EP2376746B1 - Plateforme d'extrémité d' aube - Google Patents

Plateforme d'extrémité d' aube Download PDF

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Publication number
EP2376746B1
EP2376746B1 EP10740504.5A EP10740504A EP2376746B1 EP 2376746 B1 EP2376746 B1 EP 2376746B1 EP 10740504 A EP10740504 A EP 10740504A EP 2376746 B1 EP2376746 B1 EP 2376746B1
Authority
EP
European Patent Office
Prior art keywords
shroud segment
stiffening structure
shroud
rib
blade
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
EP10740504.5A
Other languages
German (de)
English (en)
Other versions
EP2376746A2 (fr
Inventor
Markus Schlemmer
Bartlomiej Pikul
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
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Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to PL10740504T priority Critical patent/PL2376746T3/pl
Publication of EP2376746A2 publication Critical patent/EP2376746A2/fr
Application granted granted Critical
Publication of EP2376746B1 publication Critical patent/EP2376746B1/fr
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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
    • 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
    • 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
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade

Definitions

  • the invention relates to a shroud segment of a blade, in particular a gas turbine blade, according to the preamble of claim 1.
  • the invention further relates to a turbomachine, in particular a thermal gas turbine, the type specified in the preamble of claim 11.
  • shroud segment is already known from the prior art.
  • the shroud segment which is arranged at a radial end region of the blade, basically serves for damping blade vibrations and is used in particular for gas turbine blades for rear turbine stages. Furthermore, the shroud segment reduces the flow around the blade tip and thereby increases the efficiency of an associated turbomachine.
  • the shroud segments of adjacent blades of a rotor thereby form a continuous shroud.
  • known shroud segments have a stiffening structure which is raised in relation to a shroud segment surface and which is usually designed as a so-called "dogbone” or "half dogbone".
  • a disadvantage of the known shroud segments is the fact that they have to be made relatively bulky in order to enable a sufficient reduction of stress concentrations. As a result, the total weight of the shroud segment and a blade provided with this considerably increases. This also leads during operation of the blade in an associated turbomachine to high moving masses.
  • a vane or vane segment for a gas turbine with an airfoil and a shroud is known.
  • Object of the present invention is to provide a shroud segment, which allows weight reduction with good voltage reduction. It is another object of the present invention to provide a turbomachine with a rotor.
  • the stiffening structure is designed to be cross-shaped at least in some areas.
  • the cross-shaped design can significantly reduce the stress concentration in the shroud segment and improve the stiffness of the shroud segment while optimizing weight.
  • the stiffening structure of the shroud segment according to the invention comprises at least two ribs arranged in a cross shape, the main axes of which are at a predetermined angle to each other. This allows a simple and targeted adjustment of the voltage level within the shroud segment, whereby different shroud segment types can be considered individually. It can be provided, for example, that the respective angle is determined as a function of the respective shroud segment geometry, of the shroud segment material and of the subsequent conditions of use in an associated turbomachine.
  • stiffening structure comprising at least one rib which is arranged along and / or perpendicular to a stress line of the shroud segment.
  • the stiffening structure comprises at least one rib which has a constant and / or location-dependent height over its length extension in the profile.
  • one or more ribs of the stiffening structure have over their respective longitudinal extent a uniform and / or over their respective longitudinal extent varying height profile, whereby a particularly precise adaptability of the stiffening structure to the respective configuration of the shroud segment and the individual course of the voltage lines is given within the shroud segment.
  • the stiffening structure comprises at least one rib, which has a cross-sectional profile over its longitudinal extent, which is selected as a function of a tension profile of the shroud segment without this rib.
