10 may be designed as a honeycomb structure 33 with radially oriented honeycombs for this purpose.
  • the rotor seal structure 13 is designed einschleifend.
  • the rotor-seal structure 13 is formed by at least one blade-shaped annular web 32. In the example shown, two such annular webs 32 are provided, which are arranged spaced apart in the axial direction.
  • the rotor-seal structure 13 can be looped into the stator-seal structure 10, that is to say the respective annular web 32 penetrates into the honeycomb structure 33.
  • stator seal structure 10 and the rotor seal structure 13 cooperate to form the axial seal 14 in the manner of a labyrinth seal.
  • stator seal structure 10 more, z. B. have two annular axial sections 34 which are offset from an adjacent thereto, here middle annular axial section 35 radially outward.
  • the rotor-seal structure 13 then has several, here two radially outwardly projecting annular webs 32, which are each arranged in the region of one of the radially outwardly offset radial sections 34.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Low-Molecular Organic Synthesis Reactions Using Catalysts (AREA)

Abstract

A gas turbine (1) includes a rotor (2) which has two rotor blade rows (5) with a plurality of rotor blades (6), and also a rotor heat shield (7), which is arranged between them, with a plurality of heat shield elements (12), and with a stator (3) which has a stator blade row (8), with a plurality of stator blades (9), which is arranged axially between the two adjacent rotor blade rows (5). The stator blades (9) have a stator sealing structure (10) radially on the inside. The heat shield elements (12) have a rotor sealing structure (13) radially on the outside which interacts with the stator sealing structure (10) for forming an axial seal (14). Furthermore, a blade radial seal (15) is formed between two adjacent rotor blades (6), and also a heat shield radial seal (16) is formed between two adjacent heat shield elements (12), and in each case separates a gas path (17) from the rotor (2). For increasing efficiency, the heat shield elements (12) and the rotor blades (6) are matched to each other so that the heat shield radial seal (16) merges without interruption into the blade radial seals (15) of the two axially adjacent rotor blades (6) in such a way that a continuous radial seal (21) is formed from the one rotor blade (6), via the heat shield element (12), to the other rotor blade (6).

