EP1564372A1 - Auswuchteinrichtung für die Turbinenrotorscheiben eines Gasturbinentriebwerks - Google Patents

Auswuchteinrichtung für die Turbinenrotorscheiben eines Gasturbinentriebwerks Download PDF

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Publication number
EP1564372A1
EP1564372A1 EP05100778A EP05100778A EP1564372A1 EP 1564372 A1 EP1564372 A1 EP 1564372A1 EP 05100778 A EP05100778 A EP 05100778A EP 05100778 A EP05100778 A EP 05100778A EP 1564372 A1 EP1564372 A1 EP 1564372A1
Authority
EP
European Patent Office
Prior art keywords
balancing device
rim
balancing
cavities
housings
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
EP05100778A
Other languages
English (en)
French (fr)
Other versions
EP1564372B1 (de
Inventor
Jean-Louis Bertrand
Frédéric Paul Eichstadt
Joel Mathieu
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
SNECMA Moteurs SA
SNECMA SAS
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 SNECMA Moteurs SA, SNECMA SAS filed Critical SNECMA Moteurs SA
Publication of EP1564372A1 publication Critical patent/EP1564372A1/de
Application granted granted Critical
Publication of EP1564372B1 publication Critical patent/EP1564372B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/027—Arrangements for balancing
    • 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 the field technical turbomachine rotors.
  • It aims more particularly at a device balancing a rotor disk. It also aims a rotor disc equipped with such a device and a rotor having such a disk.
  • US Pat. No. 3,888,601 describes a turbomachine equipped with a balancing device. He discloses a rotor disc provided at its periphery with blades. Each blade has a blade, a foot and a blade platform placed between the blade and the foot. On his around, the disc has grooves arranged according to an axial direction, intended to receive each the foot of a dawn. When a dawn is installed on the disc, his platform overflows laterally from each side of the disc. Hooks formed from one piece with the disc are circumferentially arranged on one side of the disc, being spaced from each other. They have two opposite side walls and oriented radially in coplanar alignment with the side walls of the blade mounting grooves.
  • the balancing of the disk or the rotor is carried out at means of balancing masses comprising a body main and two tabs opposite each other intended to be inserted between the two arms a hook.
  • the blades are introduced in their respective grooves of the disc.
  • each balancing mass so as to insert its tongues in a hook of the disc, making it slide against the disc in one direction radially outward, until it arrives in abutment against a platform of dawn.
  • the balancing masses thus installed are then immobilized: their axial displacement is prevented by their tongues held in a hook, their radial outward movement is prevented by the platform that forms abutment, and their radial displacement inward is prevented by an elastic ring of hold that is placed against the corresponding face of the disk.
  • the balancing device that has just been describes a disadvantage in that it is not suitable for a rotor disk of the blisk type piece. It has another disadvantage in that this arrangement of disk balancing weights considerably increases the axial dimension of the disk. Indeed, to the axial dimension of the disc the thickness of the hooks, the size of the masses and that of the overhanging platforms. By next, in the presence of a set of several disks, the size of the turbomachine following a direction axial can become excessive.
  • US Patents 4,848,182 and US 4,926,710 describe a method and system for balancing multidisk rotor with integral blade.
  • a ring balancing is fixed by shrinking onto a disc, such that its peripheral surface is in contact with a contact face of the disc that is located on one side of the disc and radially oriented towards the inside of it.
  • the ring is in abutment laterally to the inside of the disc against a lip of the disc that rises radially towards outside from the contact face. It is retained laterally towards the outside of the disc by means of an elastic retaining ring.
  • the ring On its periphery external, the ring has teeth extending radially outwards which are separated by openings.
  • the openings form, with the contact face and lip of the disc, cavities distributed circumferentially that open laterally to the outside of the disc.
  • Many discs each equipped with their balancing ring are assembled together to form the rotor.
  • the method of balancing the disk or the rotor consists of insert balance weights in some of the cavities that are distributed circumferentially. The balancing weights are held laterally towards the outside of the disc by the retaining ring elastic, to prevent them from coming out of their cavity.
  • the balancing device that has just been described has a disadvantage in that the masses balancing devices are installed on a ring balancing. This requires the presence of a ring as well as a frettage fastening operation of this balancing ring on the disc.
  • An object of the present invention is to propose a device for balancing a disk and / or a rotor by means of balancing weights, which not present the disadvantages of the technique previous statement above.
  • the invention a balancing device that applies from preferred to a bladed rotor disc monobloc, the disc having a rim. It has housings in said rim and flyweights balancing housed in said housing.
  • these dwellings are located in a side face of the rim, under a platform of disk that supports the blades, and are distributed on the circumference of the rim.
  • the dwellings do not cross the rim, and present themselves in the form of blind holes whose orifice opens on a side face of the rim.
  • these dwellings cross the rim and their orifices open on a first and a second opposite side faces of the rim.
  • the houses and the weights have a Shape adapted to prevent rotation or tilting of each weight in its housing respective.
  • the balancing device further comprises one or two ring (s) of stop (s), intended (s) to be positioned laterally against the rim, so that at least partially close the orifices corresponding housing.
  • the snap ring closes at least half of the orifices.
  • the snap ring closes completely the orifices. To prevent a rotation axis of the snap ring, it comprises at least one protuberance intended to fit into one of housing.