  • the cross-sectional profile of the at least one rib is formed along its length in consideration of a stress profile that would have the shroud segment without this rib.
  • the at least one rib in regions of potentially high stresses may have a thickened cross-sectional profile exhibit.
  • a correspondingly reduced cross-sectional profile can be provided. As a result, a maximum reduction in stress can be generated with minimal additional weight of the shroud segment.
  • the stiffening structure comprises rounded surface transitions to the shroud segment surface, as this reliably prevents the occurrence of force peaks at the edges of the stiffening structure, for example under tensile or bending loads of the shroud segment.
  • a particularly high stiffness of the shroud segment with optimized weight is given by the fact that the stiffening structure of the shroud segment according to the invention laterally delimits at least one discrete shroud segment surface area.
  • the shroud segment has a recess formed by the raised stiffening structure.
  • a particularly uniform force and stress distribution over the shroud segment is achieved in a further embodiment in that the stiffening structure laterally delimits four and / or six discrete shroud segment surface areas.
  • the shroud segment has two oppositely arranged and in longitudinal section substantially Z-shaped contact surfaces for attaching corresponding contact surfaces of two other shroud segments.
  • the stiffening structure comprises at least one rib which extends between the two contact surfaces. It can be provided in particular that the rib extends between mutually corresponding corner regions of the two Z-shaped contact surfaces, since at these corners usually particularly large stress concentrations can occur.
  • a blade in particular a gas turbine blade, for a turbomachine having a shroud segment disposed at a radial end portion of the blade has a stiffening structure raised from a shroud segment surface.
  • a reduction in weight of the blade while at the same time a good reduction in stress is made possible in that the stiffening structure is at least partially cross-shaped.
  • the cross-shaped design can significantly reduce the stress concentration in the shroud segment and improve the stiffness of the shroud segment while optimizing weight.
  • a particularly high mechanical stability and load capacity of the blade is achieved in a further embodiment, characterized in that the shroud segment is formed integrally with the blade.
  • the shroud segment and the blade can basically also be formed in two or more parts and joined in a suitable manner, in the case of a one-piece design, the otherwise necessary assembly step can be dispensed with, which results in corresponding cost reductions.
  • a further aspect of the invention relates to a turbomachine, in particular a thermal gas turbine, having a rotor, which comprises at least one rotor blade with a shroud segment arranged on a radial end region of the rotor blade, wherein the shroud segment has a stiffening structure raised from a shroud segment surface.
  • a reduction in weight of the at least one moving blade with simultaneously good stress reduction is made possible by the fact that the shroud segment and / or the moving blade is designed according to one of the preceding embodiments.
  • the weight of the rotor or the entire turbomachine is optimized while simultaneously improving their load capacity, which can be extended maintenance cycles realize accordingly.
  • all shroud segments and / or blades of the rotor according to one of the preceding embodiments are designed to achieve maximum weight and stress reduction.
  • the moving mass is thereby reduced accordingly during operation of the turbomachine, resulting in further advantages, in particular with regard to fuel savings.
  • Fig. 1 shows a schematic plan view of a known from the prior art shroud segment 10 for placement on a blade 12 (s. Fig. 3
  • the shroud segment 10 has a stiffening structure 16 which is raised in relation to a shroud segment surface 14 and which, as can be seen from the plan view, is substantially bone-shaped and is therefore referred to as "dogbone”.
  • Fig. 2 shows a schematic plan view of a known from the prior art shroud segment 10 for placement on a blade 12 (s. Fig. 3 ) and a side sectional view of the shroud segment 10 along the section line II.
