EP2603668A1 - Segment de couronne d'aubes, turbomachine et procédé de fabrication correspondant - Google Patents

Segment de couronne d'aubes, turbomachine et procédé de fabrication correspondant

Info

Publication number
EP2603668A1
EP2603668A1 EP11757240.4A EP11757240A EP2603668A1 EP 2603668 A1 EP2603668 A1 EP 2603668A1 EP 11757240 A EP11757240 A EP 11757240A EP 2603668 A1 EP2603668 A1 EP 2603668A1
Authority
EP
European Patent Office
Prior art keywords
blade
ring segment
head
blade ring
foot
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Withdrawn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
EP11757240.4A
Other languages
German (de)
English (en)
Inventor
Anton Wimmer
Frank Truckenmüller
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
Publication of EP2603668A1 publication Critical patent/EP2603668A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D5/34—Rotor-blade aggregates of unitary construction, e.g. formed of sheet laminae
    • 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
    • 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
    • F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking

Definitions

  • the invention relates to a blade ring segment, a Strö ⁇ tion machine and a method for their preparation.
  • a blade ring segment for a turbine is so Herge ⁇ provides that threaded a plurality of Einzelleitschaufeln in grooves in a housing of the turbine and then ver ⁇ are clamped.
  • disadvantageous ⁇ is, an entire blade ring or even a blade ring segment - not be able to produce before the actual installation of the vanes in the housing of the turbine - each with a variety of Leitschau ⁇ feln.
  • a blade rim segment for a Strömungsma ⁇ machine in particular a turbine, provided, comprising: a first blade and a second
  • a turbomachine in particular a turbine, is provided with the blade rim segment according to the invention.
  • a method for manufacturing a blade ring segment in particular the inventive blade ⁇ shroud segment and / or the fluid machine according to the invention is provided, wherein a first and a second blade are positively connected with each other.
  • the first blade to a positive ⁇ contour and the second blade has a negative contour, which engages in the positive contour-locking manner.
  • each of the blades has a positive and negative contours on opposite sides, so that a plurality of blades can be easily connected to each other. More preferably, the positive connection is detachable.
  • the positive contour and Ne ⁇ negative contour are formed such that the positive connection by means of a radial relative movement between the first and second ten shovel is produced.
  • the blade ring segment can be easily assembled.
  • “Radial” here means the main direction of extension of a particular blade.
  • the first blade has a first head and a first foot and the second blade on a two ⁇ th head and a second foot, wherein the first head is positively connected to the second head and / or the first foot with the second foot.
  • a first leaf is arranged, which is connected to the first head and the first foot.
  • the first sheet acts on the fluid flowing through the turbomachine. The same applies to the second leaf connecting the second head to the second foot.
  • the negative contour is formed radially outward on the second head and / or second foot and the positive contour radially outward on the first head and / or first foot, wherein preferably also the negative contour radially open for engagement of the positive contour is trained.
  • radially outward refers to a radius starting from an intersection between two imaginary lines which extend along the main extension directions of the first and second blades. In a later use of the vane ring segment in a turbomachine, said intersection coincides with the rotor axis.
  • a connecting element is seen ⁇ before, which engages on the one hand in the first blade and the other hander ⁇ in the second blade in a form-fitting manner in order to connect them.
  • Connecting element provided, which engages in negative contours in the first and second Schaute1, wherein the connecting element preferably engages in the first and second head and / or in the first and second foot.
  • the connecting element is arranged in a negative contour radially outward in the first head and / or first foot and in a negative contour radially outward in the second head and / or first foot.
  • the connecting element is dovetail-shaped or H-shaped or has a cross section which is composed of two on / on set circles.
  • a cohesive connection is also provided, which connects the first blade with the second blade.
  • the cohesive connection is in particular a weld.
  • another positive connection is conceivable which ensures an additional form fit between the first and second blades.
  • blades may be provided which form a blade ring segment.
  • FIG. 1 m a perspective view of a blade of a blade ring segment according to an exemplary embodiment of the present invention
  • FIG. 2 is a perspective view of a vane segment according to an embodiment of the present invention having a plurality of the blades shown in FIG. 1;
  • FIG. 1 a perspective view of a blade of a blade ring segment according to an exemplary embodiment of the present invention
  • FIG. 2 is a perspective view of a vane segment according to an embodiment of the present invention having a plurality of the blades shown in FIG. 1;
  • FIG. 1 a perspective view of a blade of a blade ring segment according to an exemplary embodiment of the present invention
