US3377050A - Shrouded rotor blades - Google Patents

Shrouded rotor blades Download PDF

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Publication number
US3377050A
US3377050A US637586A US63758667A US3377050A US 3377050 A US3377050 A US 3377050A US 637586 A US637586 A US 637586A US 63758667 A US63758667 A US 63758667A US 3377050 A US3377050 A US 3377050A
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United States
Prior art keywords
blades
wire
blade
vibration
turbine
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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 - Lifetime
Application number
US637586A
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English (en)
Inventor
Guy Kenneth Ronald
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Bristol Siddeley Engines Ltd
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Bristol Siddeley Engines Ltd
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Filing date
Publication date
Application filed by Bristol Siddeley Engines Ltd filed Critical Bristol Siddeley Engines Ltd
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Publication of US3377050A publication Critical patent/US3377050A/en
Anticipated expiration legal-status Critical
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    • 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
    • F01D5/24—Blade-to-blade connections, e.g. for damping vibrations using wire or the like
    • 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
    • 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

  • ABSTRACT OF THE DISCLOSURE A turbine rotor having a disc supporting at its rim a ring of blades each provided at its tip with a shroud being apertured to provide a ring of circumferential connecting passages and at least one length of a flexible elongate member extending through the connecting passages to constitute a frictional connection between successive blades when being urged against the walls of the apertures by centrifugal force during operation of the rotor.
  • the disclosure of this invention relates to a turbine rotor blade which is provided with a tip shroud the radially outer side of which is apertured to receive a circumferential wire for resisting blade vibration.
  • wire is used herein in a broad sense to mean a flexible elongate member.
  • a rotor blade is provided at its tip with a shroud which is apertured to receive a circumferentially-extending wire.
  • a turbine rotor comprises a disc supporting at its rim a ring of blades, each blade being provided at its tip with a shroud supporting at least one fin-shaped member which projects from the radially outer side of the shroud, the fin-shaped members of the shrouds being apertured to provide a ring of circumferential connecting passages, and at least one length of flexible elongate member which extends through the connecting passages.
  • One object of this invention is to provide wire lacing for gas turbine blades which lies outside the main stream of gas through the turbine and is located to take full advantage of the effect of centrifugal force.
  • FIGURE 1 is a perspective view, partly in section, of the shrouded blade tips of two adjacent gas turbine blades and shows one form of apertured member for a vibrationresisting wire
  • FIGURE 2 is, on a larger scale, a perspective view taken from another angle of one of the tip shrouds,
  • FIGURE 3 is a perspective view, partly in section, of the shrouded blade tips of another two adjacent gas turbine blades and shows an alternative form of apertured member for a vibration-resisting wire,
  • FIGURE 4 is a perspective view taken from another angle of one of the tip shrouds of FIGURE 3.
  • FIGURE 5 is a perspective view of the shrouded blade tip of a gas turbine blade with a further form of shroud for receiving vibration-resisting wires,
  • FIGURE 6 is, on a smaller scale, a view of the upstream face of a bladed turbine disc provided with shrouded rotor blades according to FIGURE 5, and
  • FIGURE 7 is, on a different scale, a developed view in section of part of FIGURE 6 taken in the direction of the arrow 8.
  • a circular row of axial flow gas turbine rotor blades carried at the periphery of a rotor disc has each blade 10 provided at its tip with a 3,377,050 Patented Apr. 9, 1968 shroud 11 which extends at right angles to the aerofoil portion 12 of the blade.
  • shroud 11 which extends at right angles to the aerofoil portion 12 of the blade.
  • Each shroud has on its side remote from the aerofoil portion 12 a number of circumferentially-extending sealing fins 13, 14, 15- which cooperate with opposing turbine stator structure (not shown) to provide gas seals in known manner.
  • the central fin 14 is widened at its base where an elongate circumferential passage 16 is formed to receive one or more wires 17 for reducing blade vibration. When the blades are assembled together, the passages 16 join up to form a ring of circumferential connecting passages for the wire.