  • the shroud segment 10 has in comparison to in Fig. 1 Shroud segment 10 shown an alternative stiffening structure 16, which flattened to one side and is therefore referred to as "Half-Dogbone".
  • the shroud segments 10 shown have the disadvantage that their stiffening structures 16 have to be comparatively bulky in order to be able to ensure a sufficient reduction of the stress concentrations in the shroud segment 10. This increases the weight of the shroud segments 10 as well as a blade 12 connected to such a shroud segment 10.
  • Fig. 3 shows a schematic perspective view of a designed as a gas turbine blade for a turbomachine blade 12 with a shroud segment 20 according to the invention, which has a stiffening structure 22 according to a first embodiment.
  • the stiffening structure 22 is also raised in relation to a shroud segment surface 24 of the shroud segment 20, but in contrast to the in Fig. 1 and 2 shown embodiments partially formed cross-shaped.
  • the cross-shaped design, the stress concentration in the shroud segment 20 can be significantly reduced and the rigidity of the shroud segment 20 can be significantly improved with simultaneous weight optimization.
  • the stiffening structure 22 comprises two ribs 26 which are arranged in a cruciform manner and whose principal axes H1, H2 are at a predetermined angle ⁇ relative to one another and which have a constant height over their lengthwise extension in the profile.
  • the two ribs 26 are arranged along or perpendicular to stress lines of the shroud segment 20.
  • a particularly efficient reduction of the voltage level of the shroud segment 20 is achieved.
  • the angle ⁇ and the profile profile of the ribs 26, in particular their height must be determined individually for each type of shroud segment depending on the respective stress lines that would occur without the stiffening structure 22.
  • the shroud segment 20 furthermore has two contact surfaces 28 (Z-Shroud) which are arranged opposite each other and are substantially Z-shaped in longitudinal section for attaching corresponding contact surfaces of two further shroud segments (not shown).
  • One of the ribs 26 extends between corners III of the two Z-shaped contact surfaces 28, whereby a particularly high voltage reduction in otherwise heavily stress-loaded areas of the shroud segment 20 is achieved.
  • the stiffening structure 22 is formed to laterally bound four discrete shroud segment surface areas 24. In other words, the shroud segment surface areas 24 form the bottom surfaces of four depressions, while the stiffening structure 22 and its ribs 26 form the sidewalls of the depressions.
  • the stiffening structure 22 can basically be produced by separation processes from a shroud segment blank.
  • the shroud segment 20 - possibly in one piece with a blade 12 - by means of casting, in particular investment casting process, or generative process can be produced.
  • Fig. 4 shows a schematic perspective view of a blade 12 with a shroud segment 20 according to the invention, which has a stiffening structure 22 according to a second embodiment.
  • Fig. 4 is described below in synopsis with Fig. 5 which is a schematic, partial and transparent perspective of the supervision in Fig. 4 shown blade 12 shows.
  • the stiffening structure 22 comprises three ribs 26a-c, which are each arranged in pairs in a cross shape and likewise extend along or perpendicular to stress lines of the shroud segment 20.
  • the angle ⁇ between the major axis H (not shown) of the rib 26c and the major axis H of the rib 26a and the angle ⁇ between the major axis H of the rib 26c and the major axis H of the rib 26b are set equal in the present case, so that the major axes H of the Ridges 26a, 26b parallel to each other. Due to the additional rib 26b, the stiffening structure 22 now limits six discrete shroud segment surface areas 24 laterally.
  • FIG. 1 shows a schematic and partially sectioned wire grid view of a rear side of a rotor blade 12 according to the invention, which is formed integrally with a shroud segment 20.
  • the shroud segment 20 in turn has a stiffening structure 22 according to a third embodiment.
  • the stiffening structure 22 comprises, as in the first embodiment, two cross-shaped ribs 26.
  • the ribs 26 are also along or perpendicular to stress lines of the shroud segment 20 arranged, wherein only one of the ribs 26 can be seen.
  • the angle ⁇ between the main axes H of the ribs 26 and height or the profile profile of the ribs 26 is in turn selected in dependence on the voltage level of the shroud segment without these ribs 26.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (11)

