EP0214393B1 - Einrichtung zur Dämpfung von Schaufelschwingungen bei Turbomaschinen - Google Patents

Einrichtung zur Dämpfung von Schaufelschwingungen bei Turbomaschinen Download PDF

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Publication number
EP0214393B1
EP0214393B1 EP86109040A EP86109040A EP0214393B1 EP 0214393 B1 EP0214393 B1 EP 0214393B1 EP 86109040 A EP86109040 A EP 86109040A EP 86109040 A EP86109040 A EP 86109040A EP 0214393 B1 EP0214393 B1 EP 0214393B1
Authority
EP
European Patent Office
Prior art keywords
blades
magnet inserts
magnets
magnetic
cover plates
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.)
Expired
Application number
EP86109040A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0214393A1 (de
Inventor
Peter Dipl.-Ing. Novacek
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 EP0214393A1 publication Critical patent/EP0214393A1/de
Application granted granted Critical
Publication of EP0214393B1 publication Critical patent/EP0214393B1/de
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
    • F01D5/22—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
    • 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
    • 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 device for damping blade vibrations in turbomachinery.
  • a common and long-established precaution to combat the vibrations that occur is that the blades within a row of blades are connected to each other in packages by a damper wire.
  • the invention seeks to remedy this.
  • the invention as characterized in the claims, is based on the object of achieving a stiffening of the blade assembly against occurring vibrations of various excitation orders in a device of the type mentioned.
  • the individual magnets are to be set and fixed in such a way that their end faces not only lie against one another in the installed state, but also press against one another. This can be done by an excess compared to the actual distance between two blades and / or by a pre-torsion of the blades before they are installed.
  • Fig. 1 shows individual blades 1, 2, n in a row of blades, as they are usually arranged on a rotor disk, not shown here.
  • the blades 1, 2, n themselves consist of blade root 3, transition part 4, blade 5 and cover plate 6.
  • the cover plate configuration shown here is provided where slim blades 5 are used.
  • an improvement in efficiency is sought by covering plate 6 bridging the space between the end of airfoil 5 and the stator, also not shown, so that the different thermal expansions of airfoil 5 in the radial direction between the inflow and outflow sides of blades 1, 2 , n no longer play a relevant role in the dimensioning of the gap.
  • the cover plate 6 is also designed such that it engages in the stator like a labyrinth, as a result of which the flow losses there can be minimized.
  • Such cover plates 6 are particularly suitable for holding magnets 7, 8, which bridge the individually designed space between two adjacent blades.
  • the magnets 7, 8 used here are of a round design; other geometric shapes can also be used.
  • the magnetic sections protruding from the cover plates 6 each have an alternating polarity to the other adjacent section, so that the individual cover plates 6 adhere to one another via the attractive force of the individual pair magnets 7, 8.
  • a further intermediate stage, formed by preferably identical magnets 7, 8, is provided approximately at half the height of the airfoil. This precaution should only be taken into account for soft blades, because this means that flow losses are involved.
  • the intermediate stage can have a thickening in the region of the penetration of the magnet 8 by the blades 1, 2, n.
  • Fig. 2 shows the top view of a cover plate design, in which at least the opposite end faces 9a of the cover plates 9 are magnetic.
  • the attraction available here is particularly great.
  • Such an embodiment is therefore preferably used for blades that are highly susceptible to vibration.
  • the force of attraction is only fully available if the required manufacturing accuracy of the blades in general and the cover plates 9 in particular are strictly observed.
  • cover plates 10 shown in FIG. 3 In contrast, the manufacturing accuracy of the cover plates 10 shown in FIG. 3 is no longer in the foreground.
  • the individual cover plates 10 carry magnetic inserts 11, 12 which lie against one another alone.
  • the cover plates 10 are also set back in this area. It can be provided that the individual magnet inserts 11, 12 can be adjusted so that their positioning can only be carried out after the assembly of the blades 1, 2, n.
  • the embodiment according to FIG. 4 pursues similar goals.
  • the individual magnetic inserts 14, 15 can be adjusted relative to one another in such a way that their magnetic head parts abut one another.
  • the rhomboidal shape of the cover plates 13 offers advantages when installing the blades 1, 2, n: since the plane of alignment of the cover plate flanks corresponds to that of the blade root, the blades 1, 2, ⁇ can be inserted into the rotor disk without subsequent alignment.
  • the variant shown in Fig. 5 is characterized in that the cover plates 16 at their edge zones with two magnetic inserts 17, 19 and. 18, 20 are equipped. While in the area of the blade flow, the magnetic inserts 19, 20 according to the conventional direction of polarity? / e are arranged, the other edge zone has magnetic inserts 17, 18 which abut one another with poles of the same name ⁇ / ⁇ or e / e.
  • This arrangement can also be used to achieve a circumferential bracing which, in combination with the force direction of the magnetic forces acting in reverse on the other side of the cover plates 16, results in good elasticity against shock-like vibrations.
  • uniform polarity e / e and / or e / e can also be provided in all the examples explained above.

