EP3087254B1 - Component that can be charged with hot gas for a gas turbine and sealing assembly with such a component - Google Patents

Component that can be charged with hot gas for a gas turbine and sealing assembly with such a component Download PDF

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Publication number
EP3087254B1
EP3087254B1 EP15705578.1A EP15705578A EP3087254B1 EP 3087254 B1 EP3087254 B1 EP 3087254B1 EP 15705578 A EP15705578 A EP 15705578A EP 3087254 B1 EP3087254 B1 EP 3087254B1
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EP
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Prior art keywords
groove
recesses
gas
edge
component
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EP15705578.1A
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German (de)
French (fr)
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EP3087254A1 (en
Inventor
Fathi Ahmad
Ralf Müsgen
Radan RADULOVIC
Marco Schüler
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Siemens AG
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Siemens AG
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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
    • F01D3/00—Machines or engines with axial-thrust balancing effected by working-fluid
    • F01D3/02—Machines or engines with axial-thrust balancing effected by working-fluid characterised by having one fluid flow in one axial direction and another fluid flow in the opposite direction
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/02—Arrangement of sensing elements
    • F01D17/08—Arrangement of sensing elements responsive to condition of working-fluid, e.g. pressure
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines

Definitions

  • Such components are known for forming a seal assembly of the prior art.
  • the GB 2 195 403 A two such components whose second surfaces face each other gap-forming, wherein the then equally opposed grooves receive a sealing element which blocks the gap as far as possible against a flow.
  • sealing grooves can be supplied with cooling air by separate cooling air feeds opening into them.
  • the object of the invention is therefore to provide a hot gas acted upon component whose edges are less prone to wear.
  • Another object of the invention is to provide a durable, relatively oxidation-resistant and inexpensive seal assembly comprising two components which are each arranged so that their second side surfaces are gap-forming face each other and in their opposite grooves, a sealing element is used to seal the gap.
  • the groove-shaped recesses in a side wall or in both side walls serve as flow passages for cooling air and are preferably located where the edges of the components are exposed to higher wear and oxidation.
  • locally targeted blowing out of the amount of cooling air predeterminable by the dimensions of the depressions reduces the thermal load and improves the resistance of the claimed area.
  • the amount of component material to be cooled is reduced by the depressions in the side walls of the groove, why the groove-shaped depressions in the side walls represent a technically more sensible solution than the sealing elements of the GB 2 195 403 A , in turn, in places slits for the passage of cooling air exhibit.
  • the sealing elements are more durable than sealing elements with slots.
  • the sealing arrangement according to the invention achieves at least one of the components, preferably both components designed according to the invention and arranged relative to one another such that their second surfaces lie opposite one another in a gap-forming manner and a sealing element is used to seal the gap in their opposing grooves, an overall longer one Lifespan.
  • the sealing element is designed plate-shaped. That is, it is free of slits, depressions or tapers, which are intended for the targeted passage of cooling air.
  • the groove-shaped depressions of the side walls extend from the slot opening of the groove receiving the sealing element to the groove bottom of the groove receiving the sealing element.
  • each side wall has a plurality of groups with groove-shaped depressions in at least one longitudinal section of the groove receiving the sealing elements.
  • both cold gas side and hot gas side groove-shaped recesses are provided on the side walls of the groove, through which the coolant flowing through it can be selectively directed to those positions which are particularly highly thermally and / or corrosively loaded.
  • Such an arrangement can be produced in a particularly simple manner, for example by erosion, wherein the longer depressions are preferably arranged on the cold gas side. The more closely positioned depressions are then arranged on the hot gas side, which allows a better and more uniform cooling air distribution.
  • the groove has an area which is free of depressions and whose longitudinal extent is greater than the longitudinal extent of a single group.
  • each of the mutually opposing grooves in each case at least one group of recesses is provided in each of the mutually opposing grooves, which are offset at least partially along the groove extension with respect to each other.
  • the component according to the invention can be designed, for example, as turbine guide vanes, as a turbine blade or as a ring segment.
  • further fields of application within the gas turbine are also conceivable, for example in the transition from a combustion chamber to an annular channel in which the blades of the turbine are arranged.
  • the invention thus relates to a component for a gas turbine which can be charged with hot gas, with at least one wall having a first surface up to an edge, wherein the first surface is intended to delimit a hot gas flow path of the gas turbine, and the one adjacent to the edge, Arranged transversely to the first surface disposed second surface, wherein in the second surface provided for receiving a sealing member groove is arranged, which extends at a distance from the edge at least partially along the edge, and wherein the groove opposite the groove opening groove bottom and two adjacent thereto , side walls extending towards each other and extending along the edge, of which one of the two is located on the hot gas side and the other on the cold gas side and in each case have depressions.
  • the recesses are summarized in a group whose recesses are arranged such that two of these recesses of said group are arranged in the hot gas side wall and so spaced apart from each other, the one in the Cold gas side wall arranged recess of said group is partially opposite each of the two hot gas side wells.
  • FIG. 1 shows a side view of a turbine vane 11 as a component 10 of a stationary gas turbine.
  • the turbine guide vane 11 comprises a foot-side end 12 and a not further illustrated head-side end, between which an aerodynamically curved airfoil 16 extends.
  • the blade 16 itself extends in Spannweite politicians from its foot-side end 13 to its head end. Transversely thereto, the airfoil 16 extends from a leading edge 18 to a trailing edge 20.
  • a platform 22 is provided which define a flow path 24 for hot gas therebetween.
  • each platform 22 has a surface 26 facing the hot gas flow path 24.
  • the surface 26, hereinafter referred to as the first surface 26 ends laterally at an edge 28.
  • This edge 28 may - as shown - be designed as an edge.
  • a second surface 30 connects, which is oriented transversely to the first surface 26. If the edge 28 is designed not as an edge, but as a radius, go the first and the second surface 26, 30 into each other.
  • a plurality of turbine vanes 11 arranged in a ring form a row of vanes, in which case the second surfaces 30 of directly adjacent turbine blades 11 are each gap-forming (FIG. FIG. 2 ). For such arrangements, only those edges 28 of the platforms that bound the first surface 26 in the circumferential direction are then relevant.
  • each groove 34 has two side walls 36.
  • Each groove 34 extends along the edge 28, but at a slight distance thereto.
  • groove-shaped recesses 38 are provided in each side wall 36 in each side wall 36 in each side wall 36 in each side wall 36 in each side wall 36 in each side wall 36 in each side wall 36 in each side wall 36 in each side wall 36 in each side wall 36 in each side wall 36 in each side wall 36 in each side wall 36 in each side wall 36 in each side wall 36 in each side wall 36 in each side wall 36 groove-shaped recesses 38 are provided.
  • Each side wall 36 of the groove 34 has along its longitudinal extent from the upstream side End (18) to the downstream end (20) a plurality of successive recesses 38.
  • elevations and depressions 38 alternate in the side wall 36a and in the side wall 36b.
  • the recesses 38 and the protrusions remaining between two recesses 38 are arranged with a small offset, so that both depressions 38 and elevations to groups 39 can be logically combined, as represented by the dashed circles.
  • the depressions 38 on the side walls 36 of the groove 34 are distributed along the two side walls 36 such that the steps between recesses 36 and elevations of one side wall 36a (36b) are offset from the steps of the other side wall 36b (36a).
  • the hot gas side recesses 38a are only half as long as the cold gas side recesses 38b.
  • cooling air flows into the cold gas side recesses 38b, so that each cold gas side recess 38b can supply two hot gas side recesses 38a with cooling air while flowing around the sealing element 44.
  • a group 39 can be defined thereby.
  • groove 34 may also be used with ring segments circumferentially forming a circle defining an axial portion of the gas turbine flow path 24 radially outward of the tips of blades.
  • groove 34 there are longer groove portions 43, which are free of recesses 38.
  • Such grooves 34 offer themselves where only at certain positions of the edge or the first surface 26 increased signs of wear occur.
  • FIG. 1 shows part of a groove 41 associated with the component (not shown) which is opposite to the platform 22 of the illustrated turbine vane 11 gap forming.
  • the representation of the groove 41 is mirrored with respect to the groove 34, so that the hot gas side recesses 38a of the groove 41 in FIG. 1 are shown above the cold gas side recesses 38b.
  • the two groups 39 and 42 of recesses 38 of the two opposing components offset by a distance A to each other. This allows an arrangement of hot gas-side depressions 38a that is virtually continuous along the gap, so that particularly good cooling with a defined amount of cooling air is possible in this region.
  • FIG. 2 shows in cross section the seal assembly 40 comprising two components 10, each having a first surface 26, which is intended to define a flow path 24 of the gas turbine, wherein the first surfaces 26 pass over edges 28 in a second surface 30, which second surfaces 30 across are arranged to the first surfaces 26.
  • first surfaces 26 pass over edges 28 in a second surface 30, which second surfaces 30 across are arranged to the first surfaces 26.
  • second surface 30 along the edge 28 and spaced therefrom parallel grooves 34 are arranged, which may have on its side walls 36 along the longitudinal extension of the groove 34 one or more recesses 38.
  • the recesses 38 extend from a groove opening 42, which lies in the second surface 30, to a groove bottom 46, which lies opposite said groove opening 42.
  • the recesses 38 allow for the targeted and metered flow of cooling air from a cold gas side 48 that lies beyond the platforms 22 to a hot gas side that lies on either side of the platforms 22 and that define the flow path 24 of the gas turbine.
  • sealing elements 44 are used in the grooves 36 . These are along their longitudinal extent - ie parallel to the edge 28 - designed flat and thus have the same material thickness in this direction over its entire longitudinal extent. That is, the sealing elements 44 are free of slots or recesses with which cooling air can be selectively guided from the cold gas side 48 to the hot gas side. However, at one or both surfaces of the sealing element 44, which face the side walls 36, sealing tips may be arranged, which in principle prevent the occurrence of a cooling air flow in those portions of the groove 34, which are not deepened.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)

