EP1845235B1 - Axiale Haltevorrichtung für eine Schaufeldeckplatte einer Turbinenscheibe - Google Patents

Axiale Haltevorrichtung für eine Schaufeldeckplatte einer Turbinenscheibe Download PDF

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Publication number
EP1845235B1
EP1845235B1 EP07105588A EP07105588A EP1845235B1 EP 1845235 B1 EP1845235 B1 EP 1845235B1 EP 07105588 A EP07105588 A EP 07105588A EP 07105588 A EP07105588 A EP 07105588A EP 1845235 B1 EP1845235 B1 EP 1845235B1
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EP
European Patent Office
Prior art keywords
face
flange
radially
retaining ring
axial
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Active
Application number
EP07105588A
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English (en)
French (fr)
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EP1845235A1 (de
Inventor
Fabrice Garin
Maurice Judet
Thomas Langevin
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 EP1845235A1 publication Critical patent/EP1845235A1/de
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Publication of EP1845235B1 publication Critical patent/EP1845235B1/de
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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
    • 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

Definitions

  • the present invention relates to a device for axial retention of an annular flange against a radial face of a turbomachine rotor disk.
  • EP 1 498 579 A1 filed by the plaintiff.
  • Such a device makes it possible to retain an annular flange against a radial face of a rotor disk, said disk having in the radial face an annular recess delimited by a plurality of walls, one of which is formed by the internal face of a flange which is extends radially outwards, and said flange having, in its radially inner portion, an annular base bearing against the radially outer wall of the recess and a foot which extends radially inwards in the recess of the recess. disk from the base.
  • the retention device further comprises a retaining ring in the form of a split ring disposed in the recess of the rotor disk, this ring having an axially outer face which bears against an axially internal face of the flange, an axially inner face which bears against an axially outer face of the foot, and a radially outer face which bears against a radially inner face of the base of the flange.
  • This retention device and in particular the retaining ring, is simple to produce, inexpensive and facilitates the assembly and disassembly of parts.
  • it has certain disadvantages.
  • the flange undergoes an axial thrust which has the consequence of a risk of tilting of the retaining ring towards the outside of the recess of the rotor disc.
  • This tilting of the retaining ring can then lead to problems of wear by matting of the rotor disk with a risk of bursting thereof.
  • the tilting of the ring may also cause after matting wear to its disengagement from the recess and thus cause the flange to come out of its housing.
  • EP-A-1 498 579 discloses a retention device according to the preamble of claim 1.
  • the main object of the present invention is thus to overcome such drawbacks by proposing an axial retention device for a rotor disc flange to avoid any risk of tilting of the retaining ring.
  • the axial forces exerted on the retaining ring are due to the prestressed mounting of the flange on the rotor disc.
  • the radial offset between these forces comes from the fact that it is necessary to pass the foot of the flange over the disk flange during assembly and disassembly of the flange.
  • the radial force that applies to the radially outer face of the ring it comes from the centrifugal force resulting from the rotation of the rotor disc.
  • By performing an annular cut at the radially outer face of the retaining ring it is possible to axially shift the direction of the radial force applying to this face to thereby compensate for the rotational torque created by the radial offset between the axial forces. In this way, a mechanical balance of the forces applying to the different faces of the retaining ring which prevents its tilting during operation.
  • the radial plane in which is located the radial force resulting from the support of the radially outer face of the retaining ring against the radially inner face of the base of the flange is preferably arranged between the axially outer and inner faces of the ring of detention.
  • a radially inner portion of the retaining ring sits in a groove formed behind the flange of the rotor disc.
  • the invention also relates to a turbine and a turbomachine comprising at least one retention device as defined above.
  • turbomachine disk 1 for example a high-pressure turbine rotor disk.
  • the disk 1 comprises a plurality of substantially axial cells 2 which are each intended to receive a blade root (not shown).
  • An annular flange 3 mounted against a face 4 of the disk allows real estate axially blades on the disk.
  • a radially inner portion 5 of the flange 3 is housed in an annular recess 6 formed in the face 4 of the disc and is immobilized therein by a retaining ring which is in the form of a split ring 7.
  • the terms “inside” and “outside” denote a wall or a face respectively close to or distant from the axis of rotation of the disk 1, and the terms “internal” and “external” refer to a wall or face respectively near or far from the median plane of the disc.
  • the annular recess 6 is delimited radially outwardly by a substantially cylindrical wall 8 which is connected by a concave surface 9 to a U-shaped annular groove 10 disposed behind an annular flange 11 of the disc.
  • This flange 11 extends radially outwards and has a diameter which is slightly greater than the diameter of the shoulder 12 formed between the concave surface 9 and the bottom of the groove 10.
  • the groove 10 and the flange 11 emerge on the face 4 of the disc 1.
  • this provision is not mandatory for the implementation of the invention.
  • the radially inner portion 5 of the flange 3 comprises an annular base 13 which extends into the recess 6 of the disc and which has a cylindrical outer surface 14 bearing against the cylindrical wall 8 of the disc.
  • the radially inner portion 5 of the flange 3 also comprises a foot 15 which is disposed under the base 13 and which extends radially inwards.
  • the diameter of the bore 16 of the foot 15 is substantially equal to or slightly greater than that of the flange. 11.
  • the foot 15 of the radially inner portion 5 of the flange 3 has an axially outer face 17 which is disposed in a radial plane passing through the groove 10 in the vicinity of the shoulder 12. This outer face 17 is connected to the radially inner face 25 of the base 13 and forms with the latter a rabbet 18.
  • the retaining ring 7 is disposed in the recess 6 so that its radially outer portion accommodates in this rabbet 18 and its radially inner portion partially comes into the groove 10.
  • the retaining ring 7 has a substantially rectangular cross section. It comprises two axial faces parallel to each other and perpendicular to the axis of rotation of the disc 1, namely an axially outer face 19 and an axially inner face 20. In addition, at its radially outer portion housed in the rabbet 18, the ring has a radially outer face 21.
  • This other axial force F2 has a substantially axial direction and a direction opposite to that of the axial force F1, that is to say that it is directed towards the outside.
  • the axial force F1 is offset radially outwards with respect to the other axial force F2 (this offset radial is schematized by the length L on the figure 2 ). Indeed, without such a radial offset L , it would be impossible to pass the foot 15 of the flange 3 above the flange 11 during assembly or disassembly of said flange.
  • the axial forces F1 and F2 are applied to the axial faces 19, 20 of the retaining ring 7 along lines arranged radially on either side of an imaginary axial line 24 passing through the center of gravity of the ridge schematized by the point G on the figure 2 .
  • the radial force F3 preferably applies in a radial plane which is situated between the two parallel axial faces 19, 20 of the retaining ring.
  • the radially outer face 21 of the retaining ring 7 has an annular cut (or blank) 26 so that the radial force F3 resulting from the bearing of this face 21 against the radially inner face 25 of the base 13 is located in a plane 27 axially offset with respect to a radial plane 28 of the rod passing through its center of gravity G.
  • the annular cutout 26 is made such that the radial force F3 is located in a plane 27 offset axially towards the axially inner face 20 of the retaining ring 7 with respect to the radial plane 28 of the rod passing through its center of gravity G. This makes it possible to create a mechanical balance between the forces F1 to F3 applying to the retaining ring.
  • the rod 7 is retracted into the groove 10 with the aid of compression tools.
  • the flange 11 and the ring 7 have correspondingly a plurality of notches (29 on the flange 11 and 30 on the rod) in which the claws of compression tools are positioned.
  • the rod 7 Before placing the flange 3, the rod 7 is inserted into the recess 6, its radially inner portion being preferably housed in the groove 10. With the aid of the compression tools, the ring 7 is retracted into the groove 10 and the flange 3 is brought closer by passing the foot 15 above the flange 11, the ring 7 and the claws. The flange 3 is then pressed against the axial face 4 of the disk 1 by applying axial pressure to it. The ring 7 then expands and its radially outer face 21 bears against the base 13. Finally, removes the axial pressure exerted on the flange 3, and the ring 7 is then compressed between the foot 15 and the flange 11 (this compression gives rise to the axial forces F1 and F2 represented on the figure 2 ). Disassembly of the flange is done by the reverse process.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (5)

