EP2551460A1 - Groupe d'aubes - Google Patents

Groupe d'aubes Download PDF

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Publication number
EP2551460A1
EP2551460A1 EP11175958A EP11175958A EP2551460A1 EP 2551460 A1 EP2551460 A1 EP 2551460A1 EP 11175958 A EP11175958 A EP 11175958A EP 11175958 A EP11175958 A EP 11175958A EP 2551460 A1 EP2551460 A1 EP 2551460A1
Authority
EP
European Patent Office
Prior art keywords
free surface
cover plate
blade
blades
contact surface
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Withdrawn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
EP11175958A
Other languages
German (de)
English (en)
Inventor
Erich Muranyi
Andreas Sonnenschein
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
Priority to EP11175958A priority Critical patent/EP2551460A1/fr
Publication of EP2551460A1 publication Critical patent/EP2551460A1/fr
Withdrawn legal-status Critical Current

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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

Definitions

  • the invention relates to a blade assembly comprising at least two blades, wherein the blades have a blade root and a cover plate.
  • Such blade assemblies are used, for example, in turbomachines, in particular in steam turbines.
  • Such turbomachines essentially have two components, which are formed by a rotor rotatably mounted about a rotation axis and a housing arranged around the rotor.
  • the rotor usually has so-called turbine blades, which are arranged on the peripheral surface regularly in so-called turbine blade rows, the turbine blade rows being arranged one behind the other viewed in the direction of the axis of rotation.
  • the housing has so-called vanes which are arranged between the blade rows.
  • a steam having a high thermal energy flowing into the steam turbine is expanded and cooled inside the steam turbine, whereby the thermal energy is converted into rotational energy of the rotor.
  • the operating speeds of the rotor can be between 25Hz and 60Hz. In industrial applications, variable speeds are also possible, such as for the drive of compressors.
  • the effects occurring at these speeds often lead to disturbing effects.
  • the operation of steam turbines is characterized by the rotational movement, by the interaction with the steam and other disturbing influences by a high degree of machine dynamics.
  • the invention deals with the problem of damping vibrations. In particular, the vibrations of the turbine blades should be reduced.
  • the turbine blades essentially have a blade root and a cover plate and a flow-mechanically profiled airfoil arranged between the blade root and the cover plate. These blades are caulked into so-called slots in the rotor.
  • Various embodiments of the blade roots are known.
  • the blade roots are formed in fir-tree or hammer-foot shape.
  • the turbine blades are predominantly freestanding, i. designed without shroud.
  • the invention addresses the problem of vibration excitations in the blade structure. It is therefore an object of the invention to provide a blade association in which it comes to lower unwanted vibration excitations.
  • a blade assembly comprising at least two blades, wherein the blades have a blade root and a cover plate, wherein the cover plate has a double-Z shape.
  • the prior art it is known to use simple Z cover plates. By contact of a Z-cover plate with the Z-cover plate of the two adjacent blades of the blade assembly is stiffened and coupled. By friction of the cover plates against each other energy is dissipated and a vibration excitation avoided.
  • Z-cover plate now another form of Z-cover plate is proposed.
  • the shape of the cover plate should now be formed double-Z-like. That means that in comparison to a simple Z-plate having two kinks, now a double-Z cover plate is to be formed, which has twice as many so four kinks.
  • the thus formed double-Z cover plates can thereby form more contact surfaces with each other, resulting in that the blade assembly is coupled together stiffer overall. This coupling of the blades with each other has an influence on the vibration behavior. It can be shown that an increase of various natural frequencies can be achieved by the double-Z cover plate-like design. This can be ensured when moving the natural frequencies that critical natural frequencies are not excited during operation of the turbomachine.
  • the blades are rotationally symmetrical about an axis of rotation.
  • the cover plates have in the circumferential direction substantially parallel to each other aligned side surfaces and a negatively swept with respect to the axis of rotation, first, second and third front free surface, wherein the third front free surface is arranged in the direction of the axis of rotation behind the second front free surface, wherein the second seen in the direction of the axis of rotation substantially behind the first front free surface, wherein the cover plate has a first front contact surface disposed between the first and second front free surface and is positively swept, wherein the cover plate has a second front contact surface, which is arranged between the second and third front free surface and is positively swept.