Description

Die Erfindung betrifft ein heißgasbeaufschlagbares Bauteil für eine Gasturbine, mit zumindest einer Wand,

  • die eine erste Oberfläche bis zu einem Rand umfasst, wobei die erste Oberfläche zur Begrenzung eines Heißgas-Strömungspfads der Gasturbine bestimmt ist, und
  • die eine an den Rand angrenzende, quer zur ersten Oberfläche angeordnete zweite Oberfläche umfasst,
wobei in der zweiten Oberfläche eine zur Aufnahme eines Dichtelements vorgesehene Nut angeordnet ist, die sich unter Abstand zum Rand zumindest teilweise entlang des Randes erstreckt, und wobei die Nut einen der Nutöffnung gegenüberliegenden Nutgrund und zwei daran angrenzende, einander zugewandte, sich entlang des Randes erstreckende Seitenwände umfasst.The invention relates to a component for hotgasbeaufschlagbares gas turbine, with at least one wall,
  • which comprises a first surface to an edge, the first surface being intended to confine a hot gas flow path of the gas turbine, and
  • which comprises a second surface adjoining the edge and arranged transversely to the first surface,
wherein in the second surface provided for receiving a sealing element groove is arranged, which extends at a distance from the edge at least partially along the edge, and wherein the groove has a slot opening opposite the groove bottom and two adjacent thereto, facing each other, extending along the edge Includes side walls.