  1. Axiale Haltevorrichtung für eine Schaufeldeckplatte (3) einer Turbinenscheibe (1), umfassend:
    eine Turbinenscheibe (1), umfassend eine Radialfläche (4), die eine ringförmige Aussparung (6) aufweist, die von mehreren Wänden begrenzt ist, von denen eine von der Innenseite eines Flansches (11) gebildet ist, der sich radial nach außen erstreckt;
    eine ringförmige Schaufeldeckplatte (3), die in ihrem radial inneren Teil eine ringförmige Basis (13) aufweist, die an der radial äußeren Wand der Aussparung (6) anliegt, und einen Fuß (15), der sich radial nach innen in der Aussparung der Scheibe ausgehend von der Basis erstreckt; und
    einen ringförmigen gespaltenen Haltering (7), der in der Aussparung (6) der Turbinenscheibe angeordnet ist, wobei dieser Ring (7) eine axial äußere Seite (19), die an einer axial inneren Seite (22) des Flansches (11) anliegt, was in einer ersten axialen Kraft (F1) mit einer im Wesentlichen axialen Richtung resultiert, eine axial innere Seite (20), die an einer axial äußeren Seite (17) des Fußes (15) anliegt, was in einer zweiten axialen Kraft (F2) mit einer im Wesentlichen axialen Richtung und einer zur ersten axialen Kraft (F1) entgegen gesetzten Richