EP1515001B1 - Dispositif de connexion pour les aubes de rotor d'une turbomachine - Google Patents

Dispositif de connexion pour les aubes de rotor d'une turbomachine Download PDF

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Publication number
EP1515001B1
EP1515001B1 EP04104236.7A EP04104236A EP1515001B1 EP 1515001 B1 EP1515001 B1 EP 1515001B1 EP 04104236 A EP04104236 A EP 04104236A EP 1515001 B1 EP1515001 B1 EP 1515001B1
Authority
EP
European Patent Office
Prior art keywords
support surface
pressure body
projection
contour
turbomachine
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.)
Not-in-force
Application number
EP04104236.7A
Other languages
German (de)
English (en)
Other versions
EP1515001A3 (fr
EP1515001A2 (fr
Inventor
Eduard GÖTZFRIED
Heinz-Dieter Tremmel
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.)
General Electric Technology GmbH
Original Assignee
General Electric Technology 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 General Electric Technology GmbH filed Critical General Electric Technology GmbH
Publication of EP1515001A2 publication Critical patent/EP1515001A2/fr
Publication of EP1515001A3 publication Critical patent/EP1515001A3/fr
Application granted granted Critical
Publication of EP1515001B1 publication Critical patent/EP1515001B1/fr
Not-in-force legal-status Critical Current
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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • 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
    • F05D2250/24—Three-dimensional ellipsoidal
    • F05D2250/241—Three-dimensional ellipsoidal spherical
    • 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