Derartige Bauteile sind zur Bildung einer Dichtungsanordnung aus dem Stand der Technik bekannt. Beispielsweise offenbart die GB 2 195 403 A zwei derartige Bauteile, deren zweite Oberflächen einander spaltbildend gegenüberliegen, wobei die dann ebenso einander gegenüberliegenden Nuten ein Dichtelement aufnehmen, welches den Spalt gegen eine Durchströmung weitestgehend sperrt.Such components are known for forming a seal assembly of the prior art. For example, the GB 2 195 403 A two such components whose second surfaces face each other gap-forming, wherein the then equally opposed grooves receive a sealing element which blocks the gap as far as possible against a flow.

So schlägt beispielsweise die EP 2 615 254 A2 vor, in der heißgasseitig angeordneten Dichtnutseitenwand zu Gruppen zusammenfassbare Lüftungsnuten vorzusehen, die sich von ihrem Boden zu ihrer, in der Dichtnutseitenwand mündenden Öffnung hin verjüngen. Damit soll eine verbesserte Kühlwirkung bei gleichzeitig verringertem Verschleiß erreicht werden.For example, the EP 2 615 254 A2 to provide in the hot gas side arranged Dichtnutseitenwand to groups summarized ventilation grooves that taper from their bottom to their opening in the Dichtnutseitenwand opening. This is an improved cooling effect while reducing wear can be achieved.

Zudem ist es der EP 2 365 188 A1 bekannt, auch in beiden Dichtnutseitenwänden jeweils einander gegenüberliegende und paarweise miteinander verbundene Kanäle zur Kühlluftdurchleitung gleichmäßig verteilt anzuordnen. Mit diesen soll das in den Dichtnuten sitzende Dichtelement hinreichend kühlbar sein.It is also the EP 2 365 188 A1 also known in both Dichtnutseitenwänden each opposite and To arrange evenly distributed channels for cooling air passage in pairs. With these, the seated in the sealing sealing element should be sufficiently cool.

Des weiteren sind aus der EP 2 615 255 A1 und der JP 2009/257281 A1 Dichtungsanordnungen bekannt, bei denen den Dichtnuten durch separate, darin mündende Kühlluftzuführungen Kühlluft zuführbar sind.Furthermore, from the EP 2 615 255 A1 and the JP 2009/257281 A1 Sealing arrangements are known in which the sealing grooves can be supplied with cooling air by separate cooling air feeds opening into them.

Es hat sich jedoch herausgestellt, dass trotz der bekannten Varianten derartige Dichtungsanordnungen stellenweise zu Oxidationen neigen können. Die Oxidationen führen zu Materialverlust, so dass die Bauteile, welche zumeist als Turbinenschaufeln ausgestaltet sind, nicht mehr aufbereitet werden können, so dass deren Lebensdauerende vorzeitig eintritt. Zum einen verringert dies die Verfügbarkeit einer mit diesen Turbinenschaufeln ausgestatteten Gasturbine und zum anderen erhöht dies die Ausschussrate an auszutauschenden Turbinenschaufeln im Bedarfsfall.However, it has been found that, in spite of the known variants, such sealing arrangements may in places tend to oxidize. The oxidation leads to loss of material, so that the components, which are usually designed as turbine blades, can not be processed, so that their end of life occurs prematurely. On the one hand, this reduces the availability of a gas turbine equipped with these turbine blades and, on the other hand, this increases the reject rate of turbine blades to be replaced if necessary.

Aufgabe der Erfindung ist daher die Bereitstellung eines mit Heißgas beaufschlagbares Bauteil, dessen Ränder weniger zu Verschleiß neigen. Weitere Aufgabe der Erfindung ist die Bereitstellung einer langlebigen, vergleichsweise oxdiationsresistenten und kostengünstigen Dichtungsanordnung umfassend zwei Bauteile, die jeweils so angeordnet sind, dass deren zweiten Seitenoberflächen sich spaltbildend einander gegenüberliegen und in deren einander gegenüberliegenden Nuten ein Dichtelement zur Abdichtung des Spalts eingesetzt ist.The object of the invention is therefore to provide a hot gas acted upon component whose edges are less prone to wear. Another object of the invention is to provide a durable, relatively oxidation-resistant and inexpensive seal assembly comprising two components which are each arranged so that their second side surfaces are gap-forming face each other and in their opposite grooves, a sealing element is used to seal the gap.

Die der Erfindung zugrundeliegende Aufgabe wird mit einem heißgasbeaufschlagbaren Bauteil gemäß den Merkmalen des Anspruchs 1 und mit einer Dichtungsanordnung gemäß den Merkmalen des Anspruchs 5 gelöst.The problem underlying the invention is achieved with a component which can be charged with hot gas in accordance with the features of claim 1 and with a sealing arrangement according to the features of claim 5.

Weitere vorteilhafte Ausgestaltungen sind in den abhängigen Ansprüchen angegeben.Further advantageous embodiments are specified in the dependent claims.

Erfindungsgemäß ist bei dem heißgasbeaufschlagbaren Bauteil für eine Gasturbine, mit zumindest einer Wand,

