EP2009244A1 - Axiale Haltevorrichtung für Laufradschaufeln, die auf einer Rotorscheibe einer Strömungsmaschine montiert sind - Google Patents

Axiale Haltevorrichtung für Laufradschaufeln, die auf einer Rotorscheibe einer Strömungsmaschine montiert sind Download PDF

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Publication number
EP2009244A1
EP2009244A1 EP08158843A EP08158843A EP2009244A1 EP 2009244 A1 EP2009244 A1 EP 2009244A1 EP 08158843 A EP08158843 A EP 08158843A EP 08158843 A EP08158843 A EP 08158843A EP 2009244 A1 EP2009244 A1 EP 2009244A1
Authority
EP
European Patent Office
Prior art keywords
retaining ring
segments
disk
bearing face
rotor
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
EP08158843A
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English (en)
French (fr)
Other versions
EP2009244B1 (de
Inventor
Claude Gérard René Dejaune
Valérie Annie Gros
Gaël Loro
Jean-Luc Soupizon
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 SAS
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Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP2009244A1 publication Critical patent/EP2009244A1/de
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Publication of EP2009244B1 publication Critical patent/EP2009244B1/de
Active 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates

Definitions

  • the present invention relates to a device for axially retaining blades mounted on a turbomachine rotor disk such as the rotor of the last stage of the low-pressure turbine.
  • the low-pressure turbine of a turbomachine is composed of a plurality of stages of moving blades alternating with fixed vanes. For each stage of the turbine, the blades are fixed on two concentric rings and the blades are fixed by their foot on a rotor disk. All the rotor disks of the turbine are fixed to each other by bolted connections and are secured to the low-pressure shaft of the turbomachine via a trunnion.
  • the disc of the last stage of such a low-pressure turbine comprises at its periphery a plurality of axial cells in each of which is mounted the foot of a blade of the turbine.
  • the gas stream passes through the turbine exerting an axial force on the moving blades, it is necessary to prevent any axial displacement of the vanes with the aid of retaining devices.
  • One of these devices is to immobilize the blade roots with an annular flange pressed against a radial bearing surface of the disc and the blade root, the flange being held in this position by an annular ring.
  • EP 1,180,580 and EP 1,498,579 we can refer to publications EP 1,180,580 and EP 1,498,579 .
  • such a device is usually quite complex to make and assemble since it requires the use of several parts (namely the flange and the retaining ring of the flange).
  • the present invention aims to overcome the aforementioned drawbacks by proposing an axial retaining device blades whose realization and assembly are simple and which is likely to contribute to the balancing of the rotor disk.
  • an axial retention device for vanes mounted on a turbomachine rotor disk characterized in that it comprises a rotor disk comprising at its periphery a plurality of substantially axial cells and open towards the outside. outside, and at a radial bearing face, a flange extending radially outwardly to define with said bearing face an annular groove open towards the outside, the device further comprising a plurality of blades each comprising a foot mounted in a corresponding cell of the rotor disc, each blade root being provided at a radial bearing surface corresponding to that of the rotor disc of at least one radially extending spoiler inwardly to delimit with said bearing face an annular slot open towards the inside, and a retaining ring mounted against the bearing face of the rotor disc and the blade roots, said retaining ring etan t housed in the groove of the disk, held outside in the notches of the blade roots, and consists of a plurality of angular segments placed
  • the device according to the invention comprises only one piece (namely the retaining ring which is segmented) so that it is easy to make and easy to mount on the rotor disc.
  • the retaining ring consists of a plurality of angular segments placed end to end, it is possible to vary the mass of each of these segments individually in order to correct the unbalance phenomenon encountered by the rotor disks. . In this way, the unbalance correction can be obtained without having to disassemble before binding structural.