Definitions

  • the present invention relates to a binding of blades of a turbomachine with the features of the preamble of claim 1.
  • Out DE 35 17 283 C2 is a blade binding of the type mentioned, are provided in the lugs, which extend in the circumferential direction, are rigidly connected in pairs with a blade and are supported in each case via at least one pressure body to the circumferentially adjacent approach.
  • each pressure body on a support side facing the associated approach to a holding contour which projects into a receptacle formed on the associated approach and is supported therein in the circumferential direction and transversely thereto.
  • each pressure body on a side facing the adjacent approach support side on a flat support surface, which is supported on a surface of the adjacent approach associated flat counter-support surface.
  • the holding contours of the pressure hull are each formed as a cone.
  • the associated receptacles are also formed as a cone, wherein the cone of the retaining contour, however, has a different conicity than the cone of the receptacle. This ensures that manufacturing tolerances of the seat and the pressure body by slight plastic deformation on the outer edge of the cone holder and the Konushaltekontur can be compensated.
  • the counter support surface on which the support surface of the pressure hull is supported may be formed in a development of the known blade binding by the support surface of a counter-pressure body, which is identical to the pressure hull.
  • the known blade binding works optimally when only relative movements occur during operation of the turbomachine, which run parallel to the support surface.
  • the support surface can then slide on the mating support surface.
  • not only parallel relative movements occur between the approaches to be supported or to be connected to one another.
  • twisting and twisting of the blades and thus of the lugs may occur, resulting in particular in increased vibration loading of the blade tie.
  • Rotational movements between the lugs lead to a line or point load of the respective pressure body receptacle, which can lead to a brittle fracture of the hard pressure body or to tearing of the pressure body seat.
  • US 4,257,743 shows a coupling device with two approaches, one of which is provided with a fixed pressure body in the form of a hemispherical projection and the other with a hemispherical retaining contour for loosely receiving the hemispherical projection when the adjacent blades are mounted.
  • JP 63 132801 U and JP H01 152003 U in that the retaining contour of the pressure body and the contour of the associated receptacle can be formed as complementary cylindrical sections.
  • EP202531 a blade binding with cone-shaped pressure bodies.
  • the object is to provide an improved embodiment for a blade binding of the type mentioned, which makes it possible to compensate for manufacturing tolerances, games, elastic deformation and similar factors exclusively by a sliding movement.
  • the invention is based on the general idea of forming the retaining contour of the pressure hull and the contour of the associated receptacle as complementary ball sections and rigidly fixing the counterpressure elements with respect to their longitudinal center axis, so that the counterpressure body can serve as an abutment for the pressure hull supporting thereon.
  • the pressure body is supported flat on the associated approach.
  • a ball head bearing of the pressure hull is formed on the associated approach, which allows the pressure hull to rotate its support surface around the ball center.
  • the rotatably mounted pressure body can compensate for these relative movements, so that a flat power transmission between the mutually supported or interconnected Ansälzen is always achievable.
  • Changing angular positions of the moving blades or of the lugs effect an automatic adjustment of the movably mounted pressure bodies in the case of the bucket binding according to the invention. Voltage peaks are thereby avoided.
  • the friction damping is fully accentuated by the flat system. There are no high-frequency tilting movements.
  • the ball portion of the retaining contour on a ball center, while the support surface is circular and has a circle center.
  • the pressure body is then designed so that a straight line which extends through both the center of the circle and through the center of the sphere, is perpendicular to the support surface plane.
  • the pressure body is rotationally symmetrical with respect to these straight lines.
  • the counter support surface which is assigned to the adjacent approach and on which the supporting surface of the pressure hull is supported in a planar manner, can be formed, for example, by the support surface of a counterpressure body t, which is held on the adjacent projection.
  • the counter-pressure body can not carry out tumbling movements with respect to the normal direction of its counter-support surface. In this way, all compensatory movements are performed exclusively by the ball-bearing pressure body. This ensures that the movable pressure body with appropriate twists of the approaches again and again adjusted by itself to its original position.
  • both the retaining contour of the counter-pressure body and the associated receptacle are formed as a cone or a truncated cone, both truncated cones have the same conicity.
  • both truncated cones have the same conicity.
  • the counter-pressure body is fixed rigidly with respect to its longitudinal central axis at the base and can thereby serve as an abutment for the pressure body supported thereon.
  • Fig. 1a and 1b are blades 1 of a turbomachine not shown otherwise equipped with two, lying on different sides of the blade lugs 2.
  • These lugs 2 extend in a direction indicated by an arrow circumferential direction 3, in which the blades rotate 1 during operation of the turbomachine.
  • the lugs 2 are rigidly connected to the respective blade 1 and in particular can form an integral part of the respective blade 1.
  • the lugs 2 are designed in the form of support wings, which have aerodynamic profiles and are usually arranged between the radial ends of the blades 1.
  • the lugs 2 can also be designed as cover plates or cover bands, which are connected to the radially outer ends of the Blades 1 are arranged.
  • the lugs 2 can also be other binding elements.
  • the lugs 2 are not supported directly on each other at their end faces 4, but indirectly via at least one pressure body 7 (cf. Fig. 2 ).
  • these pressure body 7 are for simplicity of illustration in the Fig. 1 a and 1 b are not reproduced.
  • sectional views of Fig. 2 are each the opposite end portions of a pair of lugs 2, which support each other at least during operation of the turbomachine, reproduced in section, while arranged in this area pressure body 7 is not shown cut. It is clear that the sectional view of the Fig. 2 to 4 may also correspond to a section around the section line II in the plane of the drawing Fig. 1 b rotated by 90 °.
  • each pressure body 7 has a spherical holding side 8 and a flat support side 9. While the holding side 8 faces that projection 2 to which the respective pressure body 7 is assigned (according to FIGS Fig. 2 in each case the right-hand projection 2), the support side 9 faces the projection 2 which is adjacent in the circumferential direction 3 (ie according to FIG Fig. 2 in each case the left approach 2). On the holding side 8 a down or projecting holding contour 10 is formed.
  • the approach 2, which is associated with the pressure body 7, has on its end face 4 a receptacle 11 into which the holding contour 10 of the pressure body 7 is inserted.
  • the retaining contour 10 thus protrudes into the receptacle 11 and can are supported in the circumferential direction 3 and transverse to the circumferential direction 3, according to the invention, the holding contour 10 is now formed as a ball portion.
  • the receptacle 11 is also formed as a ball section.
  • the ball sections have the same radius R, whereby the ball portion of the retaining contour 10 is flat on the ball portion of the receptacle 11 to the plant.
  • the pressure body 7 according to the invention thereby forms a kind of ball joint, which is mounted in a joint socket about a spherical center 12 movably on the associated projection 2.
  • the joint socket is formed here by the receptacle 11.
  • the radii of pressure body 7 and receptacle 11 may also differ slightly from one another.
  • the pressure body 7 has on its support side 9 a flat support surface 13. As shown in Fig. 2 it emerges, the pressure body 7 is supported at least during operation of the turbomachine with its support surface 13 on a mating support surface 14 which is associated with the adjacent support wing 2.
  • the counter-support surface 14 is also configured so that the support surfaces 13 and 14 rest flat against one another.
  • the pressure body 7 of the invention between the interconnected lugs 2 comparatively large forces F transmitted in the circumferential direction 3.
  • forces F transmitted in the circumferential direction 3.
  • by the friction and coupling moments M between adjacent blades 1 can be transmitted via the interconnected lugs 2.
  • Due to the movable mounting of the pressure hull 7 on the associated approach 2 also Drehver einen or twists between adjacent blades 1 and between mutually supported lugs 2 can be compensated.
  • the blade binding according to the invention can thus compensate for the rotational movements and different angular positions of the lugs 2 possibly occurring during operation, in particular during startup and shutdown, without resulting in greater elastic or even plastic deformation.
  • the geometry of the support body 7 is suitably chosen so that the support surface 13 is configured circular and has a circle center point 15.
  • the spherical holding contour 10 is matched to the flat support surface 13, that a straight line 16, which extends through both the center of the circle 15 and through the ball center 12, is perpendicular to the plane of the support surface 13. This results in a rotational symmetry for the pressure body 7, so that the storage achieved thereby acts in all directions as it were.
  • the counter support surface 14 may also be formed on a special abutment element 17.
  • This abutment element 17 is fixed to the front side 4 of the adjacent projection 2, in particular by soldering or welding.
  • the abutment member 17 is designed as a plate which is inserted into the end face 4 of the adjacent lug 2 and disposed therein sunk.
  • the counter-support surface 14 is also formed on a counter-pressure member 18.
  • the counterpressure body 18 has - just like the pressure body 7 - a support side 19 with a flat support surface which forms the counter support surface 14.
  • the counter pressure element 18 is also provided with a holding side 20 on which a holding contour 21 is formed.
  • the holding contour 21 of the counterpressure body 18 is inserted into a corresponding receptacle 22, which is formed in the adjacent projection 2.
  • the shaping of the retaining contour 21 of the counterpressure body 18 and the cooperating receptacle 22 are matched to one another such that the counter support surface 14 of the counter-pressure member 18 is fixed spatially relative to the associated approach 2.
  • the retaining contour 21 is formed as a cone, while fitting the associated receptacle 22 is designed as a cone, which has the same taper as the cone of the retaining contour 21. Consequently, the retaining contour 21 of the counterpressure body 18 abuts flat against the receptacle 22. Although it is in principle still possible to rotate the counter-pressure member 18 about its longitudinal central axis, but the plane of its counter-support surface 14 remains invariant relative to the associated approach 2.
  • the support surfaces 13 and / or the counter support surfaces 14 may be provided with a low-friction coating (not shown). At the same time, the frictional forces occurring in the plane of the support surfaces 13 and the counter support surfaces 14 can be reduced by this measure.
  • the pressure bodies 7 or the counterpressure bodies 18 may be formed from a suitable hard metal, at least in a section having the support surface 13 or the counter support surface 14.

