EP3290642A1 - Segment annulaire de turbine et systeme destine a la delimitation exterieure d'un trajet d'ecoulement d'une turbine - Google Patents

Segment annulaire de turbine et systeme destine a la delimitation exterieure d'un trajet d'ecoulement d'une turbine Download PDF

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Publication number
EP3290642A1
EP3290642A1 EP16186537.3A EP16186537A EP3290642A1 EP 3290642 A1 EP3290642 A1 EP 3290642A1 EP 16186537 A EP16186537 A EP 16186537A EP 3290642 A1 EP3290642 A1 EP 3290642A1
Authority
EP
European Patent Office
Prior art keywords
sealing
ring
side wall
turbine
ring segment
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Withdrawn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
EP16186537.3A
Other languages
German (de)
English (en)
Inventor
Oliver Dominka
Ole Geisen
Marian Gollmer
David Rule
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 EP16186537.3A priority Critical patent/EP3290642A1/fr
Priority to EP17755096.9A priority patent/EP3472438B1/fr
Priority to CN201780053057.XA priority patent/CN109690025B/zh
Priority to PCT/EP2017/070030 priority patent/WO2018041555A1/fr
Priority to JP2019532171A priority patent/JP6941674B2/ja
Priority to US16/325,816 priority patent/US11319826B2/en
Publication of EP3290642A1 publication Critical patent/EP3290642A1/fr
Withdrawn legal-status Critical Current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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • 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
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F05D2240/59—Lamellar seals
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/283—Three-dimensional patterned honeycomb