Description

Strömungsmaschine, insbesondere Gasturbine Turbomachine, in particular gas turbine
Technisches GebietTechnical area
Die vorliegende Erfindung betrifft eine rotierende Strömungsmaschine, insbesondere eine Gasturbine.The present invention relates to a rotating turbomachine, in particular a gas turbine.
Stand der TechnikState of the art
Rotierende Strömungsmaschinen besitzen üblicherweise einen Rotor, der wenigstens zwei Laufschaufelreihen mit mehreren Laufschaufeln sowie wenigstens ein Rotorhitzeschutzschild mit mehreren Schutzschildelementen aufweist, wobei das jeweilige Rotorhitzeschutzschild axial zwischen zwei benachbarten Laufschaufelreihen angeordnet ist. Ferner umfasst eine derartige Strömungsmaschine üblicherweise einen Stator, der wenigstens eine, axial zwischen zwei benachbarten Laufschaufelreihen angeordnete Leitschaufelreihe mit mehreren Leitschaufeln aufweist.Rotary turbomachines usually have a rotor having at least two blade rows with multiple blades and at least one rotor heat shield with a plurality of shield elements, wherein the respective rotor heat shield is arranged axially between two adjacent blade rows. Furthermore, such a turbomachine usually comprises a stator which has at least one row of guide vanes arranged axially between two adjacent blade rows and having a plurality of guide vanes.
Zur Ausbildung einer Axialdichtung im Bereich der Leitschaufelreihe ist es grundsätzlich möglich, die Leitschaufeln der Leitschaufel reihe radial innen mit einer in Umfangshchtung geschlossenen Statordichtstruktur auszustatten und die Schutzschildelemente radial außen mit einer in Umfangsrichtung geschlossenen Rotordichtstruktur auszustatten, die mit der Statordichtstruktur zur Ausbildung der Axialdichtung zusammenwirkt. Ferner ist es grundsätzlich möglich, einen Gaspfad der Strömungsmaschine, durch den sich die Laufschaufeln und die Leitschaufeln erstrecken, vom Rotor bzw. von einem Kühlgaspfad mit Hilfe von Radialdichtungen zu trennen, die zwischen in Umfangshchtung benachbarten Laufschaufeln oder zwischen in Umfangshchtung benachbarten Schutzschildelementen ausgebildet sein können.In order to form an axial seal in the region of the guide blade row, it is basically possible to provide the guide vanes in the radial direction with a stator seal structure closed in the circumferential direction and the protective shield elements radially outwardly with a circumferentially closed Provide rotor seal structure, which cooperates with the stator seal structure to form the axial seal. Furthermore, it is basically possible to separate a gas path of the turbomachine, through which the moving blades and the guide blades extend, from the rotor or from a cooling gas path with the aid of radial seals which can be formed between circumferentially adjacent blades or between shielding elements adjacent to each other in the circumferential direction ,
Zur Leistungssteigerung bzw. zur Erhöhung des Wirkungsgrads einer derartigen Strömungsmaschine besteht permanent ein Bedürfnis, Leckageströmungen im Bereich von Dichtungen zur reduzieren.To increase performance or to increase the efficiency of such a turbomachine, there is a constant need to reduce leakage flows in the range of seals.
Darstellung der ErfindungPresentation of the invention
Hier will die Erfindung Abhilfe schaffen. Die Erfindung, wie sie in den Ansprüchen gekennzeichnet ist, beschäftigt sich mit dem Problem, für eine Strömungsmaschine der eingangs genannten Art, eine verbesserte Ausführungsform anzugeben, die sich insbesondere durch einen erhöhten Wirkungsgrad auszeichnet.The invention aims to remedy this situation. The invention, as characterized in the claims, deals with the problem, for a turbomachine of the type mentioned, to provide an improved embodiment, which is characterized in particular by an increased efficiency.
Erfindungsgemäß wird dieses Problem durch den Gegenstand des unabhängigen Anspruchs gelöst. Vorteilhafte Ausführungsformen sind Gegenstand der abhängigen Ansprüche.According to the invention, this problem is solved by the subject matter of the independent claim. Advantageous embodiments are the subject of the dependent claims.
Die Erfindung beruht auf dem allgemeinen Gedanken, eine Axialdichtung, die durch das Zusammenwirken einer Statordichtstruktur mit einer Rotordichtstruktur gebildet ist, mit einer von einer Laufschaufel über das Schutzschildelement zur anderen Laufschaufel durchgehenden Radialdichtung zu kombinieren. Auf diese Weise können Leckagen in axialer Richtung sowie in radialer Richtung reduziert werden, was die Leistungsfähigkeit der Strömungsmaschine bzw. deren Wirkungsgrad erhöht. Die Kombination der Axialdichtung im Bereich des Rotorhitzeschutzschilds mit der in axialer Richtung über das Rotorhitzeschutzschild durchgehenden, also unterbrechungsfreien oder lückenlosen Radialdichtung spielt dabei zur Wirkungsgradsteigerung zusammen. Die durchgehende Radialdichtung wird bei der erfindungsgemäßen Strömungsmaschine dadurch realisiert, dass die Schutzschildelemente und die Laufschaufeln so aufeinander abgestimmt sind, dass die im Bereich der Schutzschildelemente ausgebildete Schutzschildradialdichtung unterbrechungsfrei in die im Bereich der Laufschaufeln ausgebildete Schaufelradialdichtungen übergeht.The invention is based on the general idea of combining an axial seal, which is formed by the interaction of a stator seal structure with a rotor-seal structure, with a radial seal passing through from one blade via the shield element to the other blade. To this In this way, leaks in the axial direction and in the radial direction can be reduced, which increases the efficiency of the turbomachine or its efficiency. The combination of the axial seal in the region of the rotor heat shield with the continuous in the axial direction over the rotor heat shield, so uninterrupted or gapless radial seal plays together to increase efficiency. The continuous radial seal is realized in the turbomachine according to the invention in that the protective shield elements and the rotor blades are coordinated so that the protective shield radial formed in the region of the shield elements passes uninterrupted into the blade radial seals formed in the region of the blades.
Bei einer vorteilhaften Ausführungsform können die Radialdichtungen mit Hilfe von Dichtelementen realisiert werden, die im Bereich der Schutzschildelemente in Schutzschildnuten und im Bereich der Laufschaufeln in Schaufelnuten angeordnet sind. Durch eine spezielle Abstimmung der Schutzschildelemente und der Laufschaufeln aufeinander kann erreicht werden, dass axiale Längsenden der Schutzschildnuten zu axial benachbarten axialen Längsenden der Schaufelnuten axial fluchten, wodurch es möglich ist, plattenförmige oder bandförmige Dichtelemente so anzuordnen, dass sie sich zum Teil in den Schutzschildnuten und zum Teil in den Schaufelnuten zumindest einer der benachbarten Laufschaufeln erstrecken. Auf diese Weise kann ein Axialspalt, der axial zwischen dem Schutzschildelement und der jeweiligen Laufschaufel ausgebildet ist, durch das jeweilige Dichtelement in einem Bereich, der in Umfangsrichtung zwischen benachbarten Schutzschildelementen bzw. in Umfangsrichtung zwischen benachbarten Laufschaufeln angeordnet ist, effektiv abgedeckt werden, was die Dichtungswirkung der so gebildeten Radialdichtung erheblich verbessert. Bei einer anderen vorteilhaften Ausführungsform können die Schutzschildelemente zwischen ihren axialen Enden jeweils