  • the shroud has a total of five surfaces which are formed from blade cover plate to blade cover plate complementary to each other. At standstill of the steam turbine creates a contact between the first front contact surface and the second front contact surface with an adjacently disposed cover plate of a complementarily shaped blade. At standstill thus a distance between the open spaces is formed.
  • the length b of the second free surface is substantially two to five times as long as the length of the first and second free surface.
  • FIG. 1 shows a first cover plate 1 and a second cover plate 2 of two blades, not shown.
  • the blades form a blade assembly not shown in detail and are formed in the circumferential direction 3 about a rotation axis 4.
  • the cover plates 1, 2 and the blades are made almost identical to each other. In operation, the cover plates 1,2 rotate at high frequencies about the axis of rotation.
  • the blades have a blade root (not shown).
  • the first cover plate 1 and second cover plate 2 are characterized by a shape similar to a double Z shape.
  • the blades are for this purpose designed such that they are arranged rotationally symmetrical about the rotation axis 4 and the first cover plate 1 and the second cover plate 2 in the circumferential direction 3 substantially parallel side surfaces 5 and 6 and have a negatively swept with respect to the rotation axis 4 first front free surface 7, a second front free surface 8 and a third front free surface 9 have.
  • the first front free surface 7 is in Essentially arranged in the direction of the rotation axis 4 arranged one behind the other.
  • the third front free surface 9 is arranged behind the second front free surface 8 when viewed in the direction of rotation of the axis.
  • a first front contact surface 10 is formed, as well as between the second front free surface 8 and the third front free surface 9, a second front contact surface 11 is formed.
  • the first front contact surface 10 and the second front contact surface 11 are positively swept.
  • a surface in the sense of this application is negatively swept when it is rotated in the mathematically negative sense (ie clockwise) seen from the rotation axis direction 4.
  • the first front, second front and third front free surfaces are rotated from the rotation axis 4 in the clockwise direction.
  • the first front contact surface 10 is rotated in a mathematically positive sense. That is, the first front contact surface 10 and the second front contact surface 11 are rotated counterclockwise from the rotation axis direction 4.
  • the adjacent cover plate (first cover plate 1) has a complementary design to the first front, second front, third front free surface, and the first front contact surface and second front contact surface.
  • first cover plate has a first rear free surface 12, a second rear free surface 13 and a third rear free surface 14.
  • the third rear free surface 14 is arranged in rotation axis direction 4 behind the second rear free surface 13.
  • the second rear free surface 13 is arranged in the direction of rotation of the axis behind the first rear free surface 12.
  • the first rear free surface 12, the second rear free surface 13 and third rear free surface 14 are negatively swept.
  • Between the second rear free surface 13 and the third rear free surface 14 is a second rear contact surface 16 trained.
  • the first rear contact surface 15 and the second rear contact surface 16 are positively swept relative to the axis of rotation 4.
  • the first front free surface 7 is formed substantially parallel to the first rear free surface 12.
  • the second front free surface 8 and the second rear free surface 13 and the third front free surface 9 are formed approximately parallel to the third rear free surface 14.
  • the first front contact surface 10 contacts the first rear contact surface 15.
  • contact between the second front contact surface 11 and the second rear contact surface 16 is also possible.
  • the blade root not shown in detail is perpendicular to the axis of rotation 4 seen (ie in the radial direction) formed substantially rhomboid or parallelogram.
  • the length b of the second front free surface 8 is substantially two to five times as long as the length a of the first front free surface 7 and the length c of the third front free surface 9.
  • the first front free surface 7 and the third front free surface 9 are substantially equal in length. This means that a is approximately equal to c.
  • first front contact surface 10 has a length e.
  • the second front contact surface 11 has a length f.
  • the length e and the length f are essentially the same length.
  • the vane dressing according to FIG. 1 is intended for installation in a steam turbine, which means that the vapor direction is guided essentially along the axis of rotation 4.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP11175958A 2011-07-29 2011-07-29 Groupe d'aubes Withdrawn EP2551460A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11175958A EP2551460A1 (fr) 2011-07-29 2011-07-29 Groupe d'aubes

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11175958A EP2551460A1 (fr) 2011-07-29 2011-07-29 Groupe d'aubes

Publications (1)