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)
  • Permanent Field Magnets Of Synchronous Machinery (AREA)
EP86109040A 1985-08-31 1986-07-02 Einrichtung zur Dämpfung von Schaufelschwingungen bei Turbomaschinen Expired EP0214393B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH373085 1985-08-31
CH3730/85 1985-08-31

Publications (2)

Publication Number Publication Date
EP0214393A1 EP0214393A1 (de) 1987-03-18
EP0214393B1 true EP0214393B1 (de) 1989-12-13

Family

ID=4262270

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86109040A Expired EP0214393B1 (de) 1985-08-31 1986-07-02 Einrichtung zur Dämpfung von Schaufelschwingungen bei Turbomaschinen

Country Status (7)

Country Link
US (1) US4722668A (xx)
EP (1) EP0214393B1 (xx)
JP (1) JP2574257B2 (xx)
DE (1) DE3667521D1 (xx)
HR (1) HRP920469B1 (xx)
PL (1) PL152331B1 (xx)
YU (1) YU45358B (xx)

Families Citing this family (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4767273A (en) * 1987-02-24 1988-08-30 Westinghouse Electric Corp. Apparatus and method for reducing blade flop in steam turbine
US4815938A (en) * 1987-12-24 1989-03-28 Westinghouse Electric Corp. Shroud gap control for integral shrouded blades
FR2662784B1 (fr) * 1990-06-05 1992-08-14 Snecma Ensemble d'injection pour turbomachine, comprenant un bol de prevaporisation.
US5490759A (en) * 1994-04-28 1996-02-13 Hoffman; Jay Magnetic damping system to limit blade tip vibrations in turbomachines
DE19505389A1 (de) * 1995-02-17 1996-08-22 Abb Research Ltd Schwingungsdämpfung für Turbinenschaufeln
GB9609721D0 (en) * 1996-05-09 1996-07-10 Rolls Royce Plc Vibration damping
FR2753368B1 (fr) * 1996-09-13 1999-01-08 Chauvin Jean Luc Cage d'osteosynthese expansive
JP4058906B2 (ja) * 1997-09-05 2008-03-12 株式会社日立製作所 蒸気タービン
US5967749A (en) * 1998-01-08 1999-10-19 Electric Boat Corporation Controllable pitch propeller arrangement
DE19937146A1 (de) * 1999-08-06 2001-02-08 Abb Research Ltd Magnetische Vorrichtung zur Dämpfung von Schaufelschwingungen bei Turbomaschinen
US6568908B2 (en) 2000-02-11 2003-05-27 Hitachi, Ltd. Steam turbine
US6371727B1 (en) 2000-06-05 2002-04-16 The Boeing Company Turbine blade tip shroud enclosed friction damper
US6482533B2 (en) 2001-03-05 2002-11-19 The Boeing Company Article having imbedded cavity
US6752594B2 (en) 2002-02-07 2004-06-22 The Boeing Company Split blade frictional damper
US6699015B2 (en) 2002-02-19 2004-03-02 The Boeing Company Blades having coolant channels lined with a shape memory alloy and an associated fabrication method
GB0410778D0 (en) * 2004-05-13 2004-06-16 Rolls Royce Plc Blade arrangement
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
EP2072755A1 (de) * 2007-12-21 2009-06-24 Siemens Aktiengesellschaft Magnetische Vorrichtung zur Dämpfung von Schaufelschwingungen bei Strömungsmaschinen
EP2253801A1 (en) * 2009-05-12 2010-11-24 Alstom Technology Ltd Rotor blades with vibration damping system
DE102009032549A1 (de) 2009-07-10 2011-01-13 Mtu Aero Engines Gmbh Verfahren zum Mindern von Schwingungsamplituden
CH704127A1 (de) * 2010-11-24 2012-05-31 Alstom Technology Ltd Verfahren zum beeinflussen, insbesondere dämpfen bzw. unterdrücken von während des betriebes auftretenden mechanischen schwingungen in einer turbomaschinenschaufel, turbomaschinenschaufel zur durchführung des verfahrens sowie piezoelektrisches dämpfungselement zum einbau in eine solche turbomaschinenschaufel.
US20120195742A1 (en) * 2011-01-28 2012-08-02 Jain Sanjeev Kumar Turbine bucket for use in gas turbine engines and methods for fabricating the same
US8894368B2 (en) * 2012-01-04 2014-11-25 General Electric Company Device and method for aligning tip shrouds
US10465531B2 (en) 2013-02-21 2019-11-05 General Electric Company Turbine blade tip shroud and mid-span snubber with compound contact angle
EP2803821A1 (en) 2013-05-13 2014-11-19 Siemens Aktiengesellschaft Blade device, blade system, and corresponding method of manufacturing a blade system
US20150176413A1 (en) * 2013-12-20 2015-06-25 General Electric Company Snubber configurations for turbine rotor blades
JP6270531B2 (ja) * 2014-02-21 2018-01-31 三菱日立パワーシステムズ株式会社 動翼体及び回転機械
EP2924245B1 (en) 2014-03-24 2017-03-01 General Electric Technology GmbH Steam turbine with resonance chamber
US10371050B2 (en) * 2014-12-23 2019-08-06 Rolls-Royce Corporation Gas turbine engine with rotor blade tip clearance flow control
US10577940B2 (en) * 2017-01-31 2020-03-03 General Electric Company Turbomachine rotor blade
GB201900378D0 (en) * 2019-01-11 2019-02-27 Rolls Royce Plc Electric machine

