EP3087254B1 - Composant pouvant être alimenté par un gaz chaud pour une turbine à gaz et système d'étanchéité doté d'un tel composant - Google Patents

Composant pouvant être alimenté par un gaz chaud pour une turbine à gaz et système d'étanchéité doté d'un tel composant 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
Authority
EP
European Patent Office
Prior art keywords
groove
recesses
gas
edge
component
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.)
Active
Application number
EP15705578.1A
Other languages
German (de)
English (en)
Other versions
EP3087254A1 (fr
Inventor
Fathi Ahmad
Ralf Müsgen
Radan RADULOVIC
Marco Schüler
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP15705578.1A priority Critical patent/EP3087254B1/fr
Publication of EP3087254A1 publication Critical patent/EP3087254A1/fr
Application granted granted Critical
Publication of EP3087254B1 publication Critical patent/EP3087254B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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.

Landscapes

  • 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)

Claims (7)

  1. Pièce (10) pouvant être soumise à du gaz chaud pour une turbine à gaz,
    ayant au moins une paroi,
    - qui comprend une première surface (26) allant jusqu'à un bord (28), la première surface (26) étant destinée à un trajet d'écoulement de gaz chaud de la turbine à gaz et
    - qui comprend une deuxième surface (30) voisine du bord (28) et disposée transversalement à la première surface (26), une rainure (34), prévue pour la réception d'un élément (44) d'étanchéité, est aménagée dans la deuxième surface (30), rainure qui s'étend à distance du bord (28), au moins en partie le long du bord (28) et
    dans laquelle la rainure (34) comprend un fond (46) de rainure et deux parois (36) latérales, qui en sont voisines, qui sont tournées l'une vers l'autre, qui s'étendent le long du bord et dont l'une des deux est disposée du côté du gaz chaud et l'autre du côté du gaz froid et qui ont chacune des cavités (38),
    caractérisée en ce qu'
    au moins certaines des cavités (38a, 38b) peuvent être réunies en un groupe (39), dont les cavités (38a, 38b) sont disposées de manière à ce que deux de ces cavités (38a) dudit groupe (39) soient disposées dans la paroi (36a) latérale du côté du gaz chaud et soient à distance l'une de l'autre de manière à ce qu'une autre cavité (38b), disposée dans la paroi (36b) latérale du côté du gaz froid dudit groupe soit opposée, au moins en partie, à chacune des deux cavités du côté du gaz chaud.
  2. Pièce (10) suivant la revendication 1,
    dans laquelle chaque paroi (36) latérale a, dans au moins un tronçon longitudinal de la rainure (34) plusieurs groupes (39) de cavités (38).
  3. Pièce (10) suivant la revendication 2,
    dans laquelle le groupe (39) concerné a une étendue longitudinale, qui peut être détectée dans la direction longitudinale de la rainure (34) et en ce que la rainure (34) a une partie qui est sans cavité et dont l'étendue longitudinale est plus grande que l'étendue longitudinale d'un groupe (39) individuel.
  4. Pièce (10) suivant l'une des revendications 1 à 3, conformée en aube de turbine ou en segment annulaire.
  5. Agencement (40) d'étanchéité, comprenant deux pièces (10), dont au moins l'une, de préférence les deux (10), conformées chacune suivant l'une des revendications 1 à 4, sont disposées de manière à ce que leur deuxième surface (30) soit en face l'une de l'autre en formant un intervalle et, dans leur rainure (34) se faisant face, est inséré un élément (44) d'étanchéité pour rendre étanche l'intervalle.
  6. Agencement (40) d'étanchéité suivant la revendication 5, dans lequel l'élément (40) d'étanchéité est en forme de plaque et a des dents d'étanchéité sur au moins l'une des deux surfaces d'élément d'étanchéité tournées vers les parois (36) latérales de la rainure.
  7. Agencement suivant la revendication 5 ou 6,
    dans lequel, dans chacune des rainures (34) se faisant face, est prévu respectivement au moins un groupe (39) de cavités (38a, 38b), qui sont décalées les unes par rapport aux autres, au moins en partie le long de l'étendue de la rainure.
EP15705578.1A 2014-02-14 2015-02-13 Composant pouvant être alimenté par un gaz chaud pour une turbine à gaz et système d'étanchéité doté d'un tel composant Active EP3087254B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP15705578.1A EP3087254B1 (fr) 2014-02-14 2015-02-13 Composant pouvant être alimenté par un gaz chaud pour une turbine à gaz et système d'étanchéité doté d'un tel composant

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP14155131.7A EP2907977A1 (fr) 2014-02-14 2014-02-14 Composant pouvant être alimenté par un gaz chaud pour une turbine à gaz et système d'étanchéité doté d'un tel composant
EP15705578.1A EP3087254B1 (fr) 2014-02-14 2015-02-13 Composant pouvant être alimenté par un gaz chaud pour une turbine à gaz et système d'étanchéité doté d'un tel composant
PCT/EP2015/053070 WO2015121407A1 (fr) 2014-02-14 2015-02-13 Composant pouvant être exposé à un gaz chaud pour turbine à gaz et système d'étanchéité pourvu d'un tel composant

Publications (2)

Publication Number Publication Date
EP3087254A1 EP3087254A1 (fr) 2016-11-02
EP3087254B1 true EP3087254B1 (fr) 2018-04-18

Family

ID=50101768

Family Applications (2)

Application Number Title Priority Date Filing Date
EP14155131.7A Withdrawn EP2907977A1 (fr) 2014-02-14 2014-02-14 Composant pouvant être alimenté par un gaz chaud pour une turbine à gaz et système d'étanchéité doté d'un tel composant
EP15705578.1A Active EP3087254B1 (fr) 2014-02-14 2015-02-13 Composant pouvant être alimenté par un gaz chaud pour une turbine à gaz et système d'étanchéité doté d'un tel composant

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP14155131.7A Withdrawn EP2907977A1 (fr) 2014-02-14 2014-02-14 Composant pouvant être alimenté par un gaz chaud pour une turbine à gaz et système d'étanchéité doté d'un tel composant

Country Status (6)

Country Link
US (1) US20160362996A1 (fr)
EP (2) EP2907977A1 (fr)
JP (1) JP6273031B2 (fr)
CN (1) CN105980664B (fr)
SA (1) SA516371638B1 (fr)
WO (1) WO2015121407A1 (fr)

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US11002144B2 (en) * 2018-03-30 2021-05-11 Siemens Energy Global GmbH & Co. KG Sealing arrangement between turbine shroud segments
US11506129B2 (en) * 2020-04-24 2022-11-22 Raytheon Technologies Corporation Feather seal mateface cooling pockets
US11781440B2 (en) * 2021-03-09 2023-10-10 Rtx Corporation Scalloped mateface seal arrangement for CMC platforms

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Also Published As

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

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