  • die eine erste Oberfläche bis zu einem Rand umfasst, wobei die erste Oberfläche zur Begrenzung eines Heißgas-Strömungspfads der Gasturbine bestimmt ist, und
  • die eine an den Rand angrenzende, quer zur ersten Oberfläche angeordnete zweite Oberfläche umfasst, wobei in der zweiten Oberfläche eine zur Aufnahme eines Dichtelements vorgesehene Nut angeordnet ist, die sich unter Abstand zum Rand zumindest teilweise entlang des Randes erstreckt, und wobei die Nut einen der Nutöffnung gegenüberliegenden Nutgrund und zwei daran angrenzende, einander zugewandte, sich entlang des Randes erstreckende Seitenwände umfasst, von denen die eine der beiden heißgasseitig und die andere kaltgasseitig angeordnet ist und jeweils Vertiefungen aufweisen, wobei zumindest einige der Vertiefungen zu einer Gruppe zusammenfassbar sind, deren Vertiefungen dergestalt angeordnet sind, dass zwei dieser Vertiefungen der besagten Gruppe in der heißgasseitigen Seitenwand angeordnet sind und derart zueinander beabstandet sind, das eine weitere, in der kaltgasseitigen Seitenwand angeordnete Vertiefung der besagten Gruppe jede der beiden heißgasseitigen Vertiefungen teilweise gegenüberliegt.
According to the invention, in the gas component which can be charged with hot gas for a gas turbine, with at least one wall,
  • which comprises a first surface up to an edge, the first surface being for limiting a hot gas flow path of the gas turbine, and
  • which comprises a second surface adjacent to the edge and arranged transversely to the first surface, wherein a groove provided for receiving a sealing element is arranged in the second surface, which extends at least partially along the edge at a distance from the edge, and wherein the groove is one of Groove opening opposite groove bottom and two adjacent thereto, facing each other, extending along the edge extending side walls, of which one of the two Heißgasseitig and the other cold gas side is arranged and each have recesses, wherein at least some of the recesses are summarized into a group whose recesses are arranged such that two of these wells of said group are arranged in the hot gas side wall and are spaced from each other so that a further, arranged in the cold gas side wall recess of said group each of the two hot gas wells part wise opposite.

Die nutförmigen Vertiefungen in einer Seitenwand bzw. in beiden Seitenwänden dienen als Strömungspassagen für Kühlluft und sind vorzugsweise dort angesiedelt, wo die Ränder der Bauteile höheren Verschleiß und Oxidation ausgesetzt sind. Mithin vermindert das örtlich gezielte Ausblasen der durch die Ausmaße der Vertiefungen vorbestimmbaren Kühlluftmenge die thermische Belastung und verbessert die Widerstandsfähigkeit des beanspruchten Areals. Gleichzeitig wird durch die Vertiefungen in den Seitenwänden der Nut die Menge an zu kühlendem Bauteilmaterial reduziert, warum die nutförmigen Vertiefungen in den Seitenwänden eine technisch sinnvollere Lösung darstellen als die Dichtelemente der GB 2 195 403 A , die ihrerseits stellenweise Schlitze zum Durchlass von Kühlluft aufweisen. Da in der erfindungsgemäßen Dichtungsanordnung Schlitze in den Dichtelementen, die in den Nuten eingesetzt sind, vermieden werden können, sind die Dichtelemente langlebiger als Dichtelemente mit Schlitzen. Dadurch erreicht die erfindungsgemäße Dichtungsanordnung, bei der zumindest eines der Bauteile, vorzugsweise beide Bauteile erfindungsgemäß ausgestaltet und so zueinander angeordnet sind, dass deren zweiten Oberflächen sich spaltbildend einander gegenüberliegen und in deren einander gegenüberliegenden Nuten ein Dichtelement zur Abdichtung des Spalts eingesetzt ist, ein insgesamt längere Lebensdauer. Vorzugsweise ist dann das Dichtelement plattenförmig ausgestaltet. Das heißt, es ist frei von Schlitzen, Vertiefungen oder Verjüngungen, die zur gezielten Durchleitung von Kühlluft vorgesehen sind.The groove-shaped recesses in a side wall or in both side walls serve as flow passages for cooling air and are preferably located where the edges of the components are exposed to higher wear and oxidation. Thus, locally targeted blowing out of the amount of cooling air predeterminable by the dimensions of the depressions reduces the thermal load and improves the resistance of the claimed area. At the same time the amount of component material to be cooled is reduced by the depressions in the side walls of the groove, why the groove-shaped depressions in the side walls represent a technically more sensible solution than the sealing elements of the GB 2 195 403 A , in turn, in places slits for the passage of cooling air exhibit. Since in the sealing arrangement according to the invention, slots in the sealing elements, which are inserted in the grooves, can be avoided, the sealing elements are more durable than sealing elements with slots. As a result, the sealing arrangement according to the invention achieves at least one of the components, preferably both components designed according to the invention and arranged relative to one another such that their second surfaces lie opposite one another in a gap-forming manner and a sealing element is used to seal the gap in their opposing grooves, an overall longer one Lifespan. Preferably, then, the sealing element is designed plate-shaped. That is, it is free of slits, depressions or tapers, which are intended for the targeted passage of cooling air.

Die nutförmigen Vertiefungen der Seitenwände erstrecken sich von der Nutöffnung der das Dichtelement aufnehmenden Nut bis zum Nutgrund der das Dichtelement aufnehmenden Nut.The groove-shaped depressions of the side walls extend from the slot opening of the groove receiving the sealing element to the groove bottom of the groove receiving the sealing element.

Gemäß einer ersten vorteilhaften Weiterbildung weist jede Seitenwand in zumindest einem Längsabschnitt der die Dichtelemente aufnehmenden Nut mehrere Gruppen mit nutförmigen Vertiefungen auf. Hiermit werden sowohl kaltgasseitig als auch heißgasseitig nutförmige Vertiefungen an den Seitenwänden der Nut bereitgestellt, durch welche das dadurch strömende Kühlmittel punktuell zu denjenigen Positionen geleitet werden kann, die thermisch und/oder korrosiv besonders hoch belastet sind.According to a first advantageous development, each side wall has a plurality of groups with groove-shaped depressions in at least one longitudinal section of the groove receiving the sealing elements. Hereby, both cold gas side and hot gas side groove-shaped recesses are provided on the side walls of the groove, through which the coolant flowing through it can be selectively directed to those positions which are particularly highly thermally and / or corrosively loaded.

Eine derartige Anordnung lässt sich besonders einfach herstellen, beispielsweise durch Erodieren, wobei die längeren Vertiefungen vorzugsweise kaltgasseitig angeordnet sind. Die enger positionierten Vertiefungen sind dann heißgasseitig angeordnet, was eine bessere und gleichmäßigere Kühlluftverteilung ermöglicht.Such an arrangement can be produced in a particularly simple manner, for example by erosion, wherein the longer depressions are preferably arranged on the cold gas side. The more closely positioned depressions are then arranged on the hot gas side, which allows a better and more uniform cooling air distribution.