eine radial nach innen zurückspringende Vertiefung aufweisen, in der die Rotordichtstruktur angeordnet ist. Besonders vorteilhaft ist dabei eine Weiterbildung, bei welcher die genannte Vertiefung so dimensioniert ist, dass die Axialdichtung innerhalb dieser Vertiefung ausgebildet ist und relativ zu den Schaufelradialdichtungen der benachbarten Laufschaufeln radial nach innen versetzt angeordnet ist. Durch diese Bauweise wird erreicht, dass sich die Axialdichtung in einem Bereich befindet, der sich quasi außerhalb einer im Gaspfad der Strömungsmaschine strömenden Gasströmung befindet, was die Effektivität der Axialdichtung verbessert. Durch die Vertiefung wird innerhalb des Gaspfades quasi eine Totwasserzone gebildet, in der die Axialdichtung eine verbesserte Dichtungswirkung erzielt.In an advantageous embodiment, the radial seals can be realized by means of sealing elements, which are arranged in the shield shield elements in protective shield grooves and in the region of the blades in blade grooves. By a special vote of the shield elements and the blades to each other can be achieved that axial longitudinal ends of the shield grooves axially aligned axially adjacent axial longitudinal ends of the blade grooves, whereby it is possible to arrange plate-shaped or band-shaped sealing elements so that they are partially in the shield and extend in part in the blade grooves of at least one of the adjacent blades. In this way, an axial gap formed axially between the shield member and the respective blade can be effectively covered by the respective seal member in an area circumferentially between adjacent shield members or circumferentially between adjacent blades, which has the sealing effect the radial seal thus formed significantly improved. In another advantageous embodiment, the shield elements between their axial ends each have a radially inwardly recessed recess in which the rotor seal structure is arranged. Particularly advantageous is a development in which said recess is dimensioned so that the axial seal is formed within this recess and is arranged offset radially inwardly relative to the blade radial seals of the adjacent blades. This design ensures that the axial seal is located in a region which is virtually outside a gas flow flowing in the gas path of the turbomachine, which improves the effectiveness of the axial seal. Through the depression, virtually a dead water zone is formed within the gas path, in which the axial seal achieves an improved sealing effect.
Weitere wichtige Merkmale und Vorteile der erfindungsgemäßen Strömungsmaschine ergeben sich aus den Unteransprüchen, aus der Zeichnung und aus der zugehörigen Figurenbeschreibung anhand der Zeichnung.Further important features and advantages of the turbomachine according to the invention will become apparent from the subclaims, from the drawing and from the associated description of the figures with reference to the drawing.
Kurze Beschreibung der ZeichnungenBrief description of the drawings
Ein bevorzugtes Ausführungsbeispiel der Erfindung ist in der Zeichnung dargestellt und wird in der nachfolgenden Beschreibung näher erläutert.A preferred embodiment of the invention is illustrated in the drawing and will be explained in more detail in the following description.
Die einzige Figur zeigt einen vereinfachten Längsschnitt durch einen Teilbereich einer Strömungsmaschine. Wege zur Ausführung der ErfindungThe single FIGURE shows a simplified longitudinal section through a portion of a turbomachine. Ways to carry out the invention
Entsprechend Fig. 1 umfasst eine nur teilweise dargestellte rotierende Strömungsmaschine 1 einen Rotor 2 und einen Stator 3. Im Betrieb der Strömungsmaschine 1 , bei der es sich vorzugsweise um eine Gasturbine handelt, bei der es sich jedoch auch um einen Verdichter bzw. um eine Dampfturbine handeln kann, rotiert der Rotor 2 um eine Rotorachse 4, die gleichzeitig die Axialrichtung der Strömungsmaschine 1 definiert. Der Rotor 2 weist zumindest zwei Laufschaufelreihen 5 auf, die jeweils mehrere, in Umfangshchtung zueinander benachbarte Laufschaufeln 6 aufweisen. Des Weiteren besitzt der Rotor 2 zumindest ein Rotorhitzeschutzschild 7, das jeweils axial zwischen zwei benachbarten Laufschaufelreihen 5 angeordnet ist. Im dargestellten Ausschnitt der Strömungsmaschine 1 sind zwei Rotorhitzeschutzschilde 7 erkennbar. Der Stator 3 kann mehrere Leitschaufelreihen 8 aufweisen, von denen zumindest eine axial zwischen zwei benachbarten Laufschaufelreihen 5 angeordnet ist. Jede Leitschaufelreihe 8 weist mehrere, in Umfangsrichtung benachbarte Leitschaufeln 9 auf. Wenn im Folgenden von der Leitschaufelreihe 8 die Rede ist, ist regelmäßig die wenigstens eine, axial zwischen zwei benachbarten Laufschaufelreihen 5 angeordnete Leitschaufelreihe 8 gemeint.According to FIG. 1, a rotating turbomachine 1, which is shown only partially, comprises a rotor 2 and a stator 3. During operation of the turbomachine 1, which is preferably a gas turbine, but which is also a compressor or a steam turbine can act, the rotor 2 rotates about a rotor axis 4, which simultaneously defines the axial direction of the turbomachine 1. The rotor 2 has at least two rows of blades 5, each having a plurality of circumferentially adjacent to each other blades 6. Furthermore, the rotor 2 has at least one rotor heat shield 7, which is arranged in each case axially between two adjacent rotor blade rows 5. In the illustrated section of the turbomachine 1, two rotor heat shields 7 can be seen. The stator 3 may have a plurality of stator blade rows 8, of which at least one is arranged axially between two adjacent blade rows 5. Each vane row 8 has a plurality of circumferentially adjacent vanes 9. When reference is made below to the guide vane row 8, the at least one vane row 8 arranged axially between two adjacent rows of rotor blades 5 is regularly meant.
Die Leitschaufeln 9 zumindest einer dieser Leitschaufelreihen 8 weisen radial innen eine Statordichtstruktur 10 auf, die in Umfangsrichtung geschlossen ausgestaltet sein kann. Hierzu kann beispielsweise jede Leitschaufel 9 radial innen an ihrer Schaufelspitze eine flächige, sich in Umfangsrichtung sowie axial erstreckende Plattform 11 aufweisen, die nach Art eines Deckbands ausgestaltet sein kann. Die Statordichtstruktur 10 ist an diesen Leitschaufelplattformen 11 angeordnet. Das jeweilige Rotorhitzeschutzschild 7 umfasst in der Regel mehrere, in Umfangsrichtung benachbarte Schutzschildelemente 12, die nach Art von Ringsegmenten das jeweilige Rotorhitzeschutzschild 7 bilden. Die einzelnen Schutzschildelemente 12 weisen radial außen eine Rotordichtstruktur 13 auf, die sich in Umfangsrichtung geschlossen erstreckt. Die Rotordichtstruktur 13 und die Statordichtstruktur 10 sind dabei radial benachbart angeordnet und wirken zur Ausbildung einer Axialdichtung 14 zusammen.The guide vanes 9 of at least one of these guide blade rows 8 have radially inward a stator seal structure 10, which can be designed to be closed in the circumferential direction. For this purpose, for example, each vane 9 radially inwardly at its blade tip a flat, circumferentially and axially extending platform 11, which may be configured in the manner of a shroud. The stator seal structure 10 is disposed on these vane platforms 11. The respective rotor heat shield 7 generally includes a plurality of circumferentially adjacent shield members 12 which form the respective rotor heat shield 7 in the manner of ring segments. The individual shield elements 12 have radially outside a rotor seal structure 13 which extends closed in the circumferential direction. The rotor-seal structure 13 and the stator-seal structure 10 are arranged radially adjacent thereto and cooperate to form an axial seal 14.