  1. Segment de bandage (20) d'une pale (12), en particulier d'une pale de turbine à gaz, comprenant une structure de renfort (22) en relief vis-à-vis d'une surface de segment de bandage (24), dans lequel la structure de renfort (22) est conçue au moins par zones de façon cruciforme et la structure de renfort (22) comprend au moins deux nervures (26) agencées de façon cruciforme, dont les axes principaux (H) sont disposés mutuellement en formant un angle prédéterminé (α) pour régler un niveau de tension à l'intérieur du segment de bandage (20), caractérisé en ce que la structure de renfort (22) délimite latéralement au moins une zone discrète (24) de la surface de segment de bandage, dans lequel une cavité est formée par la délimitation latérale de la structure de renfort (22).
  2. Segment de bandage (20) selon la revendication 1, caractérisé en ce que les axes principaux (H) des nervures (26) sont disposés en formant mutuellement un angle (α) entre 20° et 90°.
  3. Segment de bandage (20) selon l'une quelconque des revendications 1 ou 2, caractérisé en ce que la structure de renfort (22) comprend au moins une nervure (26) qui est agencée le long d'une ligne de tension du segment de bandage (20) et/ou perpendiculairement à celle-ci.
  4. Segment de bandage (20) selon l'une quelconque des revendications 1 à 3, caractérisé en ce que la structure de renfort (22) comprend une nervure (26) qui présente sur son extension longitudinale en profil une hauteur constante et/ou dépendant de l'emplacement.
  5. Segment de bandage (20) selon la revendication 4, caractérisé en ce que la au moins une nervure (26) présente une hauteur entre 0,1 cm et 10 cm.
  6. Segment de bandage (20) selon l'une quelconque des revendications 1 à 5, caractérisé en ce que la structure de renfort (22) comprend au moins une nervure (26) qui présente sur son extension longitudinale un profil en coupe transversale qui est sélectionné en fonction d'un profil de tension du segment de bandage (20) sans cette nervure (26).
  7. Segment de bandage (20) selon l'une quelconque des revendications 1 à 6, caractérisé en ce que la structure de renfort (22) comprend des transitions de surface arrondies avec la surface de segment de bandage (24).
  8. Segment de bandage (20) selon l'une quelconque des revendications 1 à 7, caractérisé en ce que la structure de renfort (22) délimite latéralement quatre et/ou six zones discrètes de surface de segment de bandage (24).
  9. Segment de bandage (20) selon l'une quelconque des revendications 1 à 8, caractérisé en ce que celui-ci présente deux surfaces de contact (28) agencées en regard l'une de l'autre et sensiblement en forme de Z en coupe longitudinale pour s'appuyer sur des surfaces de contact correspondantes (28) de deux autres segments de bandage (20).
  10. Segment de bandage (20) selon la revendication, caractérisé en ce que la structure de renfort (22) comprend au moins une nervure (26) qui s'étend entre les deux surfaces de contact (28).
  11. Turbomachine, en particulier turbine à gaz thermique, comprenant un rotor qui comprend au moins une pale (12) avec un segment de bandage (20) agencé dans une zone d'extrémité radiale de la pale (12), dans laquelle le segment de bandage (20) présente une structure de renfort (22) en relief vis-à-vis d'une surface de segment de bandage (24), caractérisé en ce que le segment de bandage (20) est conçu selon l'une quelconque des revendications 1 à 10.
EP10740504.5A 2009-06-26 2010-06-21 Plateforme d'extrémité d' aube Active EP2376746B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL10740504T PL2376746T3 (pl) 2009-06-26 2010-06-21 Segment bandażu łopatki