Weiter weist die Nut einen Bereich auf, der frei von Vertiefungen ist und dessen Längserstreckung größer ist als die Längserstreckung einer einzelnen Gruppe.Furthermore, the groove has an area which is free of depressions and whose longitudinal extent is greater than the longitudinal extent of a single group.

Zweckmäßigerweise ist bei einer Weiterbildung der Dichtungsanordnung in jeder der einander gegenüberliegenden Nuten jeweils zumindest eine Gruppe von Vertiefungen vorgesehen, die in Bezug zueinander zumindest teilweise längs der Nuterstreckung versetzt sind. Das erfindungsgemäße Bauteil kann beispielsweise als Turbinenleitschaufeln, als Turbinenlaufschaufel oder als Ringsegment ausgestaltet sein. Weitere Anwendungsgebiete innerhalb der Gasturbine sind jedoch auch denkbar, beispielsweise beim Übergang von einer Brennkammer zu einem Ringkanal, in dem die Schaufeln der Turbine angeordnet sind.Expediently, in a development of the sealing arrangement, in each case at least one group of recesses is provided in each of the mutually opposing grooves, which are offset at least partially along the groove extension with respect to each other. The component according to the invention can be designed, for example, as turbine guide vanes, as a turbine blade or as a ring segment. However, further fields of application within the gas turbine are also conceivable, for example in the transition from a combustion chamber to an annular channel in which the blades of the turbine are arranged.

Insgesamt betrifft die Erfindung somit ein heißgasbeaufschlagbares Bauteil für eine Gasturbine, mit zumindest einer Wand, die eine erste Oberfläche bis zu einem Rand umfasst, wobei die erste Oberfläche zur Begrenzung eines Heißgas-Strömungspfads der Gasturbine bestimmt ist, und die eine an den Rand angrenzende, quer zur ersten Oberfläche angeordnete zweite Oberfläche umfasst, wobei in der zweiten Oberfläche eine zur Aufnahme eines Dichtelements vorgesehene Nut angeordnet ist, die sich unter Abstand zum Rand zumindest teilweise entlang des Randes erstreckt, und wobei die Nut einen der Nutöffnung gegenüberliegenden Nutgrund und zwei daran angrenzende, einander zugewandte, sich entlang des Randes erstreckende Seitenwände umfasst, von denen die eine der beiden heißgasseitig und die andere kaltgasseitig angeordnet ist und jeweils Vertiefungen aufweisen. Um einen gute Abdichtung unter Beibehaltung einer definierten Kühlung des spaltbildenden Bauteile zu erreichen, wird vorgeschlagen, dass zumindest einige der Vertiefungen zu einer Gruppe zusammenfassbar sind, deren Vertiefungen dergestalt angeordnet sind, dass zwei dieser Vertiefungen der besagten Gruppe in der heißgasseitigen Seitenwand angeordnet sind und derart zueinander beabstandet sind, das eine weitere, in der kaltgasseitigen Seitenwand angeordnete Vertiefung der besagten Gruppe jede der beiden heißgasseitigen Vertiefungen teilweise gegenüberliegt.Overall, the invention thus relates to a component for a gas turbine which can be charged with hot gas, with at least one wall having a first surface up to an edge, wherein the first surface is intended to delimit a hot gas flow path of the gas turbine, and the one adjacent to the edge, Arranged transversely to the first surface disposed second surface, wherein in the second surface provided for receiving a sealing member groove is arranged, which extends at a distance from the edge at least partially along the edge, and wherein the groove opposite the groove opening groove bottom and two adjacent thereto , side walls extending towards each other and extending along the edge, of which one of the two is located on the hot gas side and the other on the cold gas side and in each case have depressions. In order to achieve a good seal while maintaining a defined cooling of the gap-forming components, it is proposed that at least some of the recesses are summarized in a group whose recesses are arranged such that two of these recesses of said group are arranged in the hot gas side wall and so spaced apart from each other, the one in the Cold gas side wall arranged recess of said group is partially opposite each of the two hot gas side wells.

Weitere Vorteile und Merkmale der Erfindung werden anhand mehrerer Ausführungsbeispiele angegeben. Es zeigen:

FIG 1
eine Seitenansicht einer Turbinenschaufel im Bereich der Plattform mit einer Nut zur Aufnahme eines Dichtelements und
FIG 2
den Querschnitt durch eine Dichtungsanordnung mit zwei unmittelbar benachbarten Bauteilen, deren erfindungsgemäße Nuten einander unmittelbar gegenüberliegen und in denen ein plattenförmiges Dichtelement angeordnet ist.
Further advantages and features of the invention will be indicated with reference to several embodiments. Show it:
FIG. 1
a side view of a turbine blade in the region of the platform with a groove for receiving a sealing element and
FIG. 2
the cross section through a seal assembly with two immediately adjacent components whose grooves according to the invention directly opposite each other and in which a plate-shaped sealing element is arranged.

In allen Figuren sind identische Merkmale mit den gleichen Bezugszeichen versehen.In all figures, identical features are provided with the same reference numerals.