  • the balancing device has one or two circumferential slot (s) arranged under the platform intended to receive a peripheral edge of a snap ring.
  • the invention a monobloc rotor rotor, which is equipped with a balancing device according to the first aspect of the invention.
  • the invention a rotor, which comprises at least one disc according to the second aspect of the invention.
  • An advantage of the balancing device according to the invention lies in the fact that the dwellings of the flyweights are an integral part of the rim, which avoids having to use an extra room intended to receive balancing weights. he resulting in a reduction in manufacturing costs and mounting time of the rotors.
  • Another advantage of the balancing system of the invention lies in the fact that the flyweights placed are easily accessible, and that it is possible to change the balance of the disks or rotor by changing the distribution of the weights balancing, without having to disassemble the rotor while whole.
  • Another advantage lies in the fact that it is possible, with such a balancing device, to improve the correction of the unbalance of rotors.
  • a rotor 10 comprising six discs 12, 14.
  • three of the disks (right in the figure) are disks 12 each having removable vanes 16 attaching to the rim 18 of the disc.
  • the other three disks (left in the figure) are monoblock bladed disks 14, each having blades 20 made in one piece with the rim 18 of the disc.
  • FIG. 2 shows a disk one-piece bladder 14 having a rim 18 and vanes 20 made in one piece with the rim 18.
  • a connecting flange 24 intended to assemble the disk 14 with a disk adjacent (not shown), which is attached to the disk 14 by fastening means such as for example screws through a hole 26 of the rim and a bore 28 of the connecting flange 24.
  • the rim 18 is an area of larger thickness of which a face oriented radially towards the outside serves as a platform 32 from which the blades 20 extend radially outwards.
  • housing 36 which are distributed circumferentially on the rim 18. According to a first embodiment of the device balancing of the invention, these dwellings 36 are present in the form of blind holes opening on a single side face 180 of the rim 18.
  • balancing weights 40 are placed in the 36. According to the needs arising during of the balancing process, we place a weight 40 in some dwellings 36 and no weights 40 in other dwellings 36.
  • the slots 36 present in the axial plane and / or in the plane transversal, a substantially rectangular section to rounded corners.
  • the weights 40 present substantially a rectangular parallelepiped shape whose dimensions correspond to those of the dwelling 36, so that each weight 40 fits in his dwelling 36 without being able to move in rotation in this one.
  • the edges of the parallelepiped rectangle are cut to form additional facets on the flyweight 40, in order to further limit possible movements of rotation or tilting of the weight 40 in its housing 36.
  • the area of the rim 18 located between platform 32 and dwellings 36 is slightly overhanging the dwellings 36.
  • the rim 18 has a circumferential slot 42, which is arranged in a face substantially opposite to the platform 32, and which runs along the dwellings 36.
  • a snap ring 44 which has such a width that it closes at least partially housing 36 so as to hold the weights 40.
  • the snap ring 44 is cut transversely, so that it can be installed and removed easily.
  • the snap ring 44 has a anti-rotation member 46 to prevent its rotation in the transverse plane when installed in the slot 42 of the rim 18.
  • This anti-rotation member is materialized, for example, by a protuberance 46 of the snap ring 44 which fits into one of the dwellings 36 which is not occupied by a flyweight 40 (FIG. 3).
  • Figure 5 illustrates in front view and partial and enlarged housing 36.
  • the snap ring 44 closes substantially half of the dwellings 36.
  • the snap ring 44 closes two-thirds 36 or all 36 dwellings. to prevent the weights 40 from coming out of housings 36, it is preferred that the snap ring covers at least half of the dwellings 36.
  • the housing 38 is in the form through holes that open on both sides of the rim 18.
  • these dwellings 38 present a first cavity 382 similar to housings 36 of the first embodiment and which opens on a first side face 182 of the rim 18. They also present a second cavity 384 substantially symmetrical to the first cavity 382 by compared to a median plane of the rim 18, and which opens on a second side face 184 of the rim 18, opposite its first side face 182.
  • the two cavities 382, 384 are interconnected by a intermediate channel 386, which presents, on the example illustrated, a smaller section than the sections respective two cavities 382, 384.
  • weights balancing 40 are placed in some of the first cavities 382, and a first snap ring 442 is installed in a first slot 422 formed in a first part overhanging in relation to the first face 182 of the rim 18, so as to close at least partially the first cavities 382 and hold the weights 40.
  • sealing flanges 48 are provided to ensure the sealing of the disc 14. They are preferably placed at the bottom of the second cavities 384, and cut all communication between the second cavities and the intermediate channels 386 of lesser section.
  • a second stop ring 444 is installed in a second slot 424 arranged in a second part overlooking compared to the second face 184 of the rim 18, of at least partially closing the seconds cavities 384 and to retain the sealing flanges 48.
  • the first snap ring 442, respectively the second snap ring 444, is preferably cut transversely, so that it can be installed and removed easily.
  • the first stop ring 442 respectively the second snap ring 444, presents a anti-rotation member (not shown), similar to that stop ring 44 according to the first embodiment of the device.
  • Balancing also applies to the second mode of realization of the balancing device.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP05100778.9A 2004-02-06 2005-02-04 Turbinenrotorscheibe mit einer Auswuchteinrichtung Expired - Lifetime EP1564372B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0450217 2004-02-06
FR0450217A FR2866057B1 (fr) 2004-02-06 2004-02-06 Dispositif d'equilibrage d'un disque de rotor, disque equipe d'un tel dispositif, et rotor ayant un tel disque