Landscapes

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

Claims (2)

  1. Dispositif de connexion pour les aubes de rotor (1) d'une turbomachine, avec des embases (2) qui s'étendent dans la direction périphérique (3), qui sont rigidement reliées par paires à une aube de rotor (1) et qui s'appuient, au moins pendant le fonctionnement de la turbomachine, respectivement par au moins un corps de pression (7) sur l'embase (2) voisine dans la direction périphérique (3),
    - dans lequel chaque corps de pression (7) présente sur un côté de maintien (8) tourné vers l'embase correspondante (2) un contour de maintien (10), qui pénètre dans un logement (11) formé sur l'embase correspondante (2) et s'appuie dans celui-ci dans la direction périphérique (3) et transversalement à celle-ci,
    - dans lequel chaque corps de pression (7) présente sur un côté d'appui (9) tourné vers l'embase voisine (2) une face d'appui plane (13), qui s'appuie à plat, au moins pendant le fonctionnement de la turbomachine, sur une face d'appui opposée plane (14) associée à l'embase voisine (2),
    - dans lequel au moins un corps de pression (7), dont le contour de maintien (10) est réalisé en forme de partie de sphère, est associé à chaque paire d'embases (2) s'appuyant l'une sur l'autre,
    - dans lequel le logement correspondant (11) est également réalisé en forme de partie de sphère, dont le rayon (R) est au moins approximativement égal au rayon (R) de la partie de sphère du contour de maintien (10),
    caractérisé en ce que la face d'appui opposée (14) est formée par la face d'appui d'un corps de contrepression (18), qui pénètre avec son contour de maintien (21) dans un logement (22) formé dans l'embase voisine (2), dans lequel le contour de maintien (21) du corps de contrepression (18) est réalisé en forme de cône, et dans lequel le logement correspondant (22) est également réalisé en forme de cône, dont la conicité est identique à la conicité du cône du contour de maintien (21).
  2. Dispositif de connexion pour les aubes de rotor selon la revendication 1, caractérisé en ce que la face d'appui (13) et/ou la face d'appui opposée (14) est/sont réalisée(s) à frottement faible et est/sont résistante(s) à l'usure.
EP04104236.7A 2003-09-12 2004-09-02 Dispositif de connexion pour les aubes de rotor d'une turbomachine Not-in-force EP1515001B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10342207 2003-09-12
DE10342207A DE10342207A1 (de) 2003-09-12 2003-09-12 Laufschaufelbindung einer Turbomaschine