Die in Fig. 1 gewählte Schnittebene liegt in Umfangsrichtung zwischen zwei benachbarten Laufschaufeln 6 sowie zwischen zwei in Umfangsrichtung benachbarten Schutzschildelementen 12. Die Schnittebene liegt somit in einem Längsspalt, der sich jeweils zwischen zwei in Umfangsrichtung benachbarten Laufschaufeln 6 bzw. Schutzschildelementen 12 ausbildet. Im Bereich dieses Längsspalts ist einerseits jeweils zwischen zwei benachbarten Laufschaufeln 6 der gleichen Laufschaufelreihe 5 eine Schaufelradialdichtung 15 ausgebildet, während andererseits zwischen zwei benachbarten Schutzschildelementen 12 jeweils eine Schutzschildradialdichtung 16 ausgebildet ist. Sowohl die jeweilige Schaufelradialdichtung 15 als auch die jeweilige Schutzschildradialdichtung 16 trennt in radialer Richtung einen Gaspfad 17, der Strömungsmaschine 1 vom Rotor 2 bzw. von einem Kühlgaspfad 18, der radial zwischen dem Rotor 2 und der jeweiligen Radialdichtung 15, 16 ausgebildet ist. Im Gaspfad 17 strömt im Betrieb der Strömungsmaschine 1 das jeweilige Arbeitsgas, beispielsweise ein Heißgas; eine entsprechende Gasströmung ist durch Pfeile 19 symbolisiert. Die Laufschaufeln 6 und die Leitschaufeln 9 erstrecken sich jeweils durch den Gaspfad 17. Im Kühlgaspfad 18 kann im Betrieb der Strömungsmaschine 1 eine Kühlgasströmung strömen, die durch Pfeile 20 angedeutet ist.The section plane selected in FIG. 1 lies in the circumferential direction between two adjacent rotor blades 6 and between two shield elements 12 adjacent in the circumferential direction. The sectional plane thus lies in a longitudinal gap, which forms in each case between two rotor blades 6 or protective shield elements 12 which are adjacent in the circumferential direction. In the region of this longitudinal gap, on the one hand, a blade radial seal 15 is formed on each side between two adjacent moving blades 6 of the same blade row 5, while on the other hand, a respective protective shield radial seal 16 is formed between two adjacent shielding elements 12. Both the respective blade radial seal 15 and the respective protective shield radial seal 16 separate in the radial direction a gas path 17, the turbomachine 1 from the rotor 2 and from a cooling gas path 18 which is formed radially between the rotor 2 and the respective radial seal 15, 16. In the gas path 17 flows during operation of the turbomachine 1, the respective working gas, such as a hot gas; a corresponding gas flow is symbolized by arrows 19. The blades 6 and the vanes 9 each extend through the gas path 17. In the cooling gas path 18 can flow during operation of the turbomachine 1, a cooling gas flow, which is indicated by arrows 20.
Die Schutzschildelemente 12 und die Laufschaufeln 6 der zum Rotorhitzeschutzschild 7 benachbarten Laufschaufelreihen 5 sind so aufeinander abgestimmt, dass die Schutzschildradialdichtung 16 ohne Unterbrechung sowohl in die stromauf liegende Schaufelradialdichtung 15 als auch in die stromab liegende Schaufelradialdichtung 15 übergeht. Dieser unterbrechungsfreie Übergang zwischen der Schutzschildradialdichtung 16 und den beiden Schaufelradialdichtungen 15 ist dabei so realisiert, dass sich dadurch eine Radialdichtung 21 ausbilden kann, die in der Längsrichtung von der einen Laufschaufel 6 über das jeweilige Schutzschildelement 12 bis zur anderen Laufschaufel 6 quasi nahtlos oder lückenlos durchgehend ausgestaltet ist. Beachtenswert ist dabei, dass sowohl bei einem stromauf liegenden Übergang 22 als auch bei einem stromab liegenden Übergang 23 zwischen dem Schutzschildelement 12 und der jeweiligen Laufschaufel 6 eine durchgehende Radialdichtung 21 realisiert werden kann.The shield elements 12 and the blades 6 of the rotor heat shield 7 adjacent blade rows 5 are so each other matched so that the shield radial seal 16 passes without interruption both in the upstream blade radial seal 15 and in the downstream blade radial seal 15. This uninterrupted transition between the shield radial seal 16 and the two blade radial seals 15 is realized so that it can form a radial seal 21, which in the longitudinal direction of the one blade 6 via the respective shield member 12 to the other blade 6 quasi seamless or continuous is designed. It is noteworthy that both in an upstream transition 22 and at a downstream transition 23 between the shield element 12 and the respective blade 6, a continuous radial seal 21 can be realized.
Die jeweilige Schaufelradialdichtung 15 umfasst im Bereich von Schaufelfüßen 24 der in Umfangsrichtung benachbarten Laufschaufeln 6 jeweils eine in Umfangsrichtung offene Schaufelnut 25. Die beiden Schaufelnuten 25 der jeweiligen Schaufelradialdichtung 15 liegen sich mit ihren offenen Seiten zueinander fluchtend gegenüber, so dass in diese Schaufelnuten 25 ein plattenförmiges oder bandförmiges Dichtelement 26 einlegbar ist. Die Schutzschildradialdichtung 16 ist in entsprechender weise aufgebaut und weist in Bereichen 27, die an die Rotordichtstruktur 13 angrenzen, bei den in Umfangsrichtung benachbarten Schutzschildelementen 12 jeweils eine in Umfangsrichtung offene Schutzschildnut 28 auf. Auch hier liegen sich die Schutzschildnuten 28 der beiden in Umfangsrichtung benachbarten Schutzschildelemente 12 in Umfangsrichtung zueinander fluchtend gegenüber, so dass in die Schutzschildnuten 28 ebenfalls ein plattenförmiges oder bandförmiges Dichtelement 26 einführbar ist. Die Schutzschildnuten 28 und die Schaufelnuten 25 sind zweckmäßig nun so aufeinander abgestimmt, dass in den Übergangsbereichen 22, 23 axiale Längsenden 29 der Schutzschildnuten 28 zu axial benachbarten axialen Längsenden 30 der Schaufelnuten 25 axial fluchten. Hierdurch ist es möglich, in den Übergangsbereichen 22, 23 ein gemeinsames Dichtelement 26 oder jeweils ein Dichtelement 26 anzuordnen, und zwar so, dass es sich von den Schutzschildnuten 28 axial bis in die Schaufelnuten 25 hinein erstreckt oder dass es sich von den Schaufelnuten 25 der Laufschaufeln 6 der einen Laufschaufelreihe 5 axial bis in die Schutzschildnuten 28 hinein erstreckt.The respective blade radial seal 15 comprises in the region of blade roots 24 of the circumferentially adjacent blades 6 each a circumferentially open blade groove 25. The two blade grooves 25 of the respective blade radial seal 15 are aligned with their open sides facing each other, so that in these blade grooves 25 a plate-shaped or band-shaped sealing element 26 can be inserted. The shield radial seal 16 is constructed in a corresponding manner and has in regions 27 which adjoin the rotor seal structure 13, in the circumferentially adjacent shield elements 12 in each case one in the circumferential direction open Schutzschildnut 28. Here, too, the protective shield grooves 28 of the two shielding elements 12 adjacent to one another in the circumferential direction are aligned with one another in the circumferential direction, so that a plate-shaped or band-shaped sealing element 26 can likewise be inserted into the protective shield grooves 28. The shield grooves 28 and the blade grooves 25 are suitably matched to one another so that in the transition regions 22, 23 axial longitudinal ends 29 of the shield grooves 28 axially aligned axially adjacent axial longitudinal ends 30 of the blade grooves 25. This makes it possible to arrange in the transition regions 22, 23 a common sealing element 26 or in each case a sealing element 26, specifically in such a way that it extends axially from the protective shield grooves 28 into the blade grooves 25 or that it extends from the blade grooves 25 Blades 6 of a blade row 5 extends axially into the shield grooves 28 inside.