  • FIGURES 3 and 4 the arrangement is structurally similar except that the single apertured member represented in part by the central fin 14 is replaced by a plurality of circumferentially-spaced apertured lugs 20 through which a wire 21 is threaded as shown.
  • the substantially continuous ring of central fins 14 will prevent outward bulging of the wire 17 under centrifugal loading and damping of the blades will be caused by friction between the wire and that portion of each rib 14 against which the wire is urged by centrifugal force.
  • Such friction damping is promoted by the location of the wire beyond the aerofoil portion of the blade, at which location the loading on the wire due to centrifugal force is at its maximum for any given operational conditions, as also may be the amplitude of blade vibration, depending on the mode of vibration.
  • the Wire which is non-continuous would normally be of a material which is sufliciently flexible to bulge outwards under centrifugal force between the circumferentially-spaced lugs 20. Such bulging would oppose relative circumferential movement between wire and blades and so reduce friction damping between those members.
  • the vibration of blades wired together as in FIGURE 3 would have a greatly reduced amplitude, compared with vibrating blades not wired together, because the blades on any one length of outwardly bulged wire would be forced by the wire to have the same phase of vibration as one another.
  • the wire must be noncontinuous to permit bulging.
  • the spacing between the lugs 20 can be chosen to vary the unsupported span of the wire and thus lessen the uneven application along the wire of the centrifugal stress, so matching a wire of given strength and stiffness to the blade clamping requirements.
  • Another reason for making the wire non-continuous is to allow it to accommodate radial thermal expansion of the blades, a consideration which also applies to the embodiment of FIGURE 1.
  • the non-continuous wire may consist of more than one length, e.g. four lengths which between them form substantially a ring.
  • the wire may consist of a plurality of lengths alongside one another to permit friction rubbing between wire lengths.
  • a turbine rotor disc 25 supports at its outer rim a ring of blades 26 provided with tip shrouds 27.
  • Each shroud is formed on its radially outer side with three sealing fins 28, 29, 30 which extend circumferentially and are spaced apart in the chordwise direction.
  • the fins 28, 30 which are located adjacent the leading and trailing edges respectively of each shroud are thickened and formed with circumferential passages 31 which connect up to provide co-axial annular passages.
  • Wires 32 of circular cross-section are passed through the passages 31 to form flexible vibration-resisting rings.
  • Each ring of wire may be made continuous or its ends left unconnected.
  • the rotational axis 33 of the turbine is indicated in FIGURE 7.
  • chordwise-spaced Wires restrict the blades against flexural vibration, i.e. vibration normal to the chordwise direction, against edgewise vibration, i.e. vibration substantially in the chordwse direction, and against torsional vibration.
  • the wire lies outside the main flow passage through the turbine and thus is not only shielded from the main gas flow but also does not obstruct it.
  • the blade aerofoil portions 12 are not weakened 'by holes for the Wires.
  • a further important advantage- is that should a blade failure occur, eg at the aerofoil portion adjacent the blade platform, the outwardly escaping portion of the blade must overcome the wire before it can penetrate the turbine casing. In this manner the invention may assist the containment of escaping rotor blade parts.
  • the invention is also applicable to axial flow compressor blades of gas turbine engines and to steam turbine blades.
  • a rotor for a bladed fluid flow machine comprising an annular row of blades, each blade including at the tip thereof a shroud so dimensioned that there is a clearance between the shrouds of adjacent blades, the shrouds each including a circumferential aperture registering with the apertures of the adjacent shrouds, at least one elongate member placed into the apertures of successive blades so as to constitute a frictional connection between successive blades when being urged against the walls of the apertures by centrifugal force during operation.

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)
US637586A 1966-06-21 1967-05-10 Shrouded rotor blades Expired - Lifetime US3377050A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB27564/66A GB1195012A (en) 1966-06-21 1966-06-21 Rotor for Bladed Fluid Flow Machines.