FIG 1 zeigt in einer Seitenansicht eine Turbinenleitschaufel 11 als Bauteil 10 einer stationären Gasturbine. Die Turbinenleitschaufel 11 umfasst ein fußseitiges Ende 12 sowie ein nicht weiter dargestelltes kopfseitiges Ende, zwischen denen sich ein aerodynamisch gekrümmtes Schaufelblatt 16 erstreckt. Das Schaufelblatt 16 selber erstreckt sich in Spannweiterichtung von seinem fußseitigen Ende 13 zu seinem kopfseitigen Ende. Quer dazu erstreckt sich das Schaufelblatt 16 von einer Anströmkante 18 zu einer Hinterkante 20. Sowohl am fußseitigen Ende 13 als auch am kopfseitigen Ende ist eine Plattform 22 vorgesehen, die einen dazwischen angeordneten Strömungspfad 24 für Heißgas begrenzen. Dazu weist jede Plattform 22 eine dem Heißgas-Strömungspfad 24 zugewandte Oberfläche 26 auf. Die Oberfläche 26, nachfolgend als erste Oberfläche 26 bezeichnet, endet seitlich an einem Rand 28. Dieser Rand 28 kann - wie dargestellt - als Kante ausgeführt sein. An den Rand 28 schließt sich eine zweite Oberfläche 30 an, welche quer zur ersten Oberfläche 26 orientiert ist. Wenn der Rand 28 nicht als Kante, sondern als Radius ausgeführt ist, gehen die erste und die zweite Oberfläche 26, 30 ineinander über. FIG. 1 shows a side view of a turbine vane 11 as a component 10 of a stationary gas turbine. The turbine guide vane 11 comprises a foot-side end 12 and a not further illustrated head-side end, between which an aerodynamically curved airfoil 16 extends. The blade 16 itself extends in Spannweiterichtung from its foot-side end 13 to its head end. Transversely thereto, the airfoil 16 extends from a leading edge 18 to a trailing edge 20. Both at the foot end 13 and at the head end, a platform 22 is provided which define a flow path 24 for hot gas therebetween. For this purpose, each platform 22 has a surface 26 facing the hot gas flow path 24. The surface 26, hereinafter referred to as the first surface 26 ends laterally at an edge 28. This edge 28 may - as shown - be designed as an edge. At the edge 28, a second surface 30 connects, which is oriented transversely to the first surface 26. If the edge 28 is designed not as an edge, but as a radius, go the first and the second surface 26, 30 into each other.

Bei der Verwendung der gezeigten Turbinenleitschaufel innerhalb einer Gasturbine bilden mehrere, in einem Kranz angeordnete Turbinenleitschaufeln 11 eine Leitschaufelreihe, wobei dann die zweiten Oberflächen 30 unmittelbar benachbarter Turbinenschaufeln 11 jeweils spaltbildend einander gegenüberliegen (FIG 2). Für derartige Anordnungen sind dann nur diejenigen Ränder 28 der Plattformen relevant, die in Umfangsrichtung gesehen die erste Oberfläche 26 begrenzen.When using the turbine vane shown within a gas turbine, a plurality of turbine vanes 11 arranged in a ring form a row of vanes, in which case the second surfaces 30 of directly adjacent turbine blades 11 are each gap-forming (FIG. FIG. 2 ). For such arrangements, only those edges 28 of the platforms that bound the first surface 26 in the circumferential direction are then relevant.

Um den von zwei unmittelbar gegenüberliegenden zweiten Oberflächen 30 benachbarten Turbinenschaufeln 10 begrenzten Spalt weitestgehend abzudichten und eine definierte Leckage zuzulassen, sind in den zweiten Oberflächen 30 Nuten 34 vorgesehen, in denen ein plattenförmiges Dichtelement 44 (FIG 2) sitzt. Die beiden Bauteile 10 und das Dichtelement 44 bilden dann eine Dichtungsanordnung 40, welche verhindert, dass das im Strömungspfad 24 geführte Heißgas in andere, jenseits der Plattformen 22 liegende Bereiche 41 hinausströmen kann. Jede Nut 34 weist zwei Seitenwände 36 auf. Hier kann zwischen einer ersten Seitenwand 36a und einer zweiten Seitenwand 36b unterschieden werden, wobei die erste Seitenwand 36a jeweils der ersten Oberfläche 26 bzw. dem Rand 28 näher angeordnet ist als die zweite Seitenwand 36b. Mithin kann von einer heißgasseitigen Seitenwand 36a und von einer kaltgasseitigen Seitenwand 36b die Rede sein. Wenn nachfolgend nur von der Seitenwand 36 (ohne "a" und "b") die Rede ist, so gelten die gemachten Ausführungen selbstredend für jede Seitenwand.In order to largely seal the gap defined by two directly opposite second surfaces 30 adjacent turbine blades 10 and to allow a defined leakage, 30 grooves 34 are provided in the second surfaces, in which a plate-shaped sealing element 44 (FIG. FIG. 2 ) sits. The two components 10 and the sealing element 44 then form a sealing arrangement 40, which prevents the hot gas guided in the flow path 24 from flowing into other regions 41 lying beyond the platforms 22. Each groove 34 has two side walls 36. Here, a distinction can be made between a first side wall 36a and a second side wall 36b, the first side wall 36a being arranged closer to the first surface 26 and the edge 28, respectively, than the second side wall 36b. Consequently, there can be talk of a hot gas side wall 36a and a cold gas side wall 36b. If only the side wall 36 (without "a" and "b") is mentioned below, then the explanations given are of course valid for each side wall.

Jede Nut 34 erstreckt sich entlang des Randes 28, jedoch unter einem geringen Abstand dazu. In jeder Seitenwand 36 sind nutförmige Vertiefungen 38 vorgesehen.Each groove 34 extends along the edge 28, but at a slight distance thereto. In each side wall 36 groove-shaped recesses 38 are provided.