  • FIG. 2 is a perspective view of a vane segment according to an embodiment of the present invention having a plurality of the blades shown in FIG. 1;
  • FIG. 1 a perspective view of a blade of a blade ring segment according to an exemplary embodiment of the present invention
  • FIG. 2 is a perspective view of a vane segment according
  • FIG. 3 is an exploded view of a Schaufelkranzseg ⁇ ment according to another embodiment of the present invention; in perspective, a connecting element according to another embodiment of the present invention; in perspective, a still further croqusele ⁇ ment according to a further embodiment of the invention; and in a perspective view of the blade rim segment of Fig. 3, wherein the connection ⁇ elements are inserted into their respective negative contours.
  • Fig. 1 shows in a perspective view a blade 1 from a blade ring segment 2, see Fig. 2, according to an embodiment of the present invention.
  • the blade 1 is composed of a head 3, a foot 4 and a sheet 5 connecting them.
  • the head 3 has on its one side 6 a dovetail-shaped negative contour 7 (ie a recess). On its other side 11, the head 3 has a positive contour 12 (ie, a projection). Accordingly, the foot 4 has on its one side 13 a negative contour 14 and on its other side 15 a positive contour 16.
  • the negative contour 7 is formed in the head 3 radially outside and open. "Radially outward” here refers to the main extension direction H of the blade 1, starting from the center axis M shown in FIG. 2. In other words, the negative contour 7 is open on the side 8 of the head 3 facing away from the blade 5. Accordingly, the negative contour 14 is formed in the foot 4 open radially outward. After radially inward, the negative contours 7 and 14 are each formed closed.
  • the blade 1 is in particular a Leit ⁇ shovel.
  • the blade 1 can be formed from steel, titanium or a Ke ⁇ ramik.
  • Fig. 2 shows the blade ring segment 2 in a perspective view.
  • the blade ring segment 2 is composed of a multiplicity of the blades 1 shown in FIG. 1, three of the blades being designated 1, 1 'or 1 "for better explanation.
  • the blades 1, 1 ', 1' ' are arranged in the circumferential direction U about the central axis M.
  • the central axis M coincides with the intersection between the main directions of extension H, H ', H' 'of the blades 1, 1' and 1 '' together.
  • the central axis M corresponds to the central axis of the rotor, not shown, after installation of the blade ring segment 2 in a turbine 17, which is indicated only schematically in FIG. 2.
  • the blade ring segment 2 In order to form the blade ring segment 2, the
  • Blades 1, 1 ', 1'' positively connected to each other. This happens because, as explained below for the show ⁇ blades 1 and 1 ', the positive contour 12 of the blade. 1 with the negative contour 7 'of the blade 1' and the positive contour 16 of the blade 1 with the negative contour 14 'of the blade 1' is brought into engagement. This happens because the blade 1 is moved radially inward in the illustrated arrow direction.
  • the blades 1, 1 ', 1'' together by means of welds 21, 21' firmly connected.
  • the welds 21, 21 ' connect two heads 3, 3' and 3 ', 3''with each other.
  • the feet 4, 4 ', 4''of the blades 1, 1', 1 '' can also be connected by means of welds 22, 22 '.
  • the welds 21, 21 ', 22, 22' provide a permanent connection between the blades 1, 1 ', 1''.
  • it is also conceivable instead of the welds provide other material fit or form-fit or force-fit Verbin ⁇ applications.
  • Fig. 3 shows an exploded view of a Schaufelkranzseg ⁇ element 2 'in accordance with another embodiment of the constricting vorlie ⁇ invention.
  • FIG. 3 differs from that according to FIGS. 1 and 2 only in that a different type of connection between the blades 1, 1 ', 1''is provided, as described below with reference to the blades 1, 1' ⁇ her explained.
  • the heads 3, 3 'as well as the feet 4, 4' of the blades 1, 1 ' have on their opposite sides 6', 11 'and 13', 15 'in each case a negative contour 25' or 26 '.
  • a connecting element is inserted 27, which 'form-fitting buildin ⁇ Untitled the heads 3 and 3 to each other.
  • the connecting element 27 is pushed radially from the outside inwards into the negative recesses 25, 26 '.
  • the connecting element 27, 28 is composed of two opposite dovetails 31, 32.
  • the connecting element 27, 28 may also be formed as shown in FIG. 4. Accordingly, the connecting element 27 has a cross section which is composed of two successive (imaginary) circles 33, 34.
  • the connecting element 27, 28 is H-shaped, as shown in Fig. 5.
  • connecting elements 27, 28 are also possible to form the connecting elements 27, 28 of a different material than the blades 1, 1 ', 1' '.
  • the connecting elements 27, 28 may be formed of a damping material to dampen vibrations between the blades 1, 1 ', 1' '.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un segment de couronne d'aubes (2, 2') pour une turbomachine (17), notamment une turbine, comportant une première aube (1) et une deuxième aube (1'), la première aube (1) étant assemblée avec la deuxième aube (1') par complémentarité de forme.
EP11757240.4A 2010-09-30 2011-09-05 Segment de couronne d'aubes, turbomachine et procédé de fabrication correspondant Withdrawn EP2603668A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102010041808.0A DE102010041808B4 (de) 2010-09-30 2010-09-30 Schaufelkranzsegment, Strömungsmaschine sowie Verfahren zu deren Herstellung
PCT/EP2011/065289 WO2012041651A1 (fr) 2010-09-30 2011-09-05 Segment de couronne d'aubes, turbomachine et procédé de fabrication correspondant

