EP0095409B1 - Dispositif d'amortissement pour aubes dans un rotor d'une turbomachine - Google Patents

Dispositif d'amortissement pour aubes dans un rotor d'une turbomachine Download PDF

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Publication number
EP0095409B1
EP0095409B1 EP83400980A EP83400980A EP0095409B1 EP 0095409 B1 EP0095409 B1 EP 0095409B1 EP 83400980 A EP83400980 A EP 83400980A EP 83400980 A EP83400980 A EP 83400980A EP 0095409 B1 EP0095409 B1 EP 0095409B1
Authority
EP
European Patent Office
Prior art keywords
blade
damping
damping device
blades
platforms
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
EP83400980A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0095409A1 (fr
Inventor
Jean Georges Bouiller
Jean-Claude Lucien Delonge
Marcel Louis Antoine Rigo
Didier Gilbert Zietek
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0095409A1 publication Critical patent/EP0095409A1/fr
Application granted granted Critical
Publication of EP0095409B1 publication Critical patent/EP0095409B1/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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/38—Retaining components in desired mutual position by a spring, i.e. spring loaded or biased towards a certain position
    • 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 present invention relates to a turbomachine rotor comprising damping devices for blades.
  • a device in which the damping element in stone is embedded between the upstream face of the rim of the support disc and a flange.
  • the angle of this square member has a critical bending zone.
  • the turbomachine rotor comprises damping devices for blades, each damping device being constituted by a damping member disposed in a cavity delimited, circumferentially, by the stilts of the feet of two consecutive blades , radially, inside by a tooth of the blade support disc, on the outside by the lower faces of the half platforms of said two consecutive blades and, axially, upstream by the upstream parts of the half platforms, at l 'downstream, on the one hand by a bequet secured to the disc tooth and, on the other hand, by webs secured to each of the two consecutive blades.
  • This device is characterized in that, the damping member is mounted so as to be able to pivot, at its upstream end around a geometric axis perpendicular to a radial axis of the support disc and in the median plane thereof, so as to be able to occupy two positions, the first, in operation, under the centrifugal action, in which the upper part of said member, conforming to constitute a projecting dihedral comes to marry a re-entrant dihedron constituted by the half platforms of the two consecutive blades, one axial immobilization downstream of said member being obtained by a stop means, the second, retracted, in which the radial height of said member is less than that of the bevel of the disc delimiting, downstream, the cavity so as to allow the passage, above said member, of the web of each of said blades, which allows their disassembly by withdrawal upstream.
  • This arrangement allows the damping member to pass under the veil of the blade during assembly or disassembly blade by blade. In addition, it is better positioned between the stilts of the blades so that jamming cannot occur. In order to optimize its resistant work under the platforms of the blades, the bearing surface of the damping members is larger because it extends under the common platforms of two blades.
  • the damping member is pivotally mounted around its end which has a cylindrical boss engaged in a cylindrical bottom housing formed between two spoilers shaped in the middle part of a disc tooth of support.
  • This arrangement has the advantage of the simplicity of its mechanism and of using gravity to maintain the damping member of the blades located in the upper part in the retracted position, and to allow the unitary disassembly of said blades.
  • the damping member is subjected to the action of an elastic member keeping said damping member in contact with the underside of the platforms of the blades.
  • the damper is free in the cavity formed by a tooth of the disc, the stilts and the platforms of two consecutive blades.
  • an elastic member is associated with it which presses said member on the underside of the wings of two consecutive platforms and which participates in the sequence mounting.