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009030566A DE102009030566A1 (de) 2009-06-26 2009-06-26 Deckbandsegment zur Anordnung an einer Schaufel
PCT/DE2010/000707 WO2010149139A2 (fr) 2009-06-26 2010-06-21 Segment de bande de recouvrement à placer sur une aube

Publications (2)

Publication Number Publication Date
EP2376746A2 EP2376746A2 (fr) 2011-10-19
EP2376746B1 true EP2376746B1 (fr) 2017-08-09

Family

ID=43217870

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10740504.5A Active EP2376746B1 (fr) 2009-06-26 2010-06-21 Plateforme d'extrémité d' aube

Country Status (6)

Country Link
US (1) US9322281B2 (fr)
EP (1) EP2376746B1 (fr)
DE (1) DE102009030566A1 (fr)
ES (1) ES2638450T3 (fr)
PL (1) PL2376746T3 (fr)
WO (1) WO2010149139A2 (fr)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2578801B1 (fr) 2011-10-07 2021-04-07 MTU Aero Engines GmbH Talons d'aube pour une turbomachine
PL2615243T3 (pl) * 2012-01-11 2017-12-29 MTU Aero Engines AG Segment wieńca łopatkowego do maszyny przepływowej i sposób jego wytwarzania
US9683446B2 (en) * 2013-03-07 2017-06-20 Rolls-Royce Energy Systems, Inc. Gas turbine engine shrouded blade
DE102013224199A1 (de) * 2013-11-27 2015-05-28 MTU Aero Engines AG Gasturbinen-Laufschaufel
US9556741B2 (en) * 2014-02-13 2017-01-31 Pratt & Whitney Canada Corp Shrouded blade for a gas turbine engine
EP3034790B1 (fr) * 2014-12-16 2020-06-24 Ansaldo Energia Switzerland AG Aube rotative pour une turbine à gaz
EP3056677B1 (fr) 2015-02-12 2019-09-04 MTU Aero Engines GmbH Aube et turbomachine
CN107709707B (zh) * 2015-06-29 2019-08-27 西门子公司 带罩涡轮机叶片
US10526899B2 (en) 2017-02-14 2020-01-07 General Electric Company Turbine blade having a tip shroud
US10400610B2 (en) * 2017-02-14 2019-09-03 General Electric Company Turbine blade having a tip shroud notch
DE102018200964A1 (de) * 2018-01-23 2019-07-25 MTU Aero Engines AG Rotorschaufeldeckband für eine Strömungsmaschine, Rotorschaufel, Verfahren zum Herstellen eines Rotorschaufeldeckbands und einer Rotorschaufel
DE102018201265A1 (de) * 2018-01-29 2019-08-01 MTU Aero Engines AG Deckbandsegment zur Anordnung an einer Schaufel einer Strömungsmaschine und Schaufel
US10876416B2 (en) 2018-07-27 2020-12-29 Pratt & Whitney Canada Corp. Vane segment with ribs
DE102018215728A1 (de) 2018-09-17 2020-03-19 MTU Aero Engines AG Gasturbinen-Laufschaufel
US11053804B2 (en) * 2019-05-08 2021-07-06 Pratt & Whitney Canada Corp. Shroud interlock
EP3865665A1 (fr) 2020-02-11 2021-08-18 MTU Aero Engines AG Pale pour turbomachine avec un carénage

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GB2290833B (en) 1994-07-02 1998-08-05 Rolls Royce Plc Turbine blade
US5785496A (en) 1997-02-24 1998-07-28 Mitsubishi Heavy Industries, Ltd. Gas turbine rotor
JPH1150806A (ja) * 1997-08-04 1999-02-23 Ishikawajima Harima Heavy Ind Co Ltd ガスタービンのノズル部材
US6491498B1 (en) * 2001-10-04 2002-12-10 Power Systems Mfg, Llc. Turbine blade pocket shroud
EP1413712A1 (fr) * 2002-10-21 2004-04-28 Siemens Aktiengesellschaft Virole pour une turbine avec joint d'extrémité
DE10331599A1 (de) * 2003-07-11 2005-02-03 Mtu Aero Engines Gmbh Bauteil für eine Gasturbine sowie Verfahren zur Herstellung desselben
US7527477B2 (en) * 2006-07-31 2009-05-05 General Electric Company Rotor blade and method of fabricating same
US20090097979A1 (en) * 2007-07-31 2009-04-16 Omer Duane Erdmann Rotor blade
ES2698368T3 (es) * 2010-07-01 2019-02-04 MTU Aero Engines AG Pala de turbina con cubierta de punta

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Also Published As

Publication number Publication date
ES2638450T3 (es) 2017-10-20
WO2010149139A3 (fr) 2011-07-21
PL2376746T3 (pl) 2017-11-30
WO2010149139A2 (fr) 2010-12-29
EP2376746A2 (fr) 2011-10-19
DE102009030566A1 (de) 2010-12-30
US20120107123A1 (en) 2012-05-03
US9322281B2 (en) 2016-04-26

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