  • At least one of the segments of the retaining ring has a greater mass than the other segments.
  • each segment of the retaining ring comprises notches open towards the outside to allow the passage of the spoilers of the blade roots during assembly of the retaining ring in the groove of the disc of rotor.
  • the retaining ring comprises means for making it possible to stop its rotation in the groove of the rotor disk.
  • at least one of the segments of the retaining ring may comprise a foldable tongue that is adapted to be folded between two adjacent lugs of blade roots to stop the rotation of the retaining ring in the groove of the rotor disk.
  • the invention also relates to a turbomachine comprising at least one axial retention device blades mounted on a rotor disk as defined above.
  • FIGS. 1 and 1A partially represent in longitudinal section a low-pressure turbine of an aviation turbine engine equipped with a device according to one embodiment of the invention.
  • turbomachine assembly (aeronautical or terrestrial) provided with a rotor disk on which are mounted axially blades.
  • the low-pressure turbine is centered on the longitudinal axis X-X of the turbomachine.
  • the last stage of the turbine consists of a distributor formed of a plurality of blades 2 and a movable wheel placed behind the distributor and formed of a plurality of blades 4 mounted axially on a rotor disk 6.
  • the penultimate stage of the turbine also consists of a distributor (not shown) and a movable wheel formed of a plurality of blades 4 'mounted on a rotor disk 6'.
  • the discs 6, 6 'of the last and the penultimate stages of the turbine are fixed to each other by means of bolted connections 8 and are secured to the low-pressure shaft of the turbomachine (no shown) by an annular journal 10. The latter is also fixed on the discs 6, 6 'by means of the same bolted connections 8.
  • the disk 6 of the last stage of the turbine comprises at its periphery a plurality of substantially axial cells 12, open towards the outside of the disk (that is to say in the direction opposite to the longitudinal axis XX) and intended each axially receive the foot 4a (for example fir-shaped) of a blade 4 of the turbine (for example by fitting).
  • the disk 6 also comprises, at its downstream radial face 14 (hereinafter referred to as the bearing face), a flange 16 extending radially outwards of the disk to delimit with the bearing face an annular groove 18 open. outwards.
  • each blade root 4a is provided at its downstream radial face corresponding to that of the rotor disc 6 of at least one spoiler 20 extending radially towards the inside of the disk (ie say towards the longitudinal axis XX) to delimit with said downstream face an annular notch 22 which is open towards the inside.
  • the device according to the invention comprises a retaining ring 24 which is mounted against the bearing face 14 of the rotor disc 6 and the blade roots 4a.
  • This retaining ring 24 is housed in the groove 18 of the disc and is held outside in the notches 22 of the blade roots 4a.
  • the retaining ring 24 consists of a plurality of angular segments (or sectors) 24a placed end to end, each ring segment 24a being able to extend circumferentially over the same angular distance.
  • a turbomachine low-pressure turbine whose last stage comprises 98 blades, it can be provided 14 ring segments 24a which therefore each extend over 25 °.
  • each ring segment 24a comprises notches 26 which are open towards the outside. As illustrated by Figure 2A these notches are dimensioned to allow the passage of the spoilers 20 of the blade roots 4a when mounting the retaining ring in the groove of the disc. In this position, the ring segments are not maintained outside in the notches 22 of the blade roots.
  • the number of notches 26 per segment can be 7.
  • the ring segments 24a are pivoted about the longitudinal axis XX of the turbomachine so that the spoilers 20 of the blade roots are no longer arranged opposite the notches 26 ( Figure 2B ). In this position, the ring segments are then held outside in the notches of the blade roots.