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US2198784A (en) * 1937-11-27 1940-04-30 Westinghouse Electric & Mfg Co Turbine blade vibration damper
US2430140A (en) * 1945-04-06 1947-11-04 Northrop Hendy Company Turbine blade and mounting
US2906899A (en) * 1955-10-08 1959-09-29 Geneslay Raymond Henri Joseph Damping systems
US2942843A (en) * 1956-06-15 1960-06-28 Westinghouse Electric Corp Blade vibration damping structure
DE1159965B (de) * 1961-08-10 1963-12-27 Bbc Brown Boveri & Cie Einrichtung zur Schwingungsdaempfung an einem Turbinen- oder Verdichter-Schaufelkranz
DE1299004B (de) * 1965-01-19 1969-07-10 Bbc Brown Boveri & Cie Einrichtung zur Schwingungsdaempfung an einem Turbinen-oder Verdichterschaufelkranz
FR1374917A (fr) * 1963-11-21 1964-10-09 Ass Elect Ind Perfectionnements aux déflecteurs d'étanchéité des aubes mobiles de turbines et de compresseurs à écoulement axial
GB1186240A (en) * 1967-12-22 1970-04-02 Rolls Royce Improvements in Blades for Fluid Flow Machines.
GB1276100A (en) * 1968-12-16 1972-06-01 Rolls Royce Bladed member for a fluid flow machine
US3752599A (en) * 1971-03-29 1973-08-14 Gen Electric Bucket vibration damping device
FR2329845A1 (fr) * 1975-10-28 1977-05-27 Europ Turb Vapeur Disposition de liaison continue des aubes mobiles d'une turbo-machine
JPS5510561Y2 (xx) * 1975-10-30 1980-03-07
US4200003A (en) * 1976-03-29 1980-04-29 Facet Enterprises, Inc. Magnetic viscous damper
JPS5392007A (en) * 1977-01-24 1978-08-12 Toshiba Corp Coupling device for movable vane
JPS54125307A (en) * 1978-03-24 1979-09-28 Toshiba Corp Connecting device for turbine movable blades
JPS56147940A (en) * 1980-04-15 1981-11-17 Toshiba Corp Vibration damper for vertical body of rotation
JPS56165777A (en) * 1980-05-21 1981-12-19 Mitsubishi Electric Corp Vertical windmill
JPS5738602A (en) * 1980-08-20 1982-03-03 Toshiba Corp Driving blade connecting apparatus
JPS57103302U (xx) * 1980-12-18 1982-06-25
DE3136320C2 (de) * 1981-09-12 1983-10-20 Deutsche Forschungs- und Versuchsanstalt für Luft- und Raumfahrt e.V., 5000 Köln Verfahren und Vorrichtung zur Unterdrückung des Außenlast-Tragflügel-Flatterns von Flugzeugen

Also Published As

Publication number Publication date
EP0214393A1 (de) 1987-03-18
YU148086A (en) 1990-04-30
YU45358B (en) 1992-05-28
US4722668A (en) 1988-02-02
JPS6255401A (ja) 1987-03-11
DE3667521D1 (de) 1990-01-18
HRP920469B1 (en) 1996-04-30
PL260782A1 (en) 1987-08-24
PL152331B1 (en) 1990-12-31
JP2574257B2 (ja) 1997-01-22

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