Nachfolgend und in Verbindung mit FIG 1 wird zuerst die Geometrie der Nut 34 näher erläutert. Jede Seitenwand 36 der Nut 34 weist entlang ihrer Längserstreckung vom anströmseitigen Ende (18) zum abströmseitigen Ende (20) mehrere, aufeinanderfolgende Vertiefungen 38 auf. Somit wechseln sich Erhebungen und Vertiefungen 38 in der Seitenwand 36a sowie in der Seitenwand 36b ab. In Bezug auf die beiden Seitenwände 36a, 36b sind die Vertiefungen 38 und die zwischen zwei Vertiefungen 38 verbliebenden Erhebungen mit geringem Versatz angeordnet, sodass sowohl Vertiefungen 38 als auch Erhebungen zu Gruppen 39 - wie durch die gestrichelten Kreise dargestellt - logisch zusammengefasst werden können.Below and in conjunction with FIG. 1 First, the geometry of the groove 34 is explained in more detail. Each side wall 36 of the groove 34 has along its longitudinal extent from the upstream side End (18) to the downstream end (20) a plurality of successive recesses 38. Thus, elevations and depressions 38 alternate in the side wall 36a and in the side wall 36b. With respect to the two side walls 36a, 36b, the recesses 38 and the protrusions remaining between two recesses 38 are arranged with a small offset, so that both depressions 38 and elevations to groups 39 can be logically combined, as represented by the dashed circles.

Die Vertiefungen 38 an den Seitenwänden 36 der Nut 34 sind dabei derartig längs der beiden Seitenwände 36 verteilt, dass die Stufen zwischen Vertiefungen 36 und Erhebungen einer Seitenwand 36a (36b) gegenüber den Stufen der anderen Seitenwand 36b (36a) versetzt sind. Zudem sind die heißgasseitigen Vertiefungen 38a nur halb so lang wir die kaltgasseitigen Vertiefungen 38b.The depressions 38 on the side walls 36 of the groove 34 are distributed along the two side walls 36 such that the steps between recesses 36 and elevations of one side wall 36a (36b) are offset from the steps of the other side wall 36b (36a). In addition, the hot gas side recesses 38a are only half as long as the cold gas side recesses 38b.

Im Betrieb strömt Kühlluft in die kaltgasseitigen Vertiefungen 38b ein, so dass unter Umströmung des Dichtelements 44 jede kaltgasseitige Vertiefung 38b zwei heißgasseitige Vertiefungen 38a mit Kühlluft versorgen kann. Insofern kann hierdurch eine Gruppe 39 definiert werden.In operation, cooling air flows into the cold gas side recesses 38b, so that each cold gas side recess 38b can supply two hot gas side recesses 38a with cooling air while flowing around the sealing element 44. In this respect, a group 39 can be defined thereby.

Die Nut 34 kann selbstverständlich auch bei Ringsegmenten verwendet werden, die in Umfangsrichtung einen Kreis bildend einen axialen Abschnitt des Strömungspfades 24 der Gasturbine radial außerhalb von den Spitzen von Laufschaufeln begrenzen können.Of course, the groove 34 may also be used with ring segments circumferentially forming a circle defining an axial portion of the gas turbine flow path 24 radially outward of the tips of blades.

In dem gemäß FIG 2 dargestellten Ausführungsbeispiel der Nut 34 gibt es längere Nutabschnitte 43, die frei von Vertiefungen 38 sind. Derartige Nuten 34 bieten sich dort an, wo nur an bestimmten Positionen des Randes bzw. der ersten Oberfläche 26 erhöhte Verschleißerscheinungen auftreten.In the according to FIG. 2 illustrated embodiment of the groove 34, there are longer groove portions 43, which are free of recesses 38. Such grooves 34 offer themselves where only at certain positions of the edge or the first surface 26 increased signs of wear occur.

Zudem zeigt FIG 1 in gepunkteter Linienart einen Teil einer Nut 41, die demjenigen (nicht gezeigten) Bauteil zugehörig ist, welcher der Plattform 22 der dargestellten Turbinenleitschaufel 11 spaltbildend gegenüberliegt. Dabei ist die Darstellung der Nut 41 gespiegelt in Bezug auf die Nut 34, so dass die heißgasseitigen Vertiefungen 38a der Nut 41 in FIG 1 oberhalb der kaltgasseitigen Vertiefungen 38b dargestellt sind.In addition shows FIG. 1 in dotted line style, part of a groove 41 associated with the component (not shown) which is opposite to the platform 22 of the illustrated turbine vane 11 gap forming. In this case, the representation of the groove 41 is mirrored with respect to the groove 34, so that the hot gas side recesses 38a of the groove 41 in FIG. 1 are shown above the cold gas side recesses 38b.

Wie aus dieser Darstellung gut zu erkennen ist, sind die beiden Gruppen 39 und 42 von Vertiefungen 38 der beiden einander gegenüberliegenden Bauteile um einen Abstand A zueinander versetzt. Dies ermöglicht eine längs des Spalts nahezu ununterbrochene Anordnung von heißgasseitigen Vertiefungen 38a, so dass in diesem Bereich eine besonders gute Kühlung mit einer definierten Kühlluftmenge möglich ist.As can be clearly seen from this illustration, the two groups 39 and 42 of recesses 38 of the two opposing components offset by a distance A to each other. This allows an arrangement of hot gas-side depressions 38a that is virtually continuous along the gap, so that particularly good cooling with a defined amount of cooling air is possible in this region.

Die FIG 2 zeigt im Querschnitt die Dichtungsanordnung 40 umfassend zwei Bauteile 10 mit jeweils einer ersten Oberfläche 26, die dafür bestimmt ist, einen Strömungspfad 24 der Gasturbine zu begrenzen, wobei die ersten Oberflächen 26 über Ränder 28 in eine zweite Oberfläche 30 übergehen, welche zweiten Oberflächen 30 quer zu den ersten Oberflächen 26 angeordnet sind. In jeder zweiten Oberfläche 30 sind die längs des Randes 28 und mit Abstand dazu parallel verlaufenden Nuten 34 angeordnet, die an ihren Seitenwänden 36 entlang der Längserstreckung der Nut 34 ein oder mehrere Vertiefungen 38 aufweisen können. Die Vertiefungen 38 erstrecken sich von einer Nutöffnung 42, die in der zweiten Oberfläche 30 liegt, bis zu einem Nutgrund 46, welcher besagten Nutöffnung 42 gegenüber liegt.The FIG. 2 shows in cross section the seal assembly 40 comprising two components 10, each having a first surface 26, which is intended to define a flow path 24 of the gas turbine, wherein the first surfaces 26 pass over edges 28 in a second surface 30, which second surfaces 30 across are arranged to the first surfaces 26. In each second surface 30 along the edge 28 and spaced therefrom parallel grooves 34 are arranged, which may have on its side walls 36 along the longitudinal extension of the groove 34 one or more recesses 38. The recesses 38 extend from a groove opening 42, which lies in the second surface 30, to a groove bottom 46, which lies opposite said groove opening 42.