  • FIGs 1 and 2 there is shown a support disc 1 having housings 2 in which the feet 3 of the blades 4 are mounted.
  • a damping member 8 for the vibrations of the blades 4.
  • the damping member 8 consists of a plate having an upper part 8a shaped to constitute a projecting dihedral conforming, under the action of centrifugal force, to the re-entrant dihedron formed by the platforms 6, 6a of the two consecutive blades 4.
  • the damping member 8 is pivotally mounted by its upstream in the middle part of the space between the blades 4 and the support disc 1, along an axis perpendicular to a radial axis of the support disc.
  • the damping member B has at its upstream end a cylindrical boss 9 engaged in a housing 10 whose bottom 10a is cylindrical and which is formed between two spoilers 11 and 12 formed in the middle part of the tooth 7 of the disc. support 1.
  • the front spoiler 12 prevents the boss 9 from sliding forward when the engine is stopped.
  • the rear spoiler 11 supports the force ax: al, represented by an arrow in FIG. 1, due to the centrifugal force of the damping member and for this purpose it is therefore reinforced.
  • a hole 13 drilled in the cylindrical boss 9 makes it possible to position the center of gravity at the largest possible diameter, therefore as far as possible from the disc tooth.
  • the damping member 8 When the engine is running, the damping member 8 is plate under the action of centrifugal force against the platforms 6, 6a of the blades, so that the upper part 8a of said protruding dihedral-shaped member comes to marry the dihedron reentrant constitutes by platforms 6, 6a of two consecutive blades.
  • FIGS. 3, 4 and 5 Another embodiment of the damping device shown in FIGS. 3, 4 and 5 consists of a damping member 15 made of sheet metal cut in the shape of a cross and then folded longitudinally to form a projecting dihedral formed from the faces 15a, 15b and the four edges 15c, 15d, 15e, 15f are then folded in the shape of a gutter.
  • the upstream edge 15e receives in its concave part a helical torsion spring 16 which consists of two parts 16a, 16b whose free ends 17a. 17b are fixed in particular by welding to the internal face of the damping member 15, said parts 16a, 16b of the helical spring being connected by a loop 18 bearing against the support disc 1.
  • the rear edge 15f in the form of a gutter adapts to the curvature 19 of the rear veil of the blade 4.
  • the damping member 15 In operation at high speed, the damping member 15 is pressed by centrifugal force under the platforms 6, 6a of the blades, the spring 16 no longer being pressed against the tooth 7 of the disc 1, the damping takes place by friction. At low speeds, the spring 16 keeps the damping member 15 in contact with the platforms 6, 6a and prevents the blade from rattling at low speed of rotation.
  • the ribs formed by the folded edges 15c, 15d, 15e, 15f provide rigidity which prevents buckling of the part.
  • the spring 16 ensures the positioning of the damping member under the platforms 6, 6a of the blades.
  • a blade 4 To mount a blade 4, it is inserted from the front into its cell 2. Then a damping member 15 is wedged in the rear part of a lateral cavity of the blade.
  • the adjacent blade is introduced and as the rear web 14 of this second blade progresses towards the rear of the disc, it crushes the spring 16 of the damping member 15 then the spring relaxes when the web 14 of the 'dawn arrives at the base of the rear spoiler of the disc 1, and, almost completely relaxed, it plates the damper on the wings of the two adjacent platforms 6, 6a.
  • the damping member Due to its dihedral shape, the damping member is automatically positioned in the dihedral formed by the two platforms.
  • the damping member To dismantle a vane 4, the damping member must be placed in the retracted position, for this it is necessary to crush the spring 16 of the damping member, either by pulling the damper from the front using pliers special, either by pressing on the damping member 15 using a blade inserted radially by the clearance 20 existing between two platforms 6, 6a (see FIG. 2).
  • This arrangement can also be used to dampen the vibrations of stator vanes but, in this case, the stiffness of the spring must be greater.