Publications (3)

Publication Number Publication Date
EP1515001A2 EP1515001A2 (fr) 2005-03-16
EP1515001A3 EP1515001A3 (fr) 2012-07-04
EP1515001B1 true EP1515001B1 (fr) 2016-11-09

Family

ID=34129785

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04104236.7A Not-in-force EP1515001B1 (fr) 2003-09-12 2004-09-02 Dispositif de connexion pour les aubes de rotor d'une turbomachine

Country Status (6)

Country Link
US (1) US7140841B2 (fr)
EP (1) EP1515001B1 (fr)
JP (1) JP2005090506A (fr)
CN (1) CN100374688C (fr)
DE (1) DE10342207A1 (fr)
ZA (1) ZA200407296B (fr)

Families Citing this family (11)

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Publication number Priority date Publication date Assignee Title
GB2436597A (en) * 2006-03-27 2007-10-03 Alstom Technology Ltd Turbine blade and diaphragm
US20090202344A1 (en) * 2008-02-13 2009-08-13 General Electric Company Rotating assembly for a turbomachine
EP2116693A1 (fr) * 2008-05-07 2009-11-11 Siemens Aktiengesellschaft Rotor pour une turbomachine
EP2213837A1 (fr) * 2009-01-29 2010-08-04 Siemens Aktiengesellschaft Système de pale de turbine
JP5491325B2 (ja) * 2010-08-26 2014-05-14 三菱重工業株式会社 動翼及び回転機械
WO2014051670A1 (fr) * 2012-09-25 2014-04-03 United Technologies Corporation Réseau de profils aérodynamiques avec profils aérodynamiques qui ont des géométries différentes associées à des classes géométriques
US10465531B2 (en) 2013-02-21 2019-11-05 General Electric Company Turbine blade tip shroud and mid-span snubber with compound contact angle
US9464530B2 (en) 2014-02-20 2016-10-11 General Electric Company Turbine bucket and method for balancing a tip shroud of a turbine bucket
JP5836410B2 (ja) * 2014-02-27 2015-12-24 三菱重工業株式会社 動翼及び回転機械
EP3085890B1 (fr) * 2015-04-22 2017-12-27 Ansaldo Energia Switzerland AG Lame avec enveloppe pour la pointe
FR3137121A1 (fr) * 2022-06-22 2023-12-29 Safran Aircraft Engines Ensemble aubagé à liaison inter-plateformes par élément roulant interposé

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Publication number Priority date Publication date Assignee Title
US2283901A (en) * 1940-03-16 1942-05-26 Westinghouse Electric & Mfg Co Turbine blading
US2942843A (en) * 1956-06-15 1960-06-28 Westinghouse Electric Corp Blade vibration damping structure
JPS5632441B2 (fr) * 1973-11-30 1981-07-28
JPS54125307A (en) 1978-03-24 1979-09-28 Toshiba Corp Connecting device for turbine movable blades
JPS572405A (en) * 1980-06-05 1982-01-07 Hitachi Ltd Rotary blade connector of axial-flow rotary machine
US4407634A (en) * 1981-09-08 1983-10-04 Northern Engineering Industries Plc Axial-flow steam turbine wheel
DE3211073A1 (de) * 1982-03-25 1983-10-06 Kraftwerk Union Ag Einrichtung zur schwingungsdaempfung an einem leitschaufelkranz
JPS6149103A (ja) * 1984-08-16 1986-03-11 Toshiba Corp タ−ビン動翼連結装置
DE3517283A1 (de) 1985-05-14 1986-11-20 MAN Gutehoffnungshütte GmbH, 4200 Oberhausen Bindung von laufschaufeln einer thermischen turbomaschine
JPS63132801U (fr) 1987-02-20 1988-08-30
JPH0622083Y2 (ja) 1988-04-12 1994-06-08 三菱重工業株式会社 スタブダンパ
JP3933130B2 (ja) * 2001-08-03 2007-06-20 株式会社日立製作所 タービン動翼

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Also Published As

Publication number Publication date
DE10342207A1 (de) 2005-04-07
CN1594841A (zh) 2005-03-16
US20050111983A1 (en) 2005-05-26
JP2005090506A (ja) 2005-04-07
ZA200407296B (en) 2005-08-31
EP1515001A3 (fr) 2012-07-04
EP1515001A2 (fr) 2005-03-16
CN100374688C (zh) 2008-03-12
US7140841B2 (en) 2006-11-28

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