EP0203287A1 - Elément supprimant les vibrations des aubes de turbomachines - Google Patents

Elément supprimant les vibrations des aubes de turbomachines Download PDF

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Publication number
EP0203287A1
EP0203287A1 EP86103322A EP86103322A EP0203287A1 EP 0203287 A1 EP0203287 A1 EP 0203287A1 EP 86103322 A EP86103322 A EP 86103322A EP 86103322 A EP86103322 A EP 86103322A EP 0203287 A1 EP0203287 A1 EP 0203287A1
Authority
EP
European Patent Office
Prior art keywords
blades
supports
blade
rotor
damping element
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
EP86103322A
Other languages
German (de)
English (en)
Other versions
EP0203287B1 (fr
Inventor
Josef Bättig
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.)
BBC Brown Boveri AG Switzerland
Original Assignee
BBC Brown Boveri AG Switzerland
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 BBC Brown Boveri AG Switzerland filed Critical BBC Brown Boveri AG Switzerland
Publication of EP0203287A1 publication Critical patent/EP0203287A1/fr
Application granted granted Critical
Publication of EP0203287B1 publication Critical patent/EP0203287B1/fr
Expired 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
    • F01D5/14—Form or construction
    • F01D5/16—Form or construction for counteracting 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
    • 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
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • the invention relates to a damping element for free-standing blades of a turbomachine, in which the rotor blades fastened in the rotor are connected to one another, preferably in the radially outer region.
  • Freestanding blades both from axially flowed turbines and from radially flowed compressors or turbines, are - at risk of vibration.
  • the individual blade of such turbomachines carries out natural vibrations which depend on the type of vibration to which it is exposed; Tangential bend, axial bend or torsion.
  • the invention is therefore based on the object of providing a suitable, easily installed damping system for all types of free-standing blades.
  • connection between two blades consists of an elastically deformable plate which is curved toward the rotor center and which is latched into anchorages on the suction side of one and on the pressure side of a second adjacent blade.
  • the advantage of the new measure in addition to the extraordinary simplicity, is to be seen in particular in the fact that the curved plates can be made relatively thin and thus have little impact on the flow, since the lateral stresses reduce the bending stresses.
  • the weakening of the blade cross-section is significantly less if the plates are anchored in recesses in the blade.
  • the plates are preformed with a double curvature. On the one hand, this simplifies the geometry of the anchoring in the blades and, on the other hand, maintains - the platelets a perfect guidance both through their overlying underside and through the almost play-free top side. Even with a pure two-point support, they cannot tip out of the anchorages.
  • the plates are oval and have two circular supports on their narrow sides.
  • This type of support allows axial assembly, in which the plates can only be deformed very little elastically before they snap into the corresponding receptacles in the blades.
  • this type of installation also enables relatively deep recesses in the bucket walls.
  • the platelets are essentially triangular and are therefore equipped with three supports, preferably one of the supports on the suction side and the two further supports on the pressure side of the blades, then a stable position is achieved due to the only three pressure points. If, moreover, seen in the axial direction, the support on the suction side of the blade is arranged between the two supports on the pressure side, then in the case of twisted blades the plates prevent the blades from unwinding during operation.
  • FIG. 1 The blading partially shown in FIG. 1 is that of a one-piece turbine impeller of an exhaust gas turbocharger.
  • the impeller consists essentially of the turbine disc 1, the twisted blades 2 integrated with it and the damping elements clamped between the blades, which are designed as plates 3. Because of the prevailing centrifugal force and temperature conditions, these platelets are made from a nickel-based alloy, for example from the material known under the brand name Nymonic 90. According to FIG. 2, they are oval, which also means elliptical-like shapes or rectangles with rounded, narrow sides. With their semi-circular supports 4 on both sides, they lie in correspondingly shaped recesses 5, 6 on the one hand in the suction side 2 'of a first blade, on the other hand in the pressure side 2 "of a second adjacent blade. The recesses can be machined out of the blades or, as in the present case can be cast by integral wheels directly with the impeller.
  • the plates preformed during production have a double curvature and are mounted in such a way that the curvature belly is directed towards the center of the turbine disk 1 (FIG. 1, FIG. 3).
  • the procedure for assembling the platelet is as follows: 'In the axial direction, the platelet is inserted between the inlet profiles of two adjacent blades, brought into abutment in the recess 5 on the suction side 2' and then pivoted into the recess 6 on the pressure side 2 " The recesses 5 and 6 are completely filled, so that the flow-limiting walls have no cavemen.
  • the required supporting force during operation results on the one hand from the assembly preload and on the other hand as a result of the elastic deformation of the plate and the blade (torsion). I.e. the blade is thereby subjected to torsion.
  • FIG. 4 and 5 show anchorages as they are possible when using simply curved plates 3 '.
  • the anchorage according to FIG. 4 is carried out in a not very deep recess 7 attached to the airfoil, while according to FIG. 5 the plate 3 'is supported on the underside of a nose 8 cast onto the airfoil.
  • Both solutions are suitable for assembly in the radial direction, in which the plates 3 'are elastically deformed when pressed in between the blades and then snap into the associated anchoring.
  • the centrifugal force has a caulking effect during operation, so that the platelets cannot detach from the respective anchoring.
  • Platelets of simple curvature and corresponding anchors can advantageously be used in the variant shown in FIG. 6.
  • the plate 3 'here has essentially a triangular shape with the three supports 4a, 4b and 4c.
  • the support 4a is supported on the suction side of the blade in the recess 7a; the supports 4b and 4c are anchored in the recesses 7b and 7c on the pressure side of the adjacent blade.
  • the connection 4a / 7a lies between the two connections 4b / 7b and 4c / 7c, which results in the advantage already mentioned that blade torsion due to centrifugal force is prevented.
  • every second plate could be arranged on a smaller or larger radius.
  • the pressure-side and suction-side recesses of a blade would then no longer be in the same radial blade plane and would therefore have an even less weakening of the cross-section.
  • the new measure can also be used in the inlet section of radial compressor wheels, where it can replace the complex, zigzag-shaped damper wires or, if necessary, the even more complex cover disk binding.