Dabei ist es grundsätzlich möglich, ein durchgehendes, relativ langes Dichtelement 26 zu verwenden, das sich in den jeweiligen Nuten 25, 28 von der einen Laufschaufelreihe 5 über das Rotorhitzeschutzschild 7 bis in die andere Laufschaufel reihe 5 erstreckt. Bevorzugt können jedoch mehrere Dichtelemente 26 vorgesehen sein, wobei insbesondere benachbarte Dichtelemente 26 zwischen den axialen Längsenden 29 der Schutzschildnuten 28 und/oder zwischen den axialen Längsenden 30 der jeweiligen Schaufelnuten 25 axial aneinander stoßen. Ebenso ist es grundsätzlich möglich, vergleichsweise kleine Dichtelemente 26 vorzusehen, die nur im jeweiligen Übergangsbereich 22 bzw. 23 zur Überbrückung des dortigen ringförmigen Axialspalts angeordnet sind und sich dabei einerseits bis in die Schutzschildnuten 28 und andererseits bis in die Schaufelnuten 25 erstrecken.It is in principle possible to use a continuous, relatively long sealing element 26 which extends in the respective grooves 25, 28 from the one blade row 5 on the rotor heat shield 7 to the other blade row 5. Preferably, however, a plurality of sealing elements 26 may be provided, in particular adjacent sealing elements 26 axially abutting one another between the axial longitudinal ends 29 of the protective shield grooves 28 and / or between the axial longitudinal ends 30 of the respective blade grooves 25. Likewise, it is basically possible to provide comparatively small sealing elements 26, which are arranged only in the respective transitional region 22 or 23 for bridging the annular axial gap there, extending on the one hand into the protective shield grooves 28 and on the other hand into the blade grooves 25.
Die Schutzschildelemente 12 können entsprechend der hier gezeigten Ausführungsform zwischen ihren axialen Enden, also zwischen den Übergangsbereichen 22, 23 eine radial nach innen zurückspringende Vertiefung 31 aufweisen. In dieser Vertiefung 31 ist die Rotordichtstruktur 13 angeordnet. Ferner sind die Leitschaufeln 9 hier so dimensioniert, dass auch die Statordichtstruktur 10 innerhalb dieser Vertiefung 31 angeordnet ist. Gemäß der hier gezeigten bevorzugten Ausführungsform kann die Vertiefung 31 so dimensioniert sein, dass die durch das Zusammenspiel der Rotordichtstruktur 13 mit der Statordichtstruktur 10 gebildete Axialdichtung 14 innerhalb der Vertiefung 31 ausgebildet ist. Die Axialdichtung 14 ist dabei relativ zu den Schaufelradialdichtungen 15 der benachbarten Laufschaufeln 6 radial nach innen versetzt angeordnet. Hierdurch befindet sich die Axialdichtung 14 radial außerhalb der Gasströmung 19 im Gaspfad 17 und insbesondere in einem Totwassergebiet der Gasströmung 19.The shield elements 12 may according to the embodiment shown here between their axial ends, ie between the transition regions 22, 23 have a radially inwardly recessed recess 31. In this recess 31, the rotor seal structure 13 is arranged. Furthermore, the guide vanes 9 are here dimensioned so that the stator seal structure 10 is disposed within this recess 31. According to the Here shown preferred embodiment, the recess 31 may be dimensioned so that the formed by the interaction of the rotor seal structure 13 with the stator seal structure 10 axial seal 14 is formed within the recess 31. The axial seal 14 is arranged offset radially inwardly relative to the blade radial seals 15 of the adjacent blades 6. As a result, the axial seal 14 is located radially outside the gas flow 19 in the gas path 17 and in particular in a dead water region of the gas flow 19.
Gemäß einer vorteilhaften Ausführungsform kann die Statordichtstruktur 10 einschleifbar ausgestaltet sein. Beispielsweise kann die Statordichtstruktur 10 hierzu als Wabenstruktur 33 mit radial orientierten Waben ausgebildet sein. Vorzugsweise ist dann die Rotordichtstruktur 13 einschleifend ausgestaltet. Beispielsweise ist die Rotordichtstruktur 13 durch wenigstens einen klingenförmigen Ringsteg 32 gebildet. Im gezeigten Beispiel sind zwei derartige Ringstege 32 vorgesehen, die in axialer Richtung voneinander beabstandet angeordnet sind. Im Betrieb der Strömungsmaschine 1 kann sich die Rotordichtstruktur 13 in die Statordichtstruktur 10 einschleifen, das heißt, der jeweilige Ringsteg 32 dringt in die Wabenstruktur 33 ein.According to an advantageous embodiment, the stator seal structure 10 may be configured so as to be grindable. For example, the stator-seal structure 10 may be designed as a honeycomb structure 33 with radially oriented honeycombs for this purpose. Preferably, then the rotor seal structure 13 is designed einschleifend. For example, the rotor-seal structure 13 is formed by at least one blade-shaped annular web 32. In the example shown, two such annular webs 32 are provided, which are arranged spaced apart in the axial direction. During operation of the turbomachine 1, the rotor-seal structure 13 can be looped into the stator-seal structure 10, that is to say the respective annular web 32 penetrates into the honeycomb structure 33.
Zweckmäßig wirken die Statordichtstruktur 10 und die Rotordichtstruktur 13 zur Ausbildung der Axialdichtung 14 nach Art einer Labyrinthdichtung zusammen. Insbesondere kann hierzu die Statordichtstruktur 10 mehrere, z. B. zwei, ringförmige Axialabschnitte 34 aufweisen, die gegenüber einem dazu benachbarten, hier mittleren ringförmigen Axialabschnitt 35 radial nach außen versetzt sind. Die Rotordichtstruktur 13 weist dann mehrere, hier zwei radial nach außen vorstehende Ringstege 32 auf, die jeweils im Bereich eines der radial nach außen versetzten Radialabschnitte 34 angeordnet sind. Suitably, the stator seal structure 10 and the rotor seal structure 13 cooperate to form the axial seal 14 in the manner of a labyrinth seal. In particular, for this purpose, the stator seal structure 10 more, z. B. have two annular axial sections 34 which are offset from an adjacent thereto, here middle annular axial section 35 radially outward. The rotor-seal structure 13 then has several, here two radially outwardly projecting annular webs 32, which are each arranged in the region of one of the radially outwardly offset radial sections 34.
BezugszeichenlisteLIST OF REFERENCE NUMBERS
Strömungsmaschineflow machine
Rotorrotor
Statorstator
Rotorachserotor axis
LaufschaufelreiheBlade row
Laufschaufelblade
Rotorh itzesch utzsch ildRotor protection plate
Leitschaufelreihevane row
Leitschaufelvane
Statordichtstrukturstator sealing
Leitschaufelplattformvane platform
SchutzschildelementShield element
RotordichtstrukturRotor sealing structure
Axialdichtungaxial seal
SchaufelradialdichtungScoop radial seal
SchutzschildradialdichtungShield radial seal
Gaspfadgas path
KühlgaspfadCooling gas path
Pfeilarrow
Pfeilarrow
Radialdichtungradial seal
ÜbergangsbereichTransition area
Übergangsbereich SchaufelfußTransition area blade
Schaufelnutblade groove
Dichtelementsealing element
BereichArea
SchutzschildnutSchutzschildnut
Längsende von 28Longitudinal end of 28
Längsende von 25Longitudinal of 25
Vertiefungdeepening
Ringstegring land
Wabenstrukturhoneycomb structure
Axialabschnittaxial
Axialabschnitt axial

