EP2646656A1 - Moyen d'amortissement pour amortir le mouvement d'une aube d'une turbomachine - Google Patents

Moyen d'amortissement pour amortir le mouvement d'une aube d'une turbomachine

Info

Publication number
EP2646656A1
EP2646656A1 EP11813768.6A EP11813768A EP2646656A1 EP 2646656 A1 EP2646656 A1 EP 2646656A1 EP 11813768 A EP11813768 A EP 11813768A EP 2646656 A1 EP2646656 A1 EP 2646656A1
Authority
EP
European Patent Office
Prior art keywords
damping means
turbomachine
blade
damping
rotor
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
EP11813768.6A
Other languages
German (de)
English (en)
Other versions
EP2646656B1 (fr
Inventor
Carsten SCHÖNHOFF
Manfred Dopfer
Martin Pernleitner
Wilfried SCHÜTTE
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
Publication of EP2646656A1 publication Critical patent/EP2646656A1/fr
Application granted granted Critical
Publication of EP2646656B1 publication Critical patent/EP2646656B1/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing blade vibration
    • 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
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making

Definitions

  • Damping means for damping a blade movement of a turbomachine
  • the invention relates to a damping means for damping a blade movement of a turbomachine according to the preamble of claim 1 and to a method for producing the damping means.
  • Turbomachines in particular gas or steam turbines, have a rotor and blades distributed over the circumference of the rotor, which are coupled to the rotor.
  • the blades must be designed to withstand, during operation of the turbine, a variety of stresses, such as e.g. withstand centrifugal forces, erosion corrosion and vibrations.
  • the vibrational stresses to which the present invention pertains may arise from a combination of the medium flowing through the turbine and the forces acting on the blades.
  • the blade vibrations can become longer in the long term
  • a damping means for a blade of a turbine in a recess of a blade platform is arranged.
  • the damping means has in
  • Axial normal cross section a triangular shape with rounded longitudinal edges.
  • the longitudinal edges each have a symmetrical crowned shape between the corners.
  • the damping means for damping the blade movement abuts an inner wall of the recess and a friction surface of another blade platform.
  • Turbomachine is set. This may result in a correspondingly shaped friction surface of the turbomachine that the damping means is applied unfavorably to the friction surface of the turbomachine.
  • the friction surface of the turbomachine may be formed such that the damping means only in a small Reibtrust Scheme on the friction surface of the Turbomachine is present. This leads to the fact that the frictional heat occurring during the damping of the blade movement can be dissipated only via the small friction contact region, which can lead to damage or wear of the damping means and / or the corresponding friction component of the turbomachine.
  • the object of the present invention is to improve the damping of a turbomachinery blade.
  • a damping means according to the preamble of claim 1 is further developed by the characterizing features.
  • Claim 10 protects a turbomachine in which the damping means is used.
  • Claim 11 provides a method of manufacturing the damping means under protection.
  • the damping means has at least one asymmetrically crowned side surface, which is provided for damping a blade movement of a turbomachine. Upon swinging of the blade during operation of the turbomachine, the swing motion of the blade is damped by friction of the side surface of the damping means with the friction surface of the turbomachine in the frictional contact region.
  • the asymmetrically convex side surface makes it possible to displace the friction contact region between the friction surface of the turbomachine and the side surface of the damping means into a more favorable region.
  • the frictional contact region is displaced such that the frictional contact region between the side surface of the damping means and the friction surface of the turbomachine increases. The occurring at a damping of the blade movement
  • Frictional heat can be dissipated via the larger ReibMauriere Colour in a friction component of the turbomachine. Thus, reduces the risk that when damping the blade movement, the damping means and / or the friction member due to the friction heat are damaged or worn.
  • Another advantage of using an asymmetrically crowned side surface is that when the side surface of the damping means is worn due to friction and / or heating, the friction region of the damping means and thus the friction contact region between the damping means and the friction surface of the turbomachine increases disproportionately.
  • a larger frictional contact area allows a faster Reib stiinneabloom, thereby increasing the risk of damage and / or wear of the Damping means and / or friction component of the turbomachine reduced.