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)
  • Gears, Cams (AREA)
  • Supercharger (AREA)
EP86103322A 1985-05-31 1986-03-12 Elément supprimant les vibrations des aubes de turbomachines Expired EP0203287B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH2309/85A CH667493A5 (de) 1985-05-31 1985-05-31 Daempfungselement fuer freistehende turbomaschinenschaufeln.
CH2309/85 1985-05-31

Publications (2)

Publication Number Publication Date
EP0203287A1 true EP0203287A1 (fr) 1986-12-03
EP0203287B1 EP0203287B1 (fr) 1989-06-07

Family

ID=4230789

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86103322A Expired EP0203287B1 (fr) 1985-05-31 1986-03-12 Elément supprimant les vibrations des aubes de turbomachines

Country Status (9)

Country Link
US (1) US4734010A (fr)
EP (1) EP0203287B1 (fr)
JP (1) JPS61277802A (fr)
KR (1) KR910003259B1 (fr)
CN (1) CN1003464B (fr)
CH (1) CH667493A5 (fr)
DE (1) DE3663837D1 (fr)
IN (1) IN167278B (fr)
SU (1) SU1477253A3 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2251897A (en) * 1991-01-15 1992-07-22 Rolls Royce Plc Bladed rotor
GB2441543A (en) * 2006-09-07 2008-03-12 Rolls Royce Plc A bridging element for reducing vibrations in an array of elongate components
WO2011081761A1 (fr) * 2009-12-14 2011-07-07 Siemens Energy, Inc. Dispositif d'amortissement de pale de turbine présentant chargement réglé
WO2017184138A1 (fr) * 2016-04-21 2017-10-26 Siemens Aktiengesellschaft Ensemble d'amortisseur préchargé destiné à des pales de turbine
WO2018157958A1 (fr) * 2017-03-01 2018-09-07 Siemens Aktiengesellschaft Étage de turbine muni d'un élément d'accouplement

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5201850A (en) * 1991-02-15 1993-04-13 General Electric Company Rotor tip shroud damper including damper wires
US5460488A (en) * 1994-06-14 1995-10-24 United Technologies Corporation Shrouded fan blade for a turbine engine
EP1557534A1 (fr) * 2004-01-20 2005-07-27 Siemens Aktiengesellschaft Aube de turbine à gaz et turbine à gaz avec une telle aube
US7758311B2 (en) * 2006-10-12 2010-07-20 General Electric Company Part span shrouded fan blisk
JP2009007981A (ja) * 2007-06-27 2009-01-15 Toshiba Corp 蒸気タービン用長動翼翼列の中間固定支持構造及び蒸気タービン
FR2922263B1 (fr) * 2007-10-11 2009-12-11 Snecma Stator de turbine pour turbomachine d'aeronef integrant un dispositif d'amortissement de vibrations
US8540488B2 (en) * 2009-12-14 2013-09-24 Siemens Energy, Inc. Turbine blade damping device with controlled loading
USRE45690E1 (en) 2009-12-14 2015-09-29 Siemens Energy, Inc. Turbine blade damping device with controlled loading
JP5558095B2 (ja) * 2009-12-28 2014-07-23 株式会社東芝 タービン動翼翼列および蒸気タービン
US8398374B2 (en) * 2010-01-27 2013-03-19 General Electric Company Method and apparatus for a segmented turbine bucket assembly
US8790082B2 (en) * 2010-08-02 2014-07-29 Siemens Energy, Inc. Gas turbine blade with intra-span snubber
TWI418708B (zh) * 2011-03-25 2013-12-11 Delta Electronics Inc 葉輪結構
US9506353B2 (en) * 2012-12-19 2016-11-29 United Technologies Corporation Lightweight shrouded fan blade
US10465531B2 (en) 2013-02-21 2019-11-05 General Electric Company Turbine blade tip shroud and mid-span snubber with compound contact angle
CN103541459B (zh) * 2013-11-08 2015-07-29 同济大学 一种混合消能减振装置
RU178381U1 (ru) * 2017-08-16 2018-04-02 ФЕДЕРАЛЬНОЕ ГОСУДАРСТВЕННОЕ БЮДЖЕТНОЕ ОБРАЗОВАТЕЛЬНОЕ УЧРЕЖДЕНИЕ ВЫСШЕГО ОБРАЗОВАНИЯ "Брянский государственный технический университет" Амортизатор для гашения вибраций статора турбореактивного двигателя
PT3604792T (pt) * 2018-08-03 2022-01-31 Ge Renewable Tech Tampa preformada com perfis interpás para turbinas hidráulicas