  • the rotor disc 6 comprises 98 blades 4 and the retaining ring 24 consists of 14 segments 24a, each segment having 7 notches 26, a rotation (in one direction or the other ) 1.8 ° of the retaining ring allows to move from the position of the Figure 2A at the position of the Figure 2B .
  • the disassembly of the retaining ring is performed in the same manner by pivoting the latter by an angle sufficient to ensure that the spoilers of the blade roots are again arranged opposite the notches of the segments of the Ring.
  • At least one of the ring segments 24a comprises a foldable tongue 28 which is adapted to be folded between two adjacent spoilers 20 of blade roots 4a to stop the rotation of the retaining ring. in the groove 18 of the rotor disk 6 once it is correctly positioned ( Figure 2B ).
  • the tongue 28 is disposed at one of the indentations 26 of the ring segment 24a and is bendable to take two extreme positions: a position in which it extends in a plane inclined with respect to the radial plane of the segment ring to allow rotation of said segment ( Figure 2A ), and another position in which it is arranged in the same radial plane as the spoilers 20 of the blade roots and extends circumferentially between two adjacent spoilers 20 in order to lock in rotation said segment and therefore the entire ring restraint ( Figure 2B ).
  • At least one of the ring segments 24a has a larger mass than the other segments.
  • Such an arrangement makes it possible to easily correct the unbalance phenomenon observed in a low-pressure turbine. Indeed, as the retaining ring 24 is segmented, it is possible to assign to some of the ring segments an individual mass which is different from that of the others and thus ensure that the center of gravity of the rotor disc is found well on the longitudinal axis XX of the turbomachine. It should be noted that the higher the number of ring segments, the better the balance of the masses on the entire disk.
  • This arrangement is particularly advantageous when, as represented on the figure 1 the annular space between the inner end of the disk 6 of the last stage of the turbine and the pin 10 does not allow direct access to the bolted connections 8 so that it is impossible to fix balancing masses on these bolted connections without first removing the last stage of the turbine.
  • a balancing control of the rotor disk is performed once the turbine assembly and an unbalance correction is optionally applied.
  • one or more ring segments are replaced by modified mass segments adapted to the required correction.
  • the modified mass segments are ring segments whose mass is greater than that of the other segments.
  • FIGS. 3A to 3C which represent in longitudinal section different alternative embodiments of the device according to the invention, illustrate various ways of varying the mass of a ring segment 24a.
  • the ring segment 24a has an excess thickness 30 with respect to the segment shown in FIG. figure 3A .
  • the ring segment 24a of the figure 3C has a boss 32 which is present neither on the ring segment of the figure 3A nor on that of the figure 3B .
  • This extra thickness 30 and this boss 32 may extend circumferentially over all or only part of the ring segment. They correspond to mass additions.
  • the depth of the indentations 26, as well as the height and / or the thickness of the inter-indent regions may vary in order to increase or decrease the mass of the ring segments.
  • the ring segments can be pre-machined with range classes (for example from gram to gram) to provide a wide choice of segments adapted to the unbalance correction required.
  • the ring segments can be machined on demand.
  • the axial blade retainer according to the invention has many advantages.
  • it consists of only one main piece (ie the retaining ring) which makes its inexpensive manufacture and assembly / disassembly against the bearing surface of the easy disc.
  • ring segments it is possible to vary the mass of each of these segments and thus easily correct the phenomenon of unbalance observed with this type of technology.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP08158843A 2007-06-27 2008-06-24 Axiale Haltevorrichtung für Laufradschaufeln, die auf einer Rotorscheibe einer Strömungsmaschine montiert sind Active EP2009244B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0756062A FR2918106B1 (fr) 2007-06-27 2007-06-27 Dispositif de retenue axiale d'aubes montees sur un disque de rotor de turbomachine.