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)
EP83400980A 1982-05-18 1983-05-17 Dispositif d'amortissement pour aubes dans un rotor d'une turbomachine Expired EP0095409B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8208635 1982-05-18
FR8208635A FR2527260A1 (fr) 1982-05-18 1982-05-18 Dispositif d'amortissement escamotable pour aubes d'une turbomachine

Publications (2)

Publication Number Publication Date
EP0095409A1 EP0095409A1 (fr) 1983-11-30
EP0095409B1 true EP0095409B1 (fr) 1986-07-23

Family

ID=9274134

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83400980A Expired EP0095409B1 (fr) 1982-05-18 1983-05-17 Dispositif d'amortissement pour aubes dans un rotor d'une turbomachine

Country Status (4)

Country Link
US (1) US4516910A (enrdf_load_stackoverflow)
EP (1) EP0095409B1 (enrdf_load_stackoverflow)
DE (1) DE3364694D1 (enrdf_load_stackoverflow)
FR (1) FR2527260A1 (enrdf_load_stackoverflow)

Families Citing this family (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2585069B1 (fr) * 1985-07-16 1989-06-09 Snecma Dispositif de limitation du debattement angulaire d'aubes montees sur un disque de rotor de turbomachine
US4743164A (en) * 1986-12-29 1988-05-10 United Technologies Corporation Interblade seal for turbomachine rotor
US4936749A (en) * 1988-12-21 1990-06-26 General Electric Company Blade-to-blade vibration damper
US5205713A (en) * 1991-04-29 1993-04-27 General Electric Company Fan blade damper
US5215432A (en) * 1991-07-11 1993-06-01 United Technologies Corporation Stator vane damper
US5302085A (en) * 1992-02-03 1994-04-12 General Electric Company Turbine blade damper
US5261790A (en) * 1992-02-03 1993-11-16 General Electric Company Retention device for turbine blade damper
US5228835A (en) * 1992-11-24 1993-07-20 United Technologies Corporation Gas turbine blade seal
US5681142A (en) * 1993-12-20 1997-10-28 United Technologies Corporation Damping means for a stator assembly of a gas turbine engine
US5573375A (en) * 1994-12-14 1996-11-12 United Technologies Corporation Turbine engine rotor blade platform sealing and vibration damping device
GB2311826B (en) * 1996-04-02 2000-05-10 Europ Gas Turbines Ltd Turbomachines
US5827047A (en) * 1996-06-27 1998-10-27 United Technologies Corporation Turbine blade damper and seal
US5746578A (en) * 1996-10-11 1998-05-05 General Electric Company Retention system for bar-type damper of rotor
US5749705A (en) * 1996-10-11 1998-05-12 General Electric Company Retention system for bar-type damper of rotor blade
US5924699A (en) * 1996-12-24 1999-07-20 United Technologies Corporation Turbine blade platform seal
US5785499A (en) * 1996-12-24 1998-07-28 United Technologies Corporation Turbine blade damper and seal
GB2344383B (en) * 1998-12-01 2002-06-26 Rolls Royce Plc A bladed rotor
AU5006900A (en) 1999-05-13 2000-12-05 Rolls-Royce Corporation Method for designing a cyclic symmetric structure
US6315298B1 (en) * 1999-11-22 2001-11-13 United Technologies Corporation Turbine disk and blade assembly seal
US7121800B2 (en) * 2004-09-13 2006-10-17 United Technologies Corporation Turbine blade nested seal damper assembly
FR2915510B1 (fr) * 2007-04-27 2009-11-06 Snecma Sa Amortisseur pour aubes de turbomachines
US8096746B2 (en) * 2007-12-13 2012-01-17 Pratt & Whitney Canada Corp. Radial loading element for turbine vane
US8282354B2 (en) * 2008-04-16 2012-10-09 United Technologies Corporation Reduced weight blade for a gas turbine engine
US8151422B2 (en) 2008-09-23 2012-04-10 Pratt & Whitney Canada Corp. Guide tool and method for assembling radially loaded vane assembly of gas turbine engine
US8672626B2 (en) * 2010-04-21 2014-03-18 United Technologies Corporation Engine assembled seal
US20120177498A1 (en) * 2011-01-07 2012-07-12 General Electric Company Axial retention device for turbine system
US20130333173A1 (en) * 2012-06-15 2013-12-19 Mitsubishi Heavy Industries, Ltd. Blade root spring insertion jig and insertion method of blade root spring
US9587495B2 (en) 2012-06-29 2017-03-07 United Technologies Corporation Mistake proof damper pocket seals
EP2900999B1 (en) 2012-09-28 2019-10-09 United Technologies Corporation Seal damper with improved retention
EP2881544A1 (en) 2013-12-09 2015-06-10 Siemens Aktiengesellschaft Airfoil device for a gas turbine and corresponding arrangement
US9624780B2 (en) * 2013-12-17 2017-04-18 General Electric Company System and method for securing axially inserted buckets to a rotor assembly
EP3097268B1 (en) * 2014-01-24 2019-04-24 United Technologies Corporation Blade for a gas turbine engine and corresponding method of damping
US10533445B2 (en) * 2016-08-23 2020-01-14 United Technologies Corporation Rim seal for gas turbine engine
JP7039355B2 (ja) * 2018-03-28 2022-03-22 三菱重工業株式会社 回転機械
CN114508386B (zh) * 2020-11-16 2024-06-25 中国航发商用航空发动机有限责任公司 叶片阻尼器、涡轮和航空发动机

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Also Published As

Publication number Publication date
US4516910A (en) 1985-05-14
EP0095409A1 (fr) 1983-11-30
FR2527260B1 (enrdf_load_stackoverflow) 1984-12-21
DE3364694D1 (en) 1986-08-28
FR2527260A1 (fr) 1983-11-25

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