  • an advantage of an asymmetrically convex side surface is that, in the case of wear caused by friction, the friction region of the damping means is adapted to the respective one
  • Friction surface of the friction member of the turbomachine comes. This will be
  • convex in the context of the invention, a convex curved surface is referred to.
  • a convex curved surface is referred to.
  • an asymmetrical surface is understood in the context of the invention, an area that two
  • the asymmetrically crowned side surface is therefore understood in particular to mean a convexly curved side surface which has two differently shaped sections.
  • the sections are formed such that there is no mirror plane perpendicular to the side surface and to which the sections separated by the mirror plane are mirror-symmetrical.
  • a friction contact region is understood to mean a region in which friction between the friction region of the damping means and the blade is caused by a blade movement
  • Friction surface of the turbomachine occurs.
  • the friction component is understood to mean all components of a turbomachine which are in frictional contact with the damping means in order to damp a blade vibration.
  • a friction member may in particular be part of a blade or may be coupled to a blade.
  • a blade platform, a cover plate of a blade, and a positioner for the rotor blade in the rotor axis direction may each be a friction component in the sense of the present invention.
  • the asymmetrically crowned side surface may be formed such that these are slightly g um; rotate a damper axis ; can.
  • Friction of the side surface with the friction surface of the turbomachine acts on the damping means a frictional force, which can cause a slight rotation of the damping means.
  • the asymmetrically crowned side surface is formed such that increases in a slight rotation of the damping means of the friction region of the damping means and thus the Reibtrust Scheme between damping means and the Reibbaüteil the turbomachine.
  • the side surface may have at least two sections with different radii of curvature. In this case, at least one portion, which is radially further away from a rotor axis, have a smaller radius of curvature than a portion which is radially closer to
  • Rotor axis is located.
  • the damping of the blade vibration is improved.
  • the improvement of the damping results because the frictional contact portion forms in a region of the side surface of the damping means, which is far away from the rotor axis. It is true that the farther the frictional contact portion is away from the rotor axis, the greater a friction torque caused by the frictional force occurring in the frictional contact portion, which dampens the vibration of the blade.
  • the damping means comprises a base body which is triangular or polygonal shaped in a Achsnormalquerrough.
  • the side surfaces of the triangular or polygonal base body may each have rounded corners of the base body.
  • the portion of the asymmetrical crowned side surface, which has a smaller radius of curvature and is provided a the end of the side surface remote from the rotor axis, may each be provided adjacent to the rounded corners.
  • An anti-rotation means and / or a fastening means may be attached to the damping means.
  • the anti-rotation means prevents or limits a rotation of the damping means about a damping center axis within a recess of the
  • Damping means axis rotates until the anti-rotation means against a on the
  • Turbomachine provided stop surface abuts.
  • the anti-rotation means is
  • Damping means is rotated in a position, in which the above-mentioned portion with the small radius of curvature in frictional contact with the friction surface of the turbomachine.
  • Damping means and thus the position of the center of gravity of the damping means By a corresponding structural design of the side surfaces of the damping means, the Position of the center of gravity can be adjusted. This can improve the dynamic property of the damping means.
  • the fastening means serves to prevent or limit movement of the
  • Damping means in particular in the direction of a rotor axis of the turbomachine.
  • the fastener ensures that the fastener can not leave the recess of the turbomachine.
  • the turbomachine may be a gas or steam turbine and, in particular, an aircraft engine.
  • the turbomachine has a rotor and stator blades and blades distributed over the circumference of the rotor, which are arranged one after the other in the flow direction of the gas.
  • In the rotor distributed grooves are provided over the circumference of the rotor.
  • the grooves extend parallel to a rotor axis.
  • the blade in particular a blade, may have a cover plate, an airfoil, a blade platform and a blade root. The blade is positioned over the blade root in the groove in the radial direction to the rotor axis.