Publications (1)

Publication Number Publication Date
US3377050A true US3377050A (en) 1968-04-09

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Family Applications (1)

Application Number Title Priority Date Filing Date
US637586A Expired - Lifetime US3377050A (en) 1966-06-21 1967-05-10 Shrouded rotor blades

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US (1) US3377050A (de)
DE (1) DE1551173B1 (de)
GB (1) GB1195012A (de)

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3459417A (en) * 1965-11-10 1969-08-05 B P Prezemyslu Hutniczego Bipr Furnace for the production of steel
US3575523A (en) * 1968-12-05 1971-04-20 Us Navy Labyrinth seal for axial flow fluid machines
US3601500A (en) * 1968-08-28 1971-08-24 Rolls Royce Rotor assembly for a fluid flow machine
US3981615A (en) * 1974-11-14 1976-09-21 Groupe Europeen Pour La Technique Des Turbines A Vapeur G.E.T.T. Continuous connection device for the mobile blades of a turbo-machine
US4492517A (en) * 1983-01-06 1985-01-08 General Electric Company Segmented inlet nozzle for gas turbine, and methods of installation
US4576551A (en) * 1982-06-17 1986-03-18 The Garrett Corporation Turbo machine blading
US4699569A (en) * 1985-07-05 1987-10-13 Bbc Brown, Boveri & Company, Limited Rotor blade ring of an axial flow turbomachine
CH666326A5 (en) * 1984-09-19 1988-07-15 Bbc Brown Boveri & Cie Turbine rotor blades with shroud plates at outer ends - have adjacent plates connected via damping circumferential wire through bores in plates
US5201850A (en) * 1991-02-15 1993-04-13 General Electric Company Rotor tip shroud damper including damper wires
JPH068601B2 (ja) 1983-04-25 1994-02-02 ゼネラル・エレクトリック・カンパニイ 回転子及びバケット集成体
US5645402A (en) * 1996-04-10 1997-07-08 Solar Turbines Incorporated Turbine blade vibration dampening
US20050129519A1 (en) * 2003-12-12 2005-06-16 General Elecric Company Center located cutter teeth on shrouded turbine blades
DE102007059220A1 (de) * 2007-12-07 2009-06-10 Rolls-Royce Deutschland Ltd & Co Kg Leitschaufelkranz für thermische Strömungsmaschinen, insbesondere Flugtriebwerke
US20090252610A1 (en) * 2008-04-04 2009-10-08 General Electric Company Turbine blade retention system and method
FR2960021A1 (fr) * 2010-05-12 2011-11-18 Snecma Roue mobile de turbomachine munie d'un jonc d'amortissement des vibrations
US20110299989A1 (en) * 2009-02-17 2011-12-08 Christoph Hermann Richter Blade union of a turbo machine
CN102947548A (zh) * 2010-05-05 2013-02-27 阿尔斯通技术有限公司 用于转子叶片的轻量围带翼片
US20130052032A1 (en) * 2010-01-26 2013-02-28 Herakles Vibration damper comprising a strip and jackets between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel
US20130170994A1 (en) * 2012-01-04 2013-07-04 General Electric Company Device and method for aligning tip shrouds
US20140023506A1 (en) * 2012-07-20 2014-01-23 General Electric Company Damper system and a turbine
JP2014114716A (ja) * 2012-12-07 2014-06-26 Mitsubishi Heavy Ind Ltd 翼振動減衰構造
US20150017003A1 (en) * 2013-03-07 2015-01-15 Rolls-Royce Corporation Gas turbine engine shrouded blade
US20180016918A1 (en) * 2016-07-13 2018-01-18 MTU Aero Engines AG Shrouded blade of a gas turbine engine
FR3113300A1 (fr) * 2020-08-06 2022-02-11 Safran Aircraft Engines Aubage de rotor de turbomachine
FR3137128A1 (fr) * 2022-06-22 2023-12-29 Safran Aircraft Engines Ensemble de turbomachine comportant des aubes portant des léchettes et un câble reliant les léchettes les unes aux autres