Publication Number Publication Date
EP2551460A1 true EP2551460A1 (fr) 2013-01-30

Family

ID=44653988

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11175958A Withdrawn EP2551460A1 (fr) 2011-07-29 2011-07-29 Groupe d'aubes

Country Status (1)

Country Link
EP (1) EP2551460A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106569407A (zh) * 2016-09-11 2017-04-19 国网浙江省电力公司电力科学研究院 一种基于振动梯度控制的汽轮机汽流激振在线治理方法
CN109973155A (zh) * 2019-04-18 2019-07-05 中国航发沈阳发动机研究所 一种预防涡轮转子叶片锯齿冠错位的方法及航空发动机

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1519898A (fr) * 1967-02-24 1968-04-05 Creusot Forges Ateliers Perfectionnements aux aubages torses mobiles de turbo-machines
FR2406074A1 (fr) * 1977-10-11 1979-05-11 Snecma Dispositif de securite pour machine tournante axiale
DE4015206C1 (fr) * 1990-05-11 1991-10-17 Mtu Muenchen Gmbh
EP0536575A1 (fr) * 1991-10-08 1993-04-14 Asea Brown Boveri Ag Bande de recouvrement pour roue de turbine axiale
US20040151582A1 (en) * 2002-08-03 2004-08-05 Faulkner Andrew Rowell Sealing of turbomachinery casing segments
EP1731713A2 (fr) * 2005-06-02 2006-12-13 The General Electric Company Procédés et arrangements pour le montage d' aubes de turbine comprenant des viroles et des fixations tangentielles en queue d'aronde
EP1939401A2 (fr) * 2006-12-19 2008-07-02 General Electric Company Procédés et appareils pour le transfert de charge dans des ensembles rotors
DE102008023326A1 (de) * 2008-05-13 2009-11-19 Mtu Aero Engines Gmbh Deckband für Laufschaufeln einer Strömungsmaschine und Strömungsmaschine
EP2230385A1 (fr) * 2008-01-16 2010-09-22 Mitsubishi Heavy Industries, Ltd. Pale de rotor de turbine
EP2275220A1 (fr) * 2009-07-10 2011-01-19 MTU Aero Engines AG Procédé de blindage de composants à partir d'une matière première à base de TiAl et composants correspondants

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1519898A (fr) * 1967-02-24 1968-04-05 Creusot Forges Ateliers Perfectionnements aux aubages torses mobiles de turbo-machines
FR2406074A1 (fr) * 1977-10-11 1979-05-11 Snecma Dispositif de securite pour machine tournante axiale
DE4015206C1 (fr) * 1990-05-11 1991-10-17 Mtu Muenchen Gmbh
EP0536575A1 (fr) * 1991-10-08 1993-04-14 Asea Brown Boveri Ag Bande de recouvrement pour roue de turbine axiale
US20040151582A1 (en) * 2002-08-03 2004-08-05 Faulkner Andrew Rowell Sealing of turbomachinery casing segments
EP1731713A2 (fr) * 2005-06-02 2006-12-13 The General Electric Company Procédés et arrangements pour le montage d' aubes de turbine comprenant des viroles et des fixations tangentielles en queue d'aronde
EP1939401A2 (fr) * 2006-12-19 2008-07-02 General Electric Company Procédés et appareils pour le transfert de charge dans des ensembles rotors
EP2230385A1 (fr) * 2008-01-16 2010-09-22 Mitsubishi Heavy Industries, Ltd. Pale de rotor de turbine
DE102008023326A1 (de) * 2008-05-13 2009-11-19 Mtu Aero Engines Gmbh Deckband für Laufschaufeln einer Strömungsmaschine und Strömungsmaschine
EP2275220A1 (fr) * 2009-07-10 2011-01-19 MTU Aero Engines AG Procédé de blindage de composants à partir d'une matière première à base de TiAl et composants correspondants

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106569407A (zh) * 2016-09-11 2017-04-19 国网浙江省电力公司电力科学研究院 一种基于振动梯度控制的汽轮机汽流激振在线治理方法
CN109973155A (zh) * 2019-04-18 2019-07-05 中国航发沈阳发动机研究所 一种预防涡轮转子叶片锯齿冠错位的方法及航空发动机
CN109973155B (zh) * 2019-04-18 2021-10-22 中国航发沈阳发动机研究所 一种预防涡轮转子叶片锯齿冠错位的方法及航空发动机

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