Publications (2)

Publication Number Publication Date
EP1564372A1 true EP1564372A1 (de) 2005-08-17
EP1564372B1 EP1564372B1 (de) 2013-07-10

Family

ID=34685068

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05100778.9A Expired - Lifetime EP1564372B1 (de) 2004-02-06 2005-02-04 Turbinenrotorscheibe mit einer Auswuchteinrichtung

Country Status (6)

Country Link
US (1) US7347672B2 (de)
EP (1) EP1564372B1 (de)
JP (1) JP4856879B2 (de)
CA (1) CA2495848C (de)
FR (1) FR2866057B1 (de)
RU (1) RU2362028C2 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2499889C1 (ru) * 2012-03-13 2013-11-27 Открытое акционерное общество Конструкторско-производственное предприятие "Авиамотор" Способ снижения динамических напряжений в рабочих лопатках последней ступени турбины
EP3006667A1 (de) * 2014-10-09 2016-04-13 Siemens Aktiengesellschaft Turbinenlaufschaufel, Anordnung aus einer Turbinenwelle, einer Turbinenradscheibe, einer Vielzahl an Turbinenlaufschaufeln sowie einem Wuchtgewicht und Turbine
FR3028781A1 (fr) * 2014-11-25 2016-05-27 Snecma Piece pour rotor de turbomachine d'aeronef comprenant une protuberance annulaire usinable pourvue d'un orifice de deshuilage et procede de preparation de celle-ci
FR3102205A1 (fr) 2019-10-17 2021-04-23 Safran Aircraft Engines Rotor de turbomachine à masselotte

