EP2907977A1 - 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
EP2907977A1
EP2907977A1 EP14155131.7A EP14155131A EP2907977A1 EP 2907977 A1 EP2907977 A1 EP 2907977A1 EP 14155131 A EP14155131 A EP 14155131A EP 2907977 A1 EP2907977 A1 EP 2907977A1
Authority
EP
European Patent Office
Prior art keywords
groove
edge
component
side walls
gas turbine
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.)
Withdrawn
Application number
EP14155131.7A
Other languages
German (de)
English (en)
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 EP14155131.7A priority Critical patent/EP2907977A1/fr
Priority to EP15705578.1A priority patent/EP3087254B1/fr
Priority to PCT/EP2015/053070 priority patent/WO2015121407A1/fr
Priority to CN201580008567.6A priority patent/CN105980664B/zh
Priority to US15/117,334 priority patent/US20160362996A1/en
Priority to JP2016551734A priority patent/JP6273031B2/ja
Publication of EP2907977A1 publication Critical patent/EP2907977A1/fr
Priority to SA516371638A priority patent/SA516371638B1/ar
Withdrawn legal-status Critical Current

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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.
  • 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 depressions 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 subject to increased 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 , which in turn have in places slots for the passage of cooling air.
  • 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 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.
  • each well long considered the groove has a first length L t and perpendicular to the groove longitudinal extent a first depth T t .
  • L t ⁇ 2 L H ⁇ 2 .
  • Such an arrangement can be produced in a particularly simple manner, for example by erosion, the depression having the longer sections L t2 preferably being arranged on the cold gas side.
  • the tighter toothing with L t1 is then arranged on the hot gas side, which allows a better and more uniform cooling air distribution.
  • opposing recesses are longitudinally offset from each other according to a development.
  • the component according to the invention can be designed, for example, as a turbine guide vane, 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, Transverse to the first surface arranged second surface, wherein in the second surface provided for receiving a sealing element groove arranged is, which extends at a distance from the edge at least partially along the edge, and wherein the groove comprises a groove base opposite the groove opening and two adjoining, facing each other along the edge extending side walls.
  • at least one of the side walls has at least one groove-shaped depression.
  • FIG. 1 shows in perspective view as a component 10, a turbine guide vane for a stationary gas turbine.
  • the turbine vane includes a foot-side end 12 and a head-side end 14, 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-side end 15. Transversely, the blade 16 extends from a leading edge 18 to a trailing edge 20.
  • a platform 22 is provided which limit an interposed flow path 24 for hot gas.
  • 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, the first and second surfaces 26, 30 merge into one another.
  • a plurality of turbine vanes disposed in a ring form a row of vanes, and then the second surfaces 30 of immediately adjacent turbine vanes face each other in a gap forming manner. For such arrangements, only those edges 28 of the platforms that bound the first surface 26 in the circumferential direction are then relevant.
  • 30 grooves 34a, 34b are provided in the second surfaces, in which a plate-shaped sealing element 44 (Fig. FIG. 3 ) 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.
  • the groove provided at the head end 14 of the platform 22 will be referred to below by the reference numeral 34a, the groove disposed at the foot side by the reference numeral 34b. If the following is the tongue 34 (without “a” or "b"), the statements made are of course valid for both grooves.
  • Each groove 34 has two side walls 36. Again, a distinction is made between a first side wall 36a and a second side wall 36b, wherein the first side wall 36a of each of the first surface 26 and the edge 28 is arranged closer 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.
  • 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 34b has along its length from the upstream end (18) to the downstream end (20) a plurality of successive recesses 38 whose length L t1 detectable in this direction is equal to the length L h1 , said length L h1 between two recesses 38 is detected.
  • elevations and depressions 38 alternate regularly in the side wall 36a and in the side wall 36b.
  • the depressions 38 and the elevations remaining between two depressions 38 are arranged offset-free, so that both depressions 38 and elevations in pairs can be logically combined.
  • the recesses 38 on the side walls 36 of the groove 34a are distributed along the two side walls 36 such that the steps between depressions 36 and elevations of one side wall 36a (36b) are offset in half relative to the steps of the other side wall 36b (36a).
  • the term "half" refers to the length L t1 .
  • FIG. 2 shows a plan view of a second surface 30 with a along the edge 28 extending groove 34, which instead of in FIG. 1 shown grooves 34a or 34b may be arranged either on the head or foot side.
  • the groove may also be used with ring segments circumferentially forming a circle defining an axial portion of the flow path 24 of the gas turbine radially outward of the tips of blades.
  • groove 34 there are longer (ie longer than L h1 ) 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. 3 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)
EP14155131.7A 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 Withdrawn EP2907977A1 (fr)