Claims

Patentansprüche claims
1. Rotierende Strömungsmaschine, insbesondere Gasturbine,1. Rotary turbomachine, in particular gas turbine,
- mit einem Rotor (2), der wenigstens zwei Laufschaufelreihen (5) mit mehreren Laufschaufeln (6) sowie wenigstens ein Rotorhitzeschutzschild (7) mit mehreren Schutzschildelementen (12) aufweist, das axial zwischen zwei benachbarten Laufschaufelreihen (5) angeordnet ist,- having a rotor (2) having at least two blade rows (5) with a plurality of blades (6) and at least one rotor heat shield (7) with a plurality of shield elements (12), which is arranged axially between two adjacent blade rows (5),
- mit einem Stator (3), der wenigstens eine axial zwischen zwei benachbarten Laufschaufelreihen (5) angeordnete Leitschaufelreihe (8) mit mehreren Leitschaufeln (9) aufweist,- having a stator (3) which has at least one guide vane row (8) with a plurality of guide vanes (9) arranged axially between two adjacent rotor blade rows (5),
- wobei die Leitschaufeln (9) der Leitschaufelreihe (8) radial innen eine in Umfangsrichtung geschlossene Statordichtstruktur (10) aufweisen,- wherein the guide vanes (9) of the guide blade row (8) have radially inwardly a circumferentially closed stator seal structure (10),
- wobei die Schutzschildelemente (12) radial außen eine in Umfangsrichtung geschlossene Rotordichtstruktur (13) aufweisen, die mit der Statordichtstruktur (10) zur Ausbildung einer Axialdichtung (14) zusammenwirkt,- wherein the protective shield elements (12) radially outwardly a circumferentially closed rotor seal structure (13) which cooperates with the stator seal structure (10) for forming an axial seal (14),
- wobei in Umfangsrichtung zwischen zwei benachbarten Laufschaufeln (6) eine Schaufelradialdichtung (15) ausgebildet ist, die einen Gaspfad (17), durch den sich die Laufschaufeln (6) und die Leitschaufeln (9) erstrecken, vom Rotor (2) trennt,in the circumferential direction between two adjacent moving blades (6) a blade radial seal (15) is formed which separates a gas path (17) through which the moving blades (6) and the guide vanes (9) extend from the rotor (2),
- wobei in Umfangsrichtung zwischen zwei benachbarten Schutzschildelementen (12) eine Schutzschildradialdichtung (16) ausgebildet ist, die den Gaspfad (17) vom Rotor (2) trennt,- Wherein a protective shield radial seal (16) is formed in the circumferential direction between two adjacent shield elements (12), which separates the gas path (17) from the rotor (2),
- wobei die Schutzschildelemente (12) und die Laufschaufeln (6) so aufeinander abgestimmt sind, dass die Schutzschildradialdichtung (16) unterbrechungsfrei in die Schaufelradialdichtungen (15) der beiden axial benachbarten Laufschaufeln (6) übergeht, derart, dass von der einen Laufschaufel (6) über das Schutzschildelement (12) zur anderen Laufschaufel (6) eine durchgehende Radialdichtung (21) ausgebildet ist.- Wherein the shield elements (12) and the blades (6) are coordinated so that the protective shield radial seal (16) without interruption in the Schaufelradialdichtungen (15) of the two axially adjacent Blades (6) merges, such that from one blade (6) via the shield member (12) to the other blade (6) a continuous radial seal (21) is formed.
2. Strömungsmaschine nach Anspruch 1, dadurch gekennzeichnet,2. Turbomachine according to claim 1, characterized
- dass die Schaufelradialdichtung (15) im Bereich von Schaufelfüßen (24) der in Umfangsrichtung benachbarten Laufschaufeln (6) ausgebildete, in Umfangsrichtung offene Schaufelnuten (25) aufweist, in die ein platten- oder bandförmiges Dichtelement (26) eingebracht ist,- that the blade radial seal (15) in the region of blade roots (24) of the circumferentially adjacent blades (6) formed in the circumferential direction open blade grooves (25) into which a plate or band-shaped sealing element (26) is introduced
- dass die Schutzschildradialdichtung (16) in an die Rotordichtstruktur (13) angrenzenden Bereichen (27) der in Umfangsrichtung benachbarten Schutzschildelemente (12) ausgebildete, in Umfangsrichtung offene Schutzschildnuten (28) aufweist, in die ein platten- oder bandförmiges Dichtelement (26) eingebracht ist,- That the Schutzschildradialdichtung (16) in the rotor seal structure (13) adjacent regions (27) of the circumferentially adjacent shield elements (12) formed in the circumferential direction open protective shield grooves (28), in which a plate or band-shaped sealing element (26) introduced is
- dass axiale Längsenden (29) der Schutzschildnuten (28) zu axial benachbarten axialen Längsenden (30) der Schaufelnuten (25) axial fluchten,axial axial ends (29) of the protective shield grooves (28) are axially aligned axially with axially adjacent axial longitudinal ends (30) of the blade grooves (25),
- dass zumindest ein solches Dichtelement (26) vorgesehen ist, das sich von den Schutzschildnuten (28) axial bis in die Schaufelnuten (25) zumindest einer der benachbarten Laufschaufeln (6) erstreckt oder dass sich von den Schaufelnuten (25) der Laufschaufeln (6) der einen Laufschaufel reihe (5) axial bis in die Schutzschildnuten (28) erstreckt.in that at least one such sealing element (26) is provided which extends axially from the protective shield grooves (28) into the blade grooves (25) of at least one of the adjacent moving blades (6) or in that the blades (25) of the moving blades (6 ) of a blade row (5) extends axially into the shield grooves (28).
3. Strömungsmaschine nach Anspruch 2, dadurch gekennzeichnet, dass benachbarte Dichtelemente (26) zwischen den axialen Längsenden (30) der Schaufelnuten (25) und/oder zwischen den axialen Längsenden (29) der Schutzschildnuten (28) axial aneinanderstoßen. 3. Turbomachine according to claim 2, characterized in that adjacent sealing elements (26) axially abut one another between the axial longitudinal ends (30) of the blade grooves (25) and / or between the axial longitudinal ends (29) of the protective shield grooves (28).
4. Strömungsmaschine nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Schutzschildelemente (12) zwischen ihren axialen Enden eine radial nach innen zurückspringende Vertiefung (31) aufweisen, in der die Rotordichtstruktur (13) angeordnet ist.4. Turbomachine according to one of claims 1 to 3, characterized in that the protective shield elements (12) between their axial ends have a radially inwardly recessed recess (31) in which the rotor seal structure (13) is arranged.
5. Strömungsmaschine nach Anspruch 4, dadurch gekennzeichnet, dass die Leitschaufeln (9) so dimensioniert sind, dass die Statordichtstruktur (10) innerhalb der Vertiefung (31) angeordnet ist.5. Turbomachine according to claim 4, characterized in that the guide vanes (9) are dimensioned so that the stator seal structure (10) within the recess (31) is arranged.
6. Strömungsmaschine nach Anspruch 4 oder 5, dadurch gekennzeichnet, dass die Vertiefung (31 ) so dimensioniert ist, dass die Axialdichtung (14) innerhalb der Vertiefung (31) ausgebildet ist und relativ zu den Schaufelradialdichtungen (15) der benachbarten Laufschaufeln (6) radial nach innen versetzt angeordnet ist.6. Turbomachine according to claim 4 or 5, characterized in that the recess (31) is dimensioned so that the axial seal (14) within the recess (31) is formed and relative to the Schaufelradialdichtungen (15) of the adjacent blades (6). is arranged offset radially inward.
7. Strömungsmaschine nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet,7. Turbomachine according to one of claims 1 to 6, characterized
- dass die Statordichtstruktur (10) einschleifbar ausgestaltet ist, z. B. als Wabenstruktur (33) mit radial orientierten Waben,- That the stator seal structure (10) is configured einschleifbar, z. B. as a honeycomb structure (33) with radially oriented honeycomb,
- dass die Rotordichtstruktur (13) einschleifend ausgestaltet ist, z.B. als wenigstens ein klingenförmiger Ringsteg (32),- That the rotor seal structure (13) is designed einschleifend, e.g. as at least one blade-shaped annular web (32),
- dass sich die Rotordichtstruktur (13) im Betrieb der Strömungsmaschine (1 ) in die Statordichtstruktur (10) einschleift.- That the rotor seal structure (13) einschleift in operation of the turbomachine (1) in the stator seal structure (10).
8. Strömungsmaschine nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass die Statordichtstruktur (10) und die Rotordichtstruktur (13) zur Ausbildung der Axialdichtung (14) nach Art einer Labyrinthdichtung zusammenwirken.8. Turbomachine according to one of claims 1 to 7, characterized in that the stator-seal structure (10) and the rotor-seal structure (13) cooperate in the manner of a labyrinth seal to form the axial seal (14).
9. Strömungsmaschine nach Anspruch 7 oder 8, dadurch gekennzeichnet,9. Turbomachine according to claim 7 or 8, characterized
- dass die Statordichtstruktur (10) mehrere ringförmige Axialabschnitte (34) aufweist, die gegenüber einem dazu benachbarten ringförmigen Axialabschnitt (35) radial nach außen versetzt sind,the stator-seal structure (10) has a plurality of annular axial sections (34) which are offset radially outward from an annular axial section (35) adjacent thereto,
- dass die Rotordichtstruktur (13) mehrere radial nach außen vorstehende Ringstege (32) aufweist, die jeweils im Bereich eines der radial nach außen versetzten Axialabschnitte (34) angeordnet sind.- That the rotor seal structure (13) has a plurality of radially outwardly projecting annular webs (32) which are each arranged in the region of one of the radially outwardly offset axial sections (34).
10. Strömungsmaschine nach einem der Ansprüche 1 bis 9, dadurch gekennzeichnet, dass radial zwischen der Radialdichtung (21) und dem Rotor (2) ein Kühlgaspfad (18) verläuft. 10. Turbomachine according to one of claims 1 to 9, characterized in that radially between the radial seal (21) and the rotor (2) extends a cooling gas path (18).
EP07847789A 2006-12-19 2007-12-04 Turbomachine, particularly a gas turbine Not-in-force EP2092164B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH20582006 2006-12-19
PCT/EP2007/063288 WO2008074633A1 (en) 2006-12-19 2007-12-04 Turbomachine, particularly a gas turbine