Definitions

  • the invention relates to a ring segment according to the preamble of claim 1 and to an arrangement for limiting the outside of a flow path of a turbine.
  • the flow path is bounded radially outward inter alia by means of elements which can be assembled into a ring.
  • These elements are commonly known as ring segments, which extend over a certain arc length of the annular flow channel seen in cross-section.
  • the ring segments are hooked on one or more hook connections on a carrier, usually on the turbine guide vane carrier, so that its inwardly facing surface faces the tips of rotor blades passing thereunder.
  • the blade tips are designed with shrouds that clamp the blades together in the circumferential direction. At the outwardly facing surfaces of the shrouds extending sealing tips are arranged mostly in the circumferential direction, which define the gap to be minimized with the said ring segments.
  • the ring segments have sealing elements in the form of a honeycomb construction, also known in English as "honeycomb".
  • honeycomb also known in English as "honeycomb”.
  • the sealing tips pointing outward on the shrouds can cut into the lamellae of the honeycomb construction so as to further reduce a loss of working medium.
  • the object of the invention is therefore to provide a ring segment and an arrangement for the outer boundary of a flow path of a turbine, in which the leakage flow along said butt joints is further reduced. At the same time said arrangement should be particularly easy to manufacture and overall represent a particularly durable construction.
  • a plate-shaped wall which comprises a first side surface facing the blade tips of rotor blades in the installed state of the ring segment is and an edge which surrounds the first side surface and encloses closed at the four side wall sections with collide with the first side surface and provided with a sealing element which is arranged on the first side surface over the entire surface and which comprises four sealing side wall sections in an analogous manner to the wall, that on at least one of those side wall sections and / or at least one of those sealing side wall sections, - in one Turbine to a ring-mounted ring segments - to adjacent ring segments of the ring concerned, a number of unilaterally mounted sealing fins for reducing a flow along the respective sealing side wall portion is provided.
  • a mounted ring forming the flow path of a working fluid of a turbine outside are arranged limiting, the sealing lamellae of a first ring segment on a side wall portion or sealing side wall portion of a biased to the first ring segment immediately adjacent another ring segment.
  • each respective sealing side wall section or side wall section a plurality of sealing fins are provided.
  • the invention is based on the finding that the flow along said butt joint can be further reduced and, if necessary, even avoided if sealing slats are provided between immediately adjacent ring segments of an arrangement which at least partially obstruct the said leakage flow.
  • sealing strips are provided which, as it were, can be biased against the edges of a ring segment adjacent to one another on a first ring segment.
  • the sealing blades are flexible and in particular curved, so that they can deform elastically. With appropriate arrangement, these can allow for occurring, thermally induced strains of the ring segments automatic tracking of the sealing blades on the contact surfaces of the adjacent ring segments.
  • the sealing of said butt joint can be done reliably. by virtue of the one-sided attachment of the sealing lamellae is the assembly of the ring segments to ensure an arrangement in spite of the presence of the lamellar joint seal unchanged easily and quickly.
  • the respective sealing lamellae extend transversely to the flow direction of a working medium flowing in the turbine. As a result, an efficient reduction of the flow through the joints is achieved.
  • the respective sealing lamellae are at an angle of less than 90 ° from flat surfaces of the respective side wall sections or sealing side wall sections. This leads to a particularly suitable elastic deformability of the slats when two ring segments of the assembly are assembled during assembly, while the sealing blades biased reach the contact surfaces of the adjacent ring segment to concern. A compression of the sealing blades is thus avoided.
  • the aforementioned effect can be further improved if, according to a further advantageous embodiment, the sealing lamellae are arched towards their free end.
  • the sealing element is designed as a honeycomb construction.
  • the sealing element could also be configured as an abradable coating system with one or more layers applied to the first side surface.
  • the sealing blades are produced by means of an additive manufacturing process and connected to the sealing element.
  • the sealing element itself could be made by the same additive manufacturing process, which would reduce the cost and the manufacturing time.
  • FIG. 1 1 shows a schematic perspective view of a first exemplary embodiment of a ring segment 10 according to the invention, which can be assembled in a turbine with others thereof to a turbine guide vane carrier (not shown) around a gap between them and the rotor blades. to seal the said turbine as far as possible.
  • the ring segment 10 is substantially plate-shaped and rectangular in shape and comprises a corresponding wall 12, the first side surface 14 in the installed state, the blade tips of blades (not shown) facing.
  • the blades may be both freestanding, ie, deckless blades, and shroud blades.
  • the wall 12 has a second side surface 15 opposite the first side surface. This is in the installed state facing the (not shown) turbine vane carrier.
  • hooks could also be provided on the second side surface 15.
  • the side surface 14 is encompassed by a closed peripheral edge 16. Due to the rectangular shape of the wall 12, four side wall sections 16a-16d abut against the edge 16 with the side surface 14.
  • two side wall sections 16a and 16c as well as 16b and 16d are parallel to each other, wherein the pair of side wall sections 16b, 16d, when the ring segment 10 is installed in a turbine, is arranged parallel to the flow direction of the working medium of the turbine.
  • the side wall portions 16b, 16d could also be inclined to the flow direction of the working medium.
  • a sealing element 18 is arranged, which according to this exemplary embodiment as a honeycomb construction 19 (FIGS. Fig. 2 ) is configured.
  • the sealing element 18 comprises, in a manner analogous to the wall 12, four sealing side wall sections 18a-18d.
  • the respective sealing lamellae 20 protrude from flat surfaces of the sealing side wall sections 18b and side wall sections 16b at an angle ⁇ which may be less than 90 °. According to a first embodiment, the angle ⁇ can be 60 °. From their first end 20a they extend in a leaf spring-like manner curved to its free end 20b.
  • FIG. 2 shows a schematic representation of the plan view of two ring segments 10a, 10b designed according to FIG. 1 , during assembly to an assembly 22.
  • the honeycomb construction 19 is shown only schematically.
  • the two immediately adjacent ring segments 10a, 10b are moved towards each other during assembly according to one of the arrows M so that the sealing lamellae 20 of the first ring segment, in FIG. 2 as a ring segment 10a, on the side wall portion 18d of the adjacent ring segment, in FIG. 2 referred to as ring segment 10b, reach the concern.
  • the sealing blades 20 In the operating position, shown in FIG. 3 , the sealing blades 20 are elastically bent and then biased against the side wall portion 18d of the adjacent ring segment 10b.
  • FIG. 3 shows the two ring segments 10a, 10b in its operating position, in which the sealing blades 20 of the first ring segment 10a biased due to the small distance between the two ring segments 10a, 10b on the contact surface of the second ring segment 10b (sealing side wall portion 18d).
  • the arrow R indicates the direction of rotation of the blades with respect to the ring segments 10. It is advantageous if the direction of rotation, as far as possible, from the fixed end 20a of the sealing blades 20 is directed to its free end 20b.
  • FIG. 4 shows, it is possible that along the joint 24 successive sealing lamellae 20 are alternately secured to the participating ring segments 10a, 10b.
  • successive sealing lamellae 20 are alternately secured to the participating ring segments 10a, 10b.
  • the invention thus relates to a ring segment 10 for a turbine and an arrangement for sealing the gap between ring segments 10 and blade of a turbine, the ring segments comprising a plate-shaped wall 12, the first side surface 14, which in the installed state of the ring segments the blade tips of blades facing is encompassed by a closed circumferential edge 16 and in four side wall portions 16a - 16d divided and on the side surface 14 includes a full-surface arranged sealing element 18 includes.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
  • Sealing Devices (AREA)
EP16186537.3A 2016-08-31 2016-08-31 Segment annulaire de turbine et systeme destine a la delimitation exterieure d'un trajet d'ecoulement d'une turbine Withdrawn EP3290642A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP16186537.3A EP3290642A1 (fr) 2016-08-31 2016-08-31 Segment annulaire de turbine et systeme destine a la delimitation exterieure d'un trajet d'ecoulement d'une turbine
EP17755096.9A EP3472438B1 (fr) 2016-08-31 2017-08-08 Segment annulaire de turbine et système destiné à la délimitation extérieure d'un trajet d'écoulement d'une turbine
CN201780053057.XA CN109690025B (zh) 2016-08-31 2017-08-08 涡轮机的密封段、外部地限定涡轮机的流动路径的装置以及定子-转子密封装置
PCT/EP2017/070030 WO2018041555A1 (fr) 2016-08-31 2017-08-08 Segment d'étanchéité pour turbine, ensemble pour la délimitation extérieure d'un trajet d'écoulement ainsi que joint de stator et de rotor
JP2019532171A JP6941674B2 (ja) 2016-08-31 2017-08-08 タービンのためのシールセグメント、タービンの流路の外側の境界を定めるための組立体、およびステータ／ロータシール
US16/325,816 US11319826B2 (en) 2016-08-31 2017-08-08 Seal segment for a turbine, assembly for externally delimiting a flow path of a turbine, and stator/rotor seal