  • a fixing of the blade in Rotorachsplatz can be done by a provided in the groove locking plate and / or by a separately provided on the rotor positioning. Vane vibration may occur with respect to the blade and the rotor and / or between two or more blades.
  • the damping means can be arranged at different locations in the turbomachine.
  • the cover plate of a blade can have a recess which at least partially defines a, in particular closed, cavity and in which the damping means is arranged.
  • the recesses of two cover plates of adjacent blades may define the cavity.
  • the damping means is arranged in the recess such that in operation of the turbomachine, the damping means by means of a side surface in frictional contact with a friction surface of the recesses of a cover plate and with another side surface with a
  • Friction surface of the recess of the other cover plate is in frictional contact.
  • the damping means is arranged such that it is in frictional contact with a side surface a friction surface of the positioning means. Furthermore, the damping means in another side surface in contact, in particular frictional contact, with a blade surface.
  • Shovel platform be arranged.
  • the blade platform is disposed between the blade root and the airfoil.
  • the damping means is arranged in the recess such that the damping means in an operation of the turbomachine with a side surface in
  • the damping means which has at least one asymmetrically crowned side surface, can preferably be produced by prototyping, forming and / or by a machining process.
  • Embodiment. Show:
  • Figure 1 a schematic representation of a damping means in a cavity according to an embodiment of the invention.
  • FIG. 2 shows an enlarged view A-A of a friction contact region from FIG. 1 according to FIG.
  • the Dämp spangsstoff 2 shown in Figure 1 has a in a Achsnormalquerrough a in
  • the triangular base body 20 has a support surface 25 and two side surfaces 21, 21 ', which merge into one another in rounded ends.
  • the side surfaces 21, 2 each have an asymmetrical spherical shape.
  • the damping means 2 is arranged in a cavity which is defined by two recesses 11 of adjacently arranged blades 10, 10 'of a turbomachine 1.
  • the cavity has a triangular cross section in an axial normal cross section, wherein the individual cavity walls are made longer than the side surfaces 21 and
  • the damping means 2 is arranged in such a way in the cavity that it is independent of the operating state of the turbomachine 1 with the
  • Cavity walls of the two blades 10, 10 ' is in contact.
  • Both side surfaces 21, 2 of the damping means s 2 have a first portion with a first radius of curvature Rl, a second portion with a second radius of curvature R2 and a third portion with a third K_rümmungsradius R3. Further, in both side surfaces 21, 21 ', the second portion having the second radius of curvature R2 is disposed between the first and second portions and formed longer than the first and third portions.
  • the third radius of curvature R3 has a smaller value than the first and second radius of curvature Rl, R2. Furthermore, the first radius of curvature R1 has a smaller value than the second radius of curvature R2.
  • the first section with the first radius of curvature Rl is located at the end of the side surface 21 near the rotor axis.
  • the third section with the third radius of curvature R3 is in the radial direction to the rotor axis at the point remote from the rotor axis End of the side surface 21 arranged and with the corresponding cavity wall in a Reibêt Society 22 in frictional contact.
  • the third section with the third radius of curvature R3 is arranged in the radial direction to the rotor axis at the end of the side surface 21 'close to the rotor axis and in frictional contact with the corresponding cavity wall in a frictional contact region 22.
  • the blade 10 of the turbomachine 1 is designed such that it has a recess 14; by which the anti-rotation device 24 extends in a radial direction to the rotor axis.
  • the recess 14 is bounded by the walls of the recess 14 and by a stop surface 12.
  • the abutment surface 12 is provided on the blade 10 ', which is adjacent to the blade 10 with the recess 14.
  • the recess 14 is formed such that the damping means 2 can not fall over them from the cavity in an idle state of the turbine.
  • the damping means 2 is located on the support surface 25 on the corresponding cavity wall, and the anti-rotation means 24 extends through the recess 14 in the radial direction to the rotor axis.
  • the damping means 2 is moved in a radial direction in a direction away from the rotor axis due to the centrifugal force until the
  • the damping means 2 is rotated until the anti-rotation means 24 abuts against the abutment surface 12 of a blade 10. The result is the two
  • Frictional contact of the damping means 2 are damped with the cavity walls.
  • FIG. 2 shows an enlarged view A-A of the frictional contact region 22 of FIG. 1.
  • the third portion having the pitch radius R3 of the first side surface 21 is in frictional contact with the cavity wall.

