EP2376746A2 - Segment de bande de recouvrement à placer sur une aube - Google Patents

Segment de bande de recouvrement à placer sur une aube

Info

Publication number
EP2376746A2
EP2376746A2 EP10740504A EP10740504A EP2376746A2 EP 2376746 A2 EP2376746 A2 EP 2376746A2 EP 10740504 A EP10740504 A EP 10740504A EP 10740504 A EP10740504 A EP 10740504A EP 2376746 A2 EP2376746 A2 EP 2376746A2
Authority
EP
European Patent Office
Prior art keywords
shroud segment
blade
stiffening structure
shroud
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.)
Granted
Application number
EP10740504A
Other languages
German (de)
English (en)
Other versions
EP2376746B1 (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 GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
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
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • 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 according to the preamble of patent claim 1 for placement on a blade, in particular a gas turbine blade.
  • the invention further relates to a blade, in particular a gas turbine blade, the type specified in the preamble of claim 13 for a turbomachine.
  • a shroud segment and a blade with such a shroud segment are 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 5 of the blade tip and thereby increases the efficiency of an associated turbomachine.
  • 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 o "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. This considerably increases the total weight of the shroud segment as well as a blade provided therewith. This also leads during operation of the blade in an associated turbomachine to high moving masses.
  • the object of the present invention is to provide a shroud segment as well as a shovel provided with such a shroud segment, which enable a reduction in weight while at the same time providing good stress reduction.
  • the object is achieved by a shroud segment with the features of claim 1 and by a blade having the features of claim 13.
  • Advantageous embodiments with expedient developments of the invention 5 are specified in the respective subclaims, wherein advantageous embodiments of the shroud segment are to be regarded as advantageous embodiments of the blade and vice versa.
  • the stiffening structure is formed at least in regions in a cross-shaped manner.
  • the cross-shaped design can significantly reduce the stress concentration in the shroud segment and improve the stiffness of the shroud with simultaneous weight optimization.
  • the stiffening structure comprises at least two ribs arranged in the shape of a cross whose main axes are at a predetermined angle to one another. This allows a simple and targeted adjustment of the voltage level within the shroud segment, whereby different shroud segment types can be considered individually.
  • the particular angle is determined as a function of the particular shroud segment geometry, the shroud segment material and the subsequent operating conditions in an associated turbomachine.
  • stiffening structure encompassing at least one rib, which extends along and / or perpendicular to a tension line of the shroud segment is arranged.
  • stiffness achieved in the shroud segment a particularly low stress level is achieved within the shroud segment.
  • the stiffening structure comprises at least one rib, which has a constant and / or location-dependent height over its longitudinal extent in the profile.
  • one or more ribs of the stiffening structure have over their respective longitudinal extent a uniform and / or an over their respective longitudinal extent varying height profile, whereby a particularly precise adaptability of the stiffening structure to the j egard embodiment of the shroud segment and the individual course of the Stress lines is given within the shroud segment.
  • Optimal adaptability of the shroud segment in terms of minimum weight with maximum reduction in stress is made possible in a further advantageous embodiment 5 of the invention in that the at least one rib has a height between 0.1 cm and 10 cm.
  • 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 may have a thickened cross-sectional profile in areas of potentially high stresses. Conversely, in areas with potentially low voltage, 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.
  • a particularly high stiffness of the shroud with optimized weight is given in a further embodiment in that the stiffening structure 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 further shroud segments.
  • a particularly high rigidity is achieved in a further embodiment in that 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 o.
  • a further aspect of the invention relates to a blade, in particular a gas turbine blade, for a turbomachine, with a shroud segment arranged on a radial end region of the blade, which has a stiffening structure which is raised in relation to a shroud segment surface.
  • 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 with simultaneous weight optimization.
  • a particularly high mechanical stability and load capacity of the blade is achieved in a further embodiment in that the shroud segment is formed integrally with the blade.
  • the shroud segment and the blade can in principle also be formed in two or more parts and joined together 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 blade with a shroud segment arranged on a radial end region of the blade, wherein the shroud segment has a stiffening structure which is raised in relation to a shroud segment surface.
  • a weight reduction of the at least one blade with simultaneously good stress reduction is made possible by the fact that the shroud segment and / or the blade is designed in accordance with one of the preceding exemplary 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 Ie shroud segments and / or blades of the rotor designed to achieve a maximum weight and stress reduction.
  • the moving mass is reduced accordingly during operation of the turbomachine, resulting in further advantages, in particular with regard to 5 fuel savings.
  • Figure 1 is a schematic plan view and a side sectional view of a known from the prior art shroud segment with a stiffening structure.
  • Fig. 2 is a schematic plan view and a side sectional view of one of
  • FIG. 3 shows a schematic perspective view of a blade with a shroud segment according to the invention, which has a stiffening structure according to a first exemplary embodiment
  • FIG. 4 shows a schematic perspective view of a blade with a shroud segment according to the invention, which has a stiffening structure according to a second exemplary embodiment
  • Fig. 5 is a schematic, fragmentary and transparent perspective view of the blade shown in Fig. 4; and 6 shows a schematic and partial wire grid view of a rear side of a blade according to the invention with a shroud segment, which has a stiffening structure according to a third embodiment.
  • FIG. 1 shows a schematic plan view of a shroud segment 10 known from the prior art for arrangement on a blade 12 (see FIG. 3) and a lateral sectional view of the shroud segment 10 along the section line I-I.
  • 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 top view, is substantially bone-shaped and is therefore referred to as a "dogbone".
  • FIG. 2 shows a schematic plan view of a shroud segment 10 known from the prior art for arrangement on a blade 12 (see FIG. 3) and a lateral sectional view of the shroud segment 10 along the section line I-I.
  • the shroud segment 10 has an alternative stiffening structure 16, which flattens off to one side and is therefore referred to as "half-dogbone".
  • the two shroud segments 10 shown in FIG. 1 and FIG. 2 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 and a blade 12 connected to such a shroud segment 10.
  • FIG. 3 shows a schematic perspective view of a blade 12 designed as a gas turbine blade for a turbomachine with a shroud segment 20 according to the invention, which has a stiffening structure 22 according to a first exemplary embodiment.
  • the stiffening structure 22 is likewise raised in relation to a shroud segment surface 24 of the shroud segment 20, but in contrast to the embodiments shown in FIGS.
  • the stiffening structure 22 comprises two ribs 26 which are arranged in a cruciform manner and whose main 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 one another and are substantially Z-shaped in longitudinal section for attaching corresponding contact surfaces of two further shroud segments (not shown).
  • Z-Shroud two contact surfaces 28
  • one of the ribs 26 extends between corners III of the two Z-shaped contact surfaces 28, as a result of which a particularly high reduction in stress is achieved in other areas of the shroud segment 20 that are subject to high stress.
  • the stiffening structure 22 is formed to laterally bound four discrete shroud segment surface areas 24.
  • the shroud segment surface areas 24 form the bottom surfaces of four indentations, while the stiffening structure 22 and its ribs 26 form the sidewalls of the indentations.
  • the stiffening structure 22 can basically be produced by separation processes from a shroud segment blank. Alternatively, the shroud segment 20 - if appropriate, in one piece with a blade 12 - by means of casting, in particular investment casting process, or generative process can be produced.
  • 4 shows a schematic perspective view of a blade 12 having a shroud segment 20 according to the invention, which has a stiffening structure 22 according to a second exemplary embodiment.
  • FIG. 4 will be explained below in conjunction with FIG. 5, which shows a schematic, partial and transparent perspective view of the blade 12 shown in FIG. 4. In contrast to the exemplary embodiment shown in FIG.
  • the stiffening structure 22 comprises three ribs 26a-c which are arranged in pairs in a cross shape and also 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. 6 shows a schematic and partially wire-frame view of a rear side of a 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 exemplary embodiment, two cross-shaped ribs 26.
  • the ribs 26 are likewise arranged along or perpendicular to stress lines of the shroud segment 20, wherein only one of the ribs 26 can be seen.
  • the angle ⁇ between the main axes H of the ribs 26 and the height or the profile profile of the ribs 26 is again selected as a function of the stress 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)