Publications (2)

Publication Number Publication Date
EP2092164A1 true EP2092164A1 (en) 2009-08-26
EP2092164B1 EP2092164B1 (en) 2010-10-06

Family

ID=37616891

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07847789A Not-in-force EP2092164B1 (en) 2006-12-19 2007-12-04 Turbomachine, particularly a gas turbine

Country Status (9)

Country Link
US (1) US8052382B2 (en)
EP (1) EP2092164B1 (en)
JP (1) JP5027245B2 (en)
KR (1) KR101426715B1 (en)
AT (1) ATE483891T1 (en)
CA (1) CA2673079C (en)
DE (1) DE502007005296D1 (en)
MX (1) MX2009006599A (en)
WO (1) WO2008074633A1 (en)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2673079C (en) 2006-12-19 2015-11-24 Alstom Technology Ltd. Turbomachine, especially gas turbine
RU2539404C2 (en) * 2010-11-29 2015-01-20 Альстом Текнолоджи Лтд Axial gas turbine
US9341070B2 (en) * 2012-05-30 2016-05-17 United Technologies Corporation Shield slot on side of load slot in gas turbine engine rotor
US9771818B2 (en) 2012-12-29 2017-09-26 United Technologies Corporation Seals for a circumferential stop ring in a turbine exhaust case
WO2014189564A2 (en) * 2013-03-06 2014-11-27 United Technologies Corporation Pretrenched rotor for gas turbine engine
US9441639B2 (en) 2013-05-13 2016-09-13 General Electric Company Compressor rotor heat shield
EP2832952A1 (en) * 2013-07-31 2015-02-04 ALSTOM Technology Ltd Turbine blade and turbine with improved sealing
KR101584156B1 (en) * 2014-12-22 2016-01-22 주식회사 포스코 Seal for gas turbine and seal assembly having the same

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3551068A (en) 1968-10-25 1970-12-29 Westinghouse Electric Corp Rotor structure for an axial flow machine
CH525419A (en) 1970-12-18 1972-07-15 Bbc Sulzer Turbomaschinen Sealing device for turbo machines
US5293717A (en) * 1992-07-28 1994-03-15 United Technologies Corporation Method for removal of abradable material from gas turbine engine airseals
GB2307279B (en) * 1995-11-14 1999-11-17 Rolls Royce Plc A gas turbine engine
DE19654471B4 (en) * 1996-12-27 2006-05-24 Alstom Rotor of a turbomachine
DE19914227B4 (en) * 1999-03-29 2007-05-10 Alstom Heat protection device in gas turbines
JP3481596B2 (en) * 2001-02-14 2003-12-22 株式会社日立製作所 gas turbine
EP1371814A1 (en) 2002-06-11 2003-12-17 ALSTOM (Switzerland) Ltd Sealing arrangement for a rotor of a turbomachine
RU2297566C2 (en) * 2002-07-03 2007-04-20 Альстом Текнолоджи Лтд Slot seal
CA2673079C (en) 2006-12-19 2015-11-24 Alstom Technology Ltd. Turbomachine, especially gas turbine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2008074633A1 *