Die Vertiefungen 38 ermöglichen die gezielte und dosierte Strömung von Kühlluft von einer Kaltgasseite 48, die jenseits der Plattformen 22 liegt, zu einer Heißgasseite, die diesseits der Plattformen 22 liegt und die den Strömungspfad 24 der Gasturbine begrenzen.The recesses 38 allow for the targeted and metered flow of cooling air from a cold gas side 48 that lies beyond the platforms 22 to a hot gas side that lies on either side of the platforms 22 and that define the flow path 24 of the gas turbine.

Gleichwohl es anmutet, dass das Herstellen der erfindungsgemäßen Nuten 34 aufwändiger ist, kann festgehalten werden, dass sich diese vergleichsweise einfach mittels Erodieren herstellen lassen.Although it may seem that the manufacture of the grooves 34 according to the invention is more complex, it can be stated that that they can be produced comparatively easily by means of erosion.

In den Nuten 36 sind Dichtelemente 44 eingesetzt. Diese sind entlang ihrer Längserstreckung - also parallel zum Rand 28 - eben ausgestaltet und weisen somit in dieser Richtung über ihre gesamte Längserstreckung die gleiche Materialstärke auf. Das heißt, die Dichtelemente 44 sind frei von Schlitzen oder Ausnehmungen, mit denen Kühlluft gezielt von der Kaltgasseite 48 zu Heißgasseite geführt werden kann. Gleichwohl kann an einer oder beiden Flächen des Dichtelements 44, die den Seitenwänden 36 zugewandt sind, Dichtspitzen angeordnet sein, die prinzipiell das Auftreten einer Kühlluftströmung in denjenigen Abschnitten der Nut 34 verhindern, die nicht vertieft sind.In the grooves 36 sealing elements 44 are used. These are along their longitudinal extent - ie parallel to the edge 28 - designed flat and thus have the same material thickness in this direction over its entire longitudinal extent. That is, the sealing elements 44 are free of slots or recesses with which cooling air can be selectively guided from the cold gas side 48 to the hot gas side. However, at one or both surfaces of the sealing element 44, which face the side walls 36, sealing tips may be arranged, which in principle prevent the occurrence of a cooling air flow in those portions of the groove 34, which are not deepened.

Claims (7)

  1. Component (10) which can be subjected to hot gas for a gas turbine, having at least one wall
    - which comprises a first surface (26) as far as an edge (28), wherein the first surface (26) is intended for delimiting a hot gas flow path of the gas turbine, and
    - which comprises a second surface (30) which adjoins the edge (28) and is arranged transversely with respect to the first surface (26), wherein a groove (34) provided for receiving a sealing element (44) is arranged in the second surface (30) and extends at least partially along the edge (28) at a distance from the edge (28), and
    wherein the groove (34) comprises a groove base (46) and two mutually facing side walls (36) which adjoin said groove face and extend along the edge, of which side walls one of the two is arranged on the hot gas side and the other is arranged on the cold gas side and each have recesses (38),
    characterized in that at least some of the recesses (38a, 38b) can be combined to form a group (39), the recesses (38a, 38b) of which are arranged in such a manner that two of said recesses (38a) of said group (39) are arranged in the hot-gas-side side wall (36a) and are spaced apart from each other in such a manner that a further recess (38b) of said group, which recess is arranged in the cold-gas-side side wall (36b), partially lies opposite each of the two hot-gas-side recesses.
  2. Component (10) according to Claim 1, in which each side wall (36) has a plurality of groups (39) of recesses (38) in at least one longitudinal portion of the groove (34).
  3. Component (10) according to Claim 2, in which the relevant group (39) has a longitudinal extent which is detectable in the longitudinal direction of the groove (34), and in that the groove (34) has a region which is free of recesses and the longitudinal extent of which is greater than the longitudinal extent of an individual group (39).
  4. Component (10) according to one of Claims 1 to 3, configured as a turbine blade or as an annular segment.
  5. Sealing arrangement (40) comprising two components (10), of which at least one, preferably the two components (10), in each case configured according to one of Claims 1 to 4, are arranged in such a manner that the second surfaces (30) thereof lie opposite each other forming a gap and a sealing element (44) is inserted into the mutually opposite grooves (34) thereof for sealing the gap.
  6. Sealing arrangement (40) according to Claim 5, in which the sealing element (40) is configured in the shape of a panel and has sealing teeth on at least one of the two sealing element surfaces facing the side walls (36) of the groove.
  7. Sealing arrangement according to Claim 5 or 6, in which in each case at least one group (39) of recesses (38a, 38b) is provided in each of the mutually opposite grooves (34), said recesses being offset with respect to one another at least partially along the groove extent.
EP15705578.1A 2014-02-14 2015-02-13 Component that can be charged with hot gas for a gas turbine and sealing assembly with such a component Active EP3087254B1 (en)

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JP6273031B2 (en) 2018-01-31
WO2015121407A1 (en) 2015-08-20
JP2017507275A (en) 2017-03-16
CN105980664B (en) 2018-02-16
EP3087254A1 (en) 2016-11-02
US20160362996A1 (en) 2016-12-15
SA516371638B1 (en) 2021-12-13
EP2907977A1 (en) 2015-08-19
CN105980664A (en) 2016-09-28

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