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16186537.3A EP3290642A1 (fr) 2016-08-31 2016-08-31 Segment annulaire de turbine et systeme destine a la delimitation exterieure d'un trajet d'ecoulement d'une turbine

Publications (1)

Publication Number Publication Date
EP3290642A1 true EP3290642A1 (fr) 2018-03-07

Family

ID=56851514

Family Applications (2)

Application Number Title Priority Date Filing Date
EP16186537.3A Withdrawn EP3290642A1 (fr) 2016-08-31 2016-08-31 Segment annulaire de turbine et systeme destine a la delimitation exterieure d'un trajet d'ecoulement d'une turbine
EP17755096.9A Active EP3472438B1 (fr) 2016-08-31 2017-08-08 Segment annulaire de turbine et système destiné à la délimitation extérieure d'un trajet d'écoulement d'une turbine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP17755096.9A Active EP3472438B1 (fr) 2016-08-31 2017-08-08 Segment annulaire de turbine et système destiné à la délimitation extérieure d'un trajet d'écoulement d'une turbine

Country Status (5)

Country Link
US (1) US11319826B2 (fr)
EP (2) EP3290642A1 (fr)
JP (1) JP6941674B2 (fr)
CN (1) CN109690025B (fr)
WO (1) WO2018041555A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3099788B1 (fr) * 2019-08-06 2021-09-03 Safran Aircraft Engines Abradable de turbine de turbomachine comprenant une face d’usure pourvue de redresseurs de flux

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008033897A1 (fr) * 2006-09-12 2008-03-20 Parker-Hannifin Corporation Ensemble joint
US20140271142A1 (en) * 2013-03-14 2014-09-18 General Electric Company Turbine Shroud with Spline Seal

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US5941685A (en) * 1997-10-14 1999-08-24 General Electric Company Brush seal for use on bumpy rotating surfaces
JP4342840B2 (ja) 2003-05-30 2009-10-14 株式会社東芝 蒸気タービン
CN2672289Y (zh) * 2004-01-15 2005-01-19 张延峰 弹性齿汽封
US8206092B2 (en) * 2007-12-05 2012-06-26 United Technologies Corp. Gas turbine engines and related systems involving blade outer air seals
FR2928961B1 (fr) 2008-03-19 2015-11-13 Snecma Distributeur sectorise pour une turbomachine.
US20090238683A1 (en) 2008-03-24 2009-09-24 United Technologies Corporation Vane with integral inner air seal
EP2174740A1 (fr) * 2008-10-08 2010-04-14 Siemens Aktiengesellschaft Joint en nids d'abeille et son procédé de production
US8753073B2 (en) * 2010-06-23 2014-06-17 General Electric Company Turbine shroud sealing apparatus
DE102012201050B4 (de) * 2012-01-25 2017-11-30 MTU Aero Engines AG Dichtungsanordnung, Verfahren sowie Strömungsmaschine
JP5920856B2 (ja) * 2012-01-26 2016-05-18 ゼネラル エレクトリック テクノロジー ゲゼルシャフト ミット ベシュレンクテル ハフツングＧｅｎｅｒａｌ Ｅｌｅｃｔｒｉｃ Ｔｅｃｈｎｏｌｏｇｙ ＧｍｂＨ ターボ機械用のセグメント化された内環を備えるステータ構成部材
FR2989724B1 (fr) 2012-04-20 2015-12-25 Snecma Etage de turbine pour une turbomachine
EP2787177B1 (fr) * 2013-04-02 2017-01-18 MTU Aero Engines AG Turbomachine axiale et procédé de montage
DE102013205883B4 (de) * 2013-04-03 2020-04-23 MTU Aero Engines AG Anordnung aus Leitschaufelsegmenten und Verfahren zur Herstellung einer derartigen Anordnung
FR3041993B1 (fr) 2015-10-05 2019-06-21 Safran Aircraft Engines Ensemble d'anneau de turbine avec maintien axial
US11131204B2 (en) * 2018-08-21 2021-09-28 General Electric Company Additively manufactured nested segment assemblies for turbine engines

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008033897A1 (fr) * 2006-09-12 2008-03-20 Parker-Hannifin Corporation Ensemble joint
US20140271142A1 (en) * 2013-03-14 2014-09-18 General Electric Company Turbine Shroud with Spline Seal

Also Published As

Publication number Publication date
CN109690025A (zh) 2019-04-26
US11319826B2 (en) 2022-05-03
EP3472438A1 (fr) 2019-04-24
CN109690025B (zh) 2022-04-22
JP2019528405A (ja) 2019-10-10
WO2018041555A1 (fr) 2018-03-08
US20210332712A1 (en) 2021-10-28
JP6941674B2 (ja) 2021-09-29
EP3472438B1 (fr) 2020-04-01

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