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Publication number Priority date Publication date Assignee Title
FR2896289B1 (fr) * 2006-01-13 2008-03-28 Snecma Sa Masselotte d'equilibrage, disque de rotor en etant equipe, rotor et moteur d'aeronef les comportant
FR2907497B1 (fr) * 2006-10-24 2009-01-23 Snecma Sa Systeme d'equilibrage pour rotor de turbomachine
FR2907498B1 (fr) * 2006-10-24 2009-01-23 Snecma Sa Systeme d'equilibrage pour rotor de turbomachine
FR2922587B1 (fr) * 2007-10-22 2010-02-26 Snecma Roue de turbomachine
US8328519B2 (en) 2008-09-24 2012-12-11 Pratt & Whitney Canada Corp. Rotor with improved balancing features
US9297258B2 (en) * 2009-06-16 2016-03-29 General Electric Company Trapped spring balance weight and rotor assembly
US8506253B2 (en) * 2009-08-19 2013-08-13 Pratt & Whitney Canada Corp. Balancing apparatus for rotor assembly
US8246305B2 (en) * 2009-10-01 2012-08-21 Pratt & Whitney Canada Corp. Gas turbine engine balancing
US9133855B2 (en) * 2010-11-15 2015-09-15 Mtu Aero Engines Gmbh Rotor for a turbo machine
US9410436B2 (en) 2010-12-08 2016-08-09 Pratt & Whitney Canada Corp. Blade disk arrangement for blade frequency tuning
US20120219419A1 (en) * 2011-02-28 2012-08-30 Wen-Hao Liu Round axial fan with balancing structure
US20130156584A1 (en) * 2011-12-16 2013-06-20 Carney R. Anderson Compressor rotor with internal stiffening ring of distinct material
US8984940B2 (en) 2012-04-04 2015-03-24 Elliot Company Passive dynamic inertial rotor balance system for turbomachinery
US9388697B2 (en) * 2012-07-17 2016-07-12 Solar Turbines Incorporated First stage compressor disk configured for balancing the compressor rotor assembly
TWI601884B (zh) * 2016-02-22 2017-10-11 佛山市建準電子有限公司 可調整配重之扇輪及風扇
US10883370B2 (en) * 2018-08-14 2021-01-05 Raytheon Technologies Corporation Dovetail weight system for rotor balance
FR3091721B1 (fr) * 2019-01-10 2021-01-15 Safran Aircraft Engines Rotor de turbomachine a masselotte
US11352903B2 (en) * 2020-01-20 2022-06-07 Raytheon Technologies Corporation Rotor stack bushing with adaptive temperature metering for a gas turbine engine
US11976564B1 (en) 2023-03-30 2024-05-07 Rolls-Royce North American Technologies Inc. Splined balance weight for rotating components in gas turbine engines
US12305528B2 (en) 2023-08-08 2025-05-20 Rolls-Royce North American Technologies Inc. Rotor assembly for gas turbine engines with replaceable balance weight bands
US12018580B1 (en) 2023-08-08 2024-06-25 Rolls-Royce North American Technologies Inc. Rotor assembly for gas turbine engines with replaceable balance weight pins
US12018579B1 (en) 2023-08-08 2024-06-25 Rolls-Royce North American Technologies Inc. Clocking balance weight rotor assembly for gas turbine engines

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GB805371A (en) * 1956-01-16 1958-12-03 Rolls Royce Improvements in or relating to balancing means for rotors
US3748060A (en) * 1971-09-14 1973-07-24 Westinghouse Electric Corp Sideplate for turbine blade
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Publication number Priority date Publication date Assignee Title
GB805371A (en) * 1956-01-16 1958-12-03 Rolls Royce Improvements in or relating to balancing means for rotors
US3748060A (en) * 1971-09-14 1973-07-24 Westinghouse Electric Corp Sideplate for turbine blade
US4355957A (en) * 1981-06-18 1982-10-26 United Technologies Corporation Blade damper
US4803893A (en) * 1987-09-24 1989-02-14 United Technologies Corporation High speed rotor balance system
US5018943A (en) * 1989-04-17 1991-05-28 General Electric Company Boltless balance weight for turbine rotors
US5373922A (en) * 1993-10-12 1994-12-20 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Tuned mass damper for integrally bladed turbine rotor

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2499889C1 (ru) * 2012-03-13 2013-11-27 Открытое акционерное общество Конструкторско-производственное предприятие "Авиамотор" Способ снижения динамических напряжений в рабочих лопатках последней ступени турбины
EP3006667A1 (de) * 2014-10-09 2016-04-13 Siemens Aktiengesellschaft Turbinenlaufschaufel, Anordnung aus einer Turbinenwelle, einer Turbinenradscheibe, einer Vielzahl an Turbinenlaufschaufeln sowie einem Wuchtgewicht und Turbine
FR3028781A1 (fr) * 2014-11-25 2016-05-27 Snecma Piece pour rotor de turbomachine d'aeronef comprenant une protuberance annulaire usinable pourvue d'un orifice de deshuilage et procede de preparation de celle-ci
FR3102205A1 (fr) 2019-10-17 2021-04-23 Safran Aircraft Engines Rotor de turbomachine à masselotte

Also Published As

Publication number Publication date
FR2866057B1 (fr) 2006-04-28
FR2866057A1 (fr) 2005-08-12
CA2495848A1 (en) 2005-08-06
JP4856879B2 (ja) 2012-01-18
RU2005102783A (ru) 2006-07-10
EP1564372B1 (de) 2013-07-10
US20050191181A1 (en) 2005-09-01
JP2005220908A (ja) 2005-08-18
US7347672B2 (en) 2008-03-25
RU2362028C2 (ru) 2009-07-20
CA2495848C (en) 2013-01-22

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