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH334774A (de) * 1954-02-05 1958-12-15 Gen Electric Co Ltd Turbinenrad für Axial-Dampfturbinen
DE1161912B (de) * 1959-12-07 1964-01-30 Gen Electric Co Ltd Axial-Dampfturbinen-Laufrad
FR1363969A (fr) * 1963-04-11 1964-06-19 Alsthom Cgee Entretoises pour aubes de turbine
DE1426780A1 (de) * 1962-08-22 1969-05-08 Ass Elect Ind Turbinenlaeufer

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1270232A (en) * 1917-11-09 1918-06-18 Gen Electric Elastic-fluid turbine.
US1378464A (en) * 1920-10-29 1921-05-17 Gen Electric Elastic-fluid turbine
US1469901A (en) * 1922-04-18 1923-10-09 Westinghouse Electric & Mfg Co Turbine blading
DE563458C (de) * 1929-02-10 1932-11-05 Siemens Schuckertwerke Akt Ges Versteifung von Dampfturbinenschaufeln
GB910239A (en) * 1959-12-07 1962-11-14 Gen Electric Co Ltd Improvements in or relating to steam turbines
US3451654A (en) * 1967-08-25 1969-06-24 Gen Motors Corp Blade vibration damping
DE2117387A1 (de) * 1970-04-13 1971-11-04 Mini Of Aviat Supply Beschaufelter Rotor für ein Gasturbinenstrahltriebwerk
US3751182A (en) * 1971-08-20 1973-08-07 Westinghouse Electric Corp Guide vanes for supersonic turbine blades
JPS50158705A (fr) * 1974-06-17 1975-12-22
JPS5692303A (en) * 1979-12-24 1981-07-27 Mitsubishi Heavy Ind Ltd Structure of rotor blade for turbine or the like
JPS57168007A (en) * 1981-04-08 1982-10-16 Toshiba Corp Turbine runner
GB2112466A (en) * 1981-12-30 1983-07-20 Rolls Royce Rotor blade vibration damping

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH334774A (de) * 1954-02-05 1958-12-15 Gen Electric Co Ltd Turbinenrad für Axial-Dampfturbinen
DE1161912B (de) * 1959-12-07 1964-01-30 Gen Electric Co Ltd Axial-Dampfturbinen-Laufrad
DE1426780A1 (de) * 1962-08-22 1969-05-08 Ass Elect Ind Turbinenlaeufer
FR1363969A (fr) * 1963-04-11 1964-06-19 Alsthom Cgee Entretoises pour aubes de turbine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
MACHINE DESIGN, Band 34, 19. Juli 1962, Seite 165, Penton, US; "Arched spacers absorb vibration" *

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2251897A (en) * 1991-01-15 1992-07-22 Rolls Royce Plc Bladed rotor
GB2251897B (en) * 1991-01-15 1994-11-30 Rolls Royce Plc A rotor
GB2441543A (en) * 2006-09-07 2008-03-12 Rolls Royce Plc A bridging element for reducing vibrations in an array of elongate components
GB2441543B (en) * 2006-09-07 2008-07-23 Rolls Royce Plc An array of components
WO2011081761A1 (fr) * 2009-12-14 2011-07-07 Siemens Energy, Inc. Dispositif d'amortissement de pale de turbine présentant chargement réglé
US8616848B2 (en) 2009-12-14 2013-12-31 Siemens Energy, Inc. Turbine blade damping device with controlled loading
WO2017184138A1 (fr) * 2016-04-21 2017-10-26 Siemens Aktiengesellschaft Ensemble d'amortisseur préchargé destiné à des pales de turbine
WO2018157958A1 (fr) * 2017-03-01 2018-09-07 Siemens Aktiengesellschaft Étage de turbine muni d'un élément d'accouplement

Also Published As

Publication number Publication date
CH667493A5 (de) 1988-10-14
SU1477253A3 (ru) 1989-04-30
JPS61277802A (ja) 1986-12-08
CN86103683A (zh) 1986-11-26
CN1003464B (zh) 1989-03-01
DE3663837D1 (en) 1989-07-13
KR910003259B1 (ko) 1991-05-25
EP0203287B1 (fr) 1989-06-07
IN167278B (fr) 1990-09-29
US4734010A (en) 1988-03-29
KR860009213A (ko) 1986-12-20

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