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4712977A (en) * 1984-07-02 1987-12-15 Gerfast Sten R Axial fan
DE4301656A1 (de) * 1993-01-22 1994-07-28 Bmw Rolls Royce Gmbh Turbinenschaufel-Anordnung
GB2409006B (en) 2003-12-11 2006-05-17 Rolls Royce Plc Tip sealing for a turbine rotor blade

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1165005A (en) * 1914-05-14 1915-12-21 Westinghouse Machine Co Blade construction for elastic-fluid turbines.
US1544318A (en) * 1923-09-12 1925-06-30 Westinghouse Electric & Mfg Co Turbine-blade lashing
US3025037A (en) * 1957-10-24 1962-03-13 Bert F Beckstrom Gas turbine
US3095138A (en) * 1957-05-28 1963-06-25 Studebaker Corp Rotating shroud
US3326523A (en) * 1965-12-06 1967-06-20 Gen Electric Stator vane assembly having composite sectors

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE485833C (de) * 1929-11-08 J A Maffei A G Verfahren zur Herstellung von Schauflungen fuer Turbomaschinen, insbesondere fuer Dampf- oder Gasturbinen
US1061648A (en) * 1910-08-27 1913-05-13 George Westinghouse Blades.
US1858067A (en) * 1930-10-21 1932-05-10 Gen Electric Elastic fluid turbine
US2220914A (en) * 1938-07-30 1940-11-12 Gen Electric Elastic fluid turbine bucket wheel
US2315642A (en) * 1942-01-16 1943-04-06 Westinghouse Electric & Mfg Co Turbine blade shroud fastening
GB623525A (en) * 1947-05-13 1949-05-18 Svenska Turbinfab Ab Vibration damper for blades of turbines and compressors
NL179681B (nl) * 1952-07-22 1955-12-15 Hitachi Shipbuilding Eng Co Inrichting voor het verbranden van afvalgassen.
GB989260A (en) * 1962-11-21 1965-04-14 Ass Elect Ind Improvements in or relating to the shrouding of the moving blades of turbines and axial-flow compressors

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1165005A (en) * 1914-05-14 1915-12-21 Westinghouse Machine Co Blade construction for elastic-fluid turbines.
US1544318A (en) * 1923-09-12 1925-06-30 Westinghouse Electric & Mfg Co Turbine-blade lashing
US3095138A (en) * 1957-05-28 1963-06-25 Studebaker Corp Rotating shroud
US3025037A (en) * 1957-10-24 1962-03-13 Bert F Beckstrom Gas turbine
US3326523A (en) * 1965-12-06 1967-06-20 Gen Electric Stator vane assembly having composite sectors