Publications (2)

Publication Number Publication Date
EP2009244A1 true EP2009244A1 (de) 2008-12-31
EP2009244B1 EP2009244B1 (de) 2010-08-11

Family

ID=39081577

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08158843A Active EP2009244B1 (de) 2007-06-27 2008-06-24 Axiale Haltevorrichtung für Laufradschaufeln, die auf einer Rotorscheibe einer Strömungsmaschine montiert sind

Country Status (8)

Country Link
US (1) US8348620B2 (de)
EP (1) EP2009244B1 (de)
JP (1) JP5306721B2 (de)
CN (1) CN101333942B (de)
CA (1) CA2635635C (de)
DE (1) DE602008002103D1 (de)
FR (1) FR2918106B1 (de)
RU (1) RU2471999C2 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2933442A1 (fr) * 2008-07-04 2010-01-08 Snecma Flasque de maintien d'un jonc de retenue, ensemble d'un disque de rotor de turbomachine, d'un jonc de retenue et d'un flasque de maintien et turbomachine comprenant un tel ensemble

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DE102010015404B4 (de) * 2010-04-19 2012-02-16 Mtu Aero Engines Gmbh Verfahren zur Reparatur einer Rotoranordnung einer Turbomaschine, Ringelement für eine Rotoranordnung einer Turbomaschine sowie Rotoranordnung für eine Turbomaschine
US8936440B2 (en) 2011-05-26 2015-01-20 United Technologies Corporation Hybrid rotor disk assembly with ceramic matrix composites platform for a gas turbine engine
US8851853B2 (en) * 2011-05-26 2014-10-07 United Technologies Corporation Hybrid rotor disk assembly for a gas turbine engine
US8834125B2 (en) 2011-05-26 2014-09-16 United Technologies Corporation Hybrid rotor disk assembly with a ceramic matrix composite airfoil for a gas turbine engine
DE102011077501A1 (de) * 2011-06-14 2012-12-20 Rolls-Royce Deutschland Ltd & Co Kg Rotorvorrichtung für ein Strahltriebwerk mit einem Scheibenrad und mehreren Laufschaufeln
US8979502B2 (en) * 2011-12-15 2015-03-17 Pratt & Whitney Canada Corp. Turbine rotor retaining system
FR2988128A1 (fr) 2012-03-19 2013-09-20 Alstom Technology Ltd Rotor de turbine pour une centrale thermoelectrique
EP2964894B1 (de) 2013-03-05 2019-04-10 Rolls-Royce North American Technologies, Inc. Verfahren zur rückhaltung einer segmentierten turbinenabdeckplatte
GB2506712B (en) * 2013-05-14 2018-05-02 Rolls Royce Plc Balancing method
US9624775B2 (en) * 2014-05-30 2017-04-18 Rolls-Royce Plc Developments in or relating to rotor balancing
EP3009608B1 (de) 2014-10-02 2019-10-30 United Technologies Corporation Schaufelanordnung mit eingeschlossenen, segmentierten schaufelstrukturen
JP2017028674A (ja) * 2016-02-12 2017-02-02 Ｎｅｃプラットフォームズ株式会社 管理装置、管理方法及び管理プログラム
US10724384B2 (en) 2016-09-01 2020-07-28 Raytheon Technologies Corporation Intermittent tab configuration for retaining ring retention
US10415401B2 (en) 2016-09-08 2019-09-17 United Technologies Corporation Airfoil retention assembly for a gas turbine engine
IT201600130088A1 (it) 2016-12-22 2018-06-22 Nuovo Pignone Tecnologie Srl Pala di turbina e set di fissaggio
CN108808905B (zh) * 2017-05-04 2020-07-28 东元电机股份有限公司 分段式转子结构的制造方法
US10458244B2 (en) 2017-10-18 2019-10-29 United Technologies Corporation Tuned retention ring for rotor disk
FR3082232B1 (fr) * 2018-06-12 2020-08-28 Safran Aircraft Engines Systeme de maintien pour le demontage d'une roue a aubes
IT201900014739A1 (it) * 2019-08-13 2021-02-13 Ge Avio Srl Elementi di trattenimento delle pale per turbomacchine.

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US3853425A (en) * 1973-09-07 1974-12-10 Westinghouse Electric Corp Turbine rotor blade cooling and sealing system
US4648799A (en) * 1981-09-22 1987-03-10 Westinghouse Electric Corp. Cooled combustion turbine blade with retrofit blade seal
US5518369A (en) * 1994-12-15 1996-05-21 Pratt & Whitney Canada Inc. Gas turbine blade retention
EP1180580A1 (de) 2000-08-10 2002-02-20 Snecma Moteurs Vorrichtung zur Halterung eines ringförmigen Lagerschildes an einer radialen Seite eines beschaufelten Rotors
EP1498579A1 (de) 2003-07-17 2005-01-19 Snecma Moteurs Halterung eines Lagerschildes am Rotor
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2933442A1 (fr) * 2008-07-04 2010-01-08 Snecma Flasque de maintien d'un jonc de retenue, ensemble d'un disque de rotor de turbomachine, d'un jonc de retenue et d'un flasque de maintien et turbomachine comprenant un tel ensemble

Also Published As

Publication number Publication date
US20090004018A1 (en) 2009-01-01
RU2008126092A (ru) 2010-01-10
CN101333942B (zh) 2013-07-24
US8348620B2 (en) 2013-01-08
CN101333942A (zh) 2008-12-31
JP5306721B2 (ja) 2013-10-02
DE602008002103D1 (de) 2010-09-23
JP2009008085A (ja) 2009-01-15
CA2635635C (fr) 2013-01-22
CA2635635A1 (fr) 2008-12-27
EP2009244B1 (de) 2010-08-11
RU2471999C2 (ru) 2013-01-10
FR2918106A1 (fr) 2009-01-02
FR2918106B1 (fr) 2011-05-06

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