Abstract

L'invention concerne un segment de bande de recouvrement (20) à placer sur une aube (12), en particulier une aube de turbine à gaz, qui comprend une structure raidisseuse (22) faisant saillie par rapport à la surface (24) du segment de bande de recouvrement et ayant au moins par endroits une forme en croix. L'invention concerne également une aube (12), en particulier une aube de turbine à gaz, pour une turbomachine dont une zone d'extrémité radiale comporte un segment de bande de recouvrement (20) qui présente une structure raidisseuse (22) faisant saillie par rapport à la surface (24) du segment de bande de recouvrement et ayant au moins par endroits une forme en croix.
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 true EP2376746A2 (fr) 2011-10-19
EP2376746B1 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 (17)

* 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
EP2615243B1 (fr) * 2012-01-11 2017-08-30 MTU Aero Engines AG Segment de couronne d'aubes pour une turbomachine et son procédé de fabrication
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
PL3056677T3 (pl) 2015-02-12 2020-06-01 MTU Aero Engines AG Łopatka i maszyna przepływowa
JP6461382B2 (ja) * 2015-06-29 2019-01-30 シーメンス アクチエンゲゼルシヤフトＳｉｅｍｅｎｓ Ａｋｔｉｅｎｇｅｓｅｌｌｓｃｈａｆｔ シュラウド付きタービンブレード
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
DE102024125586A1 (de) * 2024-09-06 2026-03-12 MTU Aero Engines AG Leitschaufelsegment

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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
PL2402559T3 (pl) * 2010-07-01 2019-04-30 MTU Aero Engines AG Łopatka turbiny z bandażem szczytu łopatki

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Also Published As

Publication number Publication date
WO2010149139A2 (fr) 2010-12-29
PL2376746T3 (pl) 2017-11-30
US9322281B2 (en) 2016-04-26
DE102009030566A1 (de) 2010-12-30
ES2638450T3 (es) 2017-10-20
WO2010149139A3 (fr) 2011-07-21
US20120107123A1 (en) 2012-05-03
EP2376746B1 (fr) 2017-08-09

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