Cited By (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3459417A (en) * 1965-11-10 1969-08-05 B P Prezemyslu Hutniczego Bipr Furnace for the production of steel
US3601500A (en) * 1968-08-28 1971-08-24 Rolls Royce Rotor assembly for a fluid flow machine
US3575523A (en) * 1968-12-05 1971-04-20 Us Navy Labyrinth seal for axial flow fluid machines
US3981615A (en) * 1974-11-14 1976-09-21 Groupe Europeen Pour La Technique Des Turbines A Vapeur G.E.T.T. Continuous connection device for the mobile blades of a turbo-machine
US4576551A (en) * 1982-06-17 1986-03-18 The Garrett Corporation Turbo machine blading
US4492517A (en) * 1983-01-06 1985-01-08 General Electric Company Segmented inlet nozzle for gas turbine, and methods of installation
JPH068601B2 (ja) 1983-04-25 1994-02-02 ゼネラル・エレクトリック・カンパニイ 回転子及びバケット集成体
CH666326A5 (en) * 1984-09-19 1988-07-15 Bbc Brown Boveri & Cie Turbine rotor blades with shroud plates at outer ends - have adjacent plates connected via damping circumferential wire through bores in plates
US4699569A (en) * 1985-07-05 1987-10-13 Bbc Brown, Boveri & Company, Limited Rotor blade ring of an axial flow turbomachine
US5201850A (en) * 1991-02-15 1993-04-13 General Electric Company Rotor tip shroud damper including damper wires
US5645402A (en) * 1996-04-10 1997-07-08 Solar Turbines Incorporated Turbine blade vibration dampening
US20050129519A1 (en) * 2003-12-12 2005-06-16 General Elecric Company Center located cutter teeth on shrouded turbine blades
US6913445B1 (en) * 2003-12-12 2005-07-05 General Electric Company Center located cutter teeth on shrouded turbine blades
DE102007059220A1 (de) * 2007-12-07 2009-06-10 Rolls-Royce Deutschland Ltd & Co Kg Leitschaufelkranz für thermische Strömungsmaschinen, insbesondere Flugtriebwerke
US20090252610A1 (en) * 2008-04-04 2009-10-08 General Electric Company Turbine blade retention system and method
US8894370B2 (en) * 2008-04-04 2014-11-25 General Electric Company Turbine blade retention system and method
US20110299989A1 (en) * 2009-02-17 2011-12-08 Christoph Hermann Richter Blade union of a turbo machine
US20130052032A1 (en) * 2010-01-26 2013-02-28 Herakles Vibration damper comprising a strip and jackets between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel
US9188014B2 (en) * 2010-01-26 2015-11-17 Snecma Vibration damper comprising a strip and jackets between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel
US8967972B2 (en) * 2010-05-05 2015-03-03 Alstom Technology Ltd. Light weight shroud fin for a rotor blade
US20130058788A1 (en) * 2010-05-05 2013-03-07 Alstom Technology Ltd Light weight shroud fin for a rotor blade
JP2013525689A (ja) * 2010-05-05 2013-06-20 アルストム テクノロジー リミテッド ロータブレード用の軽量シュラウド
CN102947548A (zh) * 2010-05-05 2013-02-27 阿尔斯通技术有限公司 用于转子叶片的轻量围带翼片
CN102947548B (zh) * 2010-05-05 2016-01-20 阿尔斯通技术有限公司 用于转子叶片的轻量围带翼片
RU2541078C2 (ru) * 2010-05-05 2015-02-10 Альстом Текнолоджи Лтд Турбинная лопатка и способ ее изготовления
FR2960021A1 (fr) * 2010-05-12 2011-11-18 Snecma Roue mobile de turbomachine munie d'un jonc d'amortissement des vibrations
US20130170994A1 (en) * 2012-01-04 2013-07-04 General Electric Company Device and method for aligning tip shrouds
US8894368B2 (en) * 2012-01-04 2014-11-25 General Electric Company Device and method for aligning tip shrouds
US20140023506A1 (en) * 2012-07-20 2014-01-23 General Electric Company Damper system and a turbine
CN104471192A (zh) * 2012-07-20 2015-03-25 通用电气公司 封挡器系统和对应的涡轮
JP2014114716A (ja) * 2012-12-07 2014-06-26 Mitsubishi Heavy Ind Ltd 翼振動減衰構造
US20150017003A1 (en) * 2013-03-07 2015-01-15 Rolls-Royce Corporation Gas turbine engine shrouded blade
US9683446B2 (en) * 2013-03-07 2017-06-20 Rolls-Royce Energy Systems, Inc. Gas turbine engine shrouded blade
US20180016918A1 (en) * 2016-07-13 2018-01-18 MTU Aero Engines AG Shrouded blade of a gas turbine engine
US10544687B2 (en) * 2016-07-13 2020-01-28 MTU Aero Engines AG Shrouded blade of a gas turbine engine
FR3113300A1 (fr) * 2020-08-06 2022-02-11 Safran Aircraft Engines Aubage de rotor de turbomachine
FR3137128A1 (fr) * 2022-06-22 2023-12-29 Safran Aircraft Engines Ensemble de turbomachine comportant des aubes portant des léchettes et un câble reliant les léchettes les unes aux autres

Also Published As

Publication number Publication date
DE1551173B1 (de) 1971-07-08
GB1195012A (en) 1970-06-17

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