Also Published As

Publication number Publication date
CA2673079A1 (en) 2008-06-26
ATE483891T1 (en) 2010-10-15
US20090274552A1 (en) 2009-11-05
JP5027245B2 (en) 2012-09-19
EP2092164B1 (en) 2010-10-06
WO2008074633A1 (en) 2008-06-26
US8052382B2 (en) 2011-11-08
MX2009006599A (en) 2009-07-02
KR20090091190A (en) 2009-08-26
CA2673079C (en) 2015-11-24
JP2010513783A (en) 2010-04-30
KR101426715B1 (en) 2014-08-06
DE502007005296D1 (en) 2010-11-18

Similar Documents

Publication Publication Date Title
EP2092164B1 (en) Turbomachine, particularly a gas turbine
DE2717810C2 (en) Gas turbine rotor with ceramic blades
DE69912539T2 (en) Cooling a turbine jacket ring
DE60024701T2 (en) Sealing arrangement and equipped with such a seal assembly, rotating machine
DE3544652C2 (en) poetry
DE102004024683B4 (en) Sealing system for horizontal joints of intermediate floors of steam turbines
EP2179143B1 (en) Gap cooling between combustion chamber wall and turbine wall of a gas turbine installation
DE102014115264A1 (en) Microchannel outlet for cooling and / or flushing gas turbine segment gaps
DE10047307A1 (en) sealing arrangement
EP2132414B1 (en) Shiplap arrangement
DE60113796T2 (en) Stator vane structure of a gas turbine
EP1180196A1 (en) Turbo-machine comprising a sealing system for a rotor
DE102014117262A1 (en) L-brush seal for turbomachinery applications
DE2241194B2 (en) Turbomachine blade with internal cooling channels
CH698121B1 (en) Grouped reaction nozzle shrouds with integrated seals.
CH702000A2 (en) Swirl chambers to the gap flow control.
WO2000070191A1 (en) Sealing system for a rotor of a turbo engine
DE10350209A1 (en) Hybrid honeycomb and brush seal for a steam gland
DE102015122928A1 (en) Gas turbine seal
DE1930411A1 (en) Rotary seal
DE102004026503A1 (en) Intermediate nozzle seal for steam turbines
CH708764A2 (en) Interlocking spacer assembly for insertion into a peripheral attachment slot between platforms of adjacent blades.
EP3324002A1 (en) Axial turbomachine and sealing system for an axial turbomachine
EP1995413B1 (en) Gap seal for airfoils of a turbomachine
DE602004001306T2 (en) External air sealing arrangement

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: 20090610

AK Designated contracting states

Kind code of ref document: A1

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

DAX Request for extension of the european patent (deleted)
GRAJ Information related to disapproval of communication of intention to grant by the applicant or resumption of examination proceedings by the epo deleted

Free format text: ORIGINAL CODE: EPIDOSDIGR1

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

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

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REF Corresponds to:

Ref document number: 502007005296

Country of ref document: DE

Date of ref document: 20101118

Kind code of ref document: P

REG Reference to a national code

Ref country code: NL

Ref legal event code: T3

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: 20101006

LTIE Lt: invalidation of european patent or patent extension

Effective date: 20101006

REG Reference to a national code

Ref country code: IE

Ref legal event code: FD4D

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

Ref country code: 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: 20101006

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: 20101006

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: 20101006

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: 20110106

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: 20110206

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: 20110207

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: 20101006

BERE Be: lapsed

Owner name: ALSTOM TECHNOLOGY LTD

Effective date: 20101231

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: 20110107

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

Ref country code: CZ

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

Effective date: 20101006

Ref country code: IE

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

Effective date: 20101006

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: 20110117

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: 20101006

Ref country code: MC

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

Effective date: 20101231

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: 20101006

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: 20101006

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: 20101006

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: 20101006

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20110831

26N No opposition filed

Effective date: 20110707

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: 20101231

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

Ref country code: FR

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

Effective date: 20110103

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502007005296

Country of ref document: DE

Effective date: 20110707

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: 20101006

Ref country code: IT

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

Effective date: 20101204

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: 20101006

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: 20101204

Ref country code: HU

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

Effective date: 20110407

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: 20101006

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 483891

Country of ref document: AT

Kind code of ref document: T

Effective date: 20121204

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: 20121204

REG Reference to a national code

Ref country code: CH

Ref legal event code: PFA

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD, CH

REG Reference to a national code

Ref country code: NL

Ref legal event code: HC

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH; CH

Free format text: DETAILS ASSIGNMENT: VERANDERING VAN EIGENAAR(S), VERANDERING VAN NAAM VAN DE EIGENAAR(S); FORMER OWNER NAME: ALSTOM TECHNOLOGY LTD

Effective date: 20160623

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 502007005296

Country of ref document: DE

Representative=s name: RUEGER | ABEL PATENT- UND RECHTSANWAELTE, DE

Ref country code: DE

Ref legal event code: R082

Ref document number: 502007005296

Country of ref document: DE

Representative=s name: RUEGER ABEL PATENTANWAELTE PARTGMBB, DE

Ref country code: DE

Ref legal event code: R082

Ref document number: 502007005296

Country of ref document: DE

Representative=s name: RUEGER, BARTHELT & ABEL, DE

Ref country code: DE

Ref legal event code: R081

Ref document number: 502007005296

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: R082

Ref document number: 502007005296

Country of ref document: DE

Representative=s name: RUEGER ABEL PATENT- UND RECHTSANWAELTE, DE

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

Ref country code: CH

Payment date: 20161227

Year of fee payment: 10

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

Ref country code: NL

Payment date: 20171226

Year of fee payment: 11

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

Ref country code: GB

Payment date: 20171227

Year of fee payment: 11

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

Ref country code: DE

Payment date: 20171229

Year of fee payment: 11

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

Ref country code: IT

Payment date: 20171221

Year of fee payment: 11

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: CH

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

Effective date: 20171231

Ref country code: LI

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

Effective date: 20171231

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502007005296

Country of ref document: DE

REG Reference to a national code

Ref country code: NL

Ref legal event code: MM

Effective date: 20190101

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

Effective date: 20181204

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 NON-PAYMENT OF DUE FEES

Effective date: 20190101

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

Ref country code: DE

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

Effective date: 20190702

Ref country code: IT

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

Effective date: 20181204

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: 20181204