Priority Applications (7)

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
CN201580008567.6A CN105980664B (zh) 2014-02-14 2015-02-13 可以经受用于燃气轮机的热气的组件和具有这种组件的密封装置
US15/117,334 US20160362996A1 (en) 2014-02-14 2015-02-13 Component which can be subjected to hot gas for a gas turbine and sealing arrangement having such a component
JP2016551734A JP6273031B2 (ja) 2014-02-14 2015-02-13 ガスタービンのための高温ガスに暴露され得る構成部品およびそのような構成部品を備えたシール手段
SA516371638A SA516371638B1 (ar) 2014-02-14 2016-08-09 مكون يمكن أن يتعرض لغاز ساخن من تربين غازي وتجهيزة منع تسرب بها ذلك المكون

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP2907977A1 true EP2907977A1 (fr) 2015-08-19

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 After (1)

Application Number Title Priority Date Filing Date
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

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)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3755886B1 (fr) * 2018-03-30 2023-12-13 Siemens Energy Global GmbH & Co. KG Agencement d'étanchéité entre les segments d'une virole de turbine
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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Publication number Priority date Publication date Assignee Title
GB2195403A (en) 1986-09-17 1988-04-07 Rolls Royce Plc Improvements in or relating to sealing and cooling means
EP1731714A1 (fr) * 2005-06-08 2006-12-13 Siemens Aktiengesellschaft Dispositif de blocage de fente et utilisation d'un tel dispositif
JP2009257281A (ja) * 2008-04-21 2009-11-05 Toshiba Corp ガスタービン静翼およびガスタービン装置
EP2365188A1 (fr) * 2010-03-03 2011-09-14 General Electric Company Refroidissement de composants de turbine à gaz comprenant des canaux dans les rainures de joints
EP2615254A2 (fr) * 2012-01-10 2013-07-17 General Electric Company Ensemble de stator pour une turbine à gaz ayant des composants adjacents avec des échancrures pour recevoir un élément d'étanchéité
EP2615255A1 (fr) * 2012-01-10 2013-07-17 General Electric Company Ensemble turbine et procédé de régulation de la température d'un ensemble

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JPH03213602A (ja) * 1990-01-08 1991-09-19 General Electric Co <Ge> ガスタービンエンジンの当接セグメントを連結する自己冷却式ジョイント連結構造
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2195403A (en) 1986-09-17 1988-04-07 Rolls Royce Plc Improvements in or relating to sealing and cooling means
EP1731714A1 (fr) * 2005-06-08 2006-12-13 Siemens Aktiengesellschaft Dispositif de blocage de fente et utilisation d'un tel dispositif
JP2009257281A (ja) * 2008-04-21 2009-11-05 Toshiba Corp ガスタービン静翼およびガスタービン装置
EP2365188A1 (fr) * 2010-03-03 2011-09-14 General Electric Company Refroidissement de composants de turbine à gaz comprenant des canaux dans les rainures de joints
EP2615254A2 (fr) * 2012-01-10 2013-07-17 General Electric Company Ensemble de stator pour une turbine à gaz ayant des composants adjacents avec des échancrures pour recevoir un élément d'étanchéité
EP2615255A1 (fr) * 2012-01-10 2013-07-17 General Electric Company Ensemble turbine et procédé de régulation de la température d'un ensemble

Also Published As

Publication number Publication date
US20160362996A1 (en) 2016-12-15
WO2015121407A1 (fr) 2015-08-20
JP6273031B2 (ja) 2018-01-31
SA516371638B1 (ar) 2021-12-13
CN105980664A (zh) 2016-09-28
JP2017507275A (ja) 2017-03-16
EP3087254A1 (fr) 2016-11-02
EP3087254B1 (fr) 2018-04-18
CN105980664B (zh) 2018-02-16

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Effective date: 20160220