Publications (1)

Publication Number Publication Date
EP2603668A1 true EP2603668A1 (fr) 2013-06-19

Family

ID=44651725

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11757240.4A Withdrawn EP2603668A1 (fr) 2010-09-30 2011-09-05 Segment de couronne d'aubes, turbomachine et procédé de fabrication correspondant

Country Status (4)

Country Link
EP (1) EP2603668A1 (fr)
CN (1) CN103119249A (fr)
DE (1) DE102010041808B4 (fr)
WO (1) WO2012041651A1 (fr)

Families Citing this family (15)

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EP2666969B1 (fr) * 2012-05-21 2017-04-19 General Electric Technology GmbH Structure de diaphragme de turbine
EP2669477B1 (fr) * 2012-05-31 2017-04-05 General Electric Technology GmbH Carénage pour aubes
ITCO20130004A1 (it) 2013-02-20 2014-08-21 Nuovo Pignone Srl Metodo per realizzare una girante da segmenti a settore
EP2995775A1 (fr) * 2014-09-15 2016-03-16 Siemens Aktiengesellschaft Dispositif destiné à enfoncer une aube directrice dans une rainure d'aube
RU2700313C2 (ru) 2014-11-03 2019-09-16 Нуово Пиньоне СРЛ Сектор для сборки ступени турбины и соответствующий способ изготовления
US9777594B2 (en) * 2015-04-15 2017-10-03 Siemens Energy, Inc. Energy damping system for gas turbine engine stationary vane
JP6546053B2 (ja) * 2015-09-18 2019-07-17 株式会社東芝 組立式ノズルダイヤフラム及び蒸気タービン
US10113438B2 (en) 2016-02-18 2018-10-30 United Technologies Corporation Stator vane shiplap seal assembly
JP6689117B2 (ja) * 2016-03-31 2020-04-28 三菱日立パワーシステムズ株式会社 軸流回転機械に装備される静翼環及び軸流回転機械
DE102016113912A1 (de) * 2016-07-28 2018-02-01 Man Diesel & Turbo Se Leitschaufelanordnung einer Strömungsmaschine
DE102018210601A1 (de) 2018-06-28 2020-01-02 MTU Aero Engines AG Segmentring zur montage in einer strömungsmaschine
DE102018210600A1 (de) 2018-06-28 2020-01-02 MTU Aero Engines AG Mantelringanordnung für eine strömungsmaschine
US10738634B2 (en) * 2018-07-19 2020-08-11 Raytheon Technologies Corporation Contact coupled singlets
FR3129685A1 (fr) * 2021-11-29 2023-06-02 Safran Aircraft Engines Aube de moteur d’aéronef comprenant un talon avec un assemblage en puzzle
FR3137120A1 (fr) * 2022-06-22 2023-12-29 Safran Aircraft Engines Ensemble aubagé de turbomachine comportant des moyens de limitations de vibrations entre plateformes

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Also Published As

Publication number Publication date
CN103119249A (zh) 2013-05-22
DE102010041808A1 (de) 2012-04-05
WO2012041651A1 (fr) 2012-04-05
DE102010041808B4 (de) 2014-10-23

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