Landscapes

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

Abstract

L'invention concerne un moyen d'amortissement (2) pour amortir le mouvement d'une aube d'une turbomachine (1) et un procédé de fabrication de ce moyen d'amortissement (2). Le moyen d'amortissement (2) comporte au moins une face latérale (21, 21') qui, pour amortir un mouvement d'aube, peut être mise en contact de frottement avec une surface de frottement de la turbomachine (1), les faces latérales (21, 21') étant bombées de manière asymétrique.
EP11813768.6A 2010-11-30 2011-11-29 Moyen d'amortissement pour amortir le mouvement d'une aube d'une turbomachine Active EP2646656B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102010052965.6A DE102010052965B4 (de) 2010-11-30 2010-11-30 Dämpfungsmittel zum Dämpfen einer Schaufelbewegung einer Turbomaschine
PCT/DE2011/002110 WO2012072069A1 (fr) 2010-11-30 2011-11-29 Moyen d'amortissement pour amortir le mouvement d'une aube d'une turbomachine

Publications (2)

Publication Number Publication Date
EP2646656A1 true EP2646656A1 (fr) 2013-10-09
EP2646656B1 EP2646656B1 (fr) 2017-08-02

Family

ID=45554402

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11813768.6A Active EP2646656B1 (fr) 2010-11-30 2011-11-29 Moyen d'amortissement pour amortir le mouvement d'une aube d'une turbomachine

Country Status (5)

Country Link
US (1) US9506372B2 (fr)
EP (1) EP2646656B1 (fr)
DE (1) DE102010052965B4 (fr)
ES (1) ES2637991T3 (fr)
WO (1) WO2012072069A1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10316673B2 (en) * 2016-03-24 2019-06-11 General Electric Company CMC turbine blade platform damper
DE102017208631A1 (de) 2017-05-22 2018-11-22 Siemens Aktiengesellschaft Verfahren zum Herstellen einer schwingungsdämpfenden Strukturkombination zur Dämpfung von Schwingungen bewegbarer Massen
JP6991912B2 (ja) * 2018-03-28 2022-01-13 三菱重工業株式会社 回転機械
DE102018221533A1 (de) 2018-12-12 2020-06-18 MTU Aero Engines AG Turbomaschinen Schaufelanordnung
US11193376B2 (en) * 2020-02-10 2021-12-07 Raytheon Technologies Corporation Disk supported damper for a gas turbine engine

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2927357A1 (fr) * 2008-02-12 2009-08-14 Snecma Sa Dispositif d'amortissement des vibrations entre deux aubes de roue aubagee de turbomachine

Family Cites Families (11)

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Publication number Priority date Publication date Assignee Title
US3037741A (en) * 1958-12-29 1962-06-05 Gen Electric Damping turbine buckets
US3266770A (en) * 1961-12-22 1966-08-16 Gen Electric Turbomachine rotor assembly
US4182598A (en) * 1977-08-29 1980-01-08 United Technologies Corporation Turbine blade damper
FR2665726B1 (fr) * 1990-08-08 1993-07-02 Snecma Soufflante de turbomachine a amortisseur dynamique a cames.
US5478207A (en) * 1994-09-19 1995-12-26 General Electric Company Stable blade vibration damper for gas turbine engine
US6851932B2 (en) 2003-05-13 2005-02-08 General Electric Company Vibration damper assembly for the buckets of a turbine
DE10340773A1 (de) 2003-09-02 2005-03-24 Man Turbomaschinen Ag Rotor einer Dampf- oder Gasturbine
JP2005273646A (ja) 2004-02-25 2005-10-06 Mitsubishi Heavy Ind Ltd 動翼体及びこの動翼体を有する回転機械
US7534090B2 (en) * 2006-06-13 2009-05-19 General Electric Company Enhanced bucket vibration system
DE102006041322A1 (de) 2006-09-01 2008-04-24 Rolls-Royce Deutschland Ltd & Co Kg Dämpfungs- und Dichtungssystem für Turbinenschaufeln
US7572098B1 (en) * 2006-10-10 2009-08-11 Johnson Gabriel L Vane ring with a damper

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2927357A1 (fr) * 2008-02-12 2009-08-14 Snecma Sa Dispositif d'amortissement des vibrations entre deux aubes de roue aubagee de turbomachine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of WO2012072069A1 *

Also Published As

Publication number Publication date
DE102010052965B4 (de) 2014-06-12
US20130287583A1 (en) 2013-10-31
EP2646656B1 (fr) 2017-08-02
WO2012072069A1 (fr) 2012-06-07
DE102010052965A1 (de) 2012-05-31
ES2637991T3 (es) 2017-10-18
US9506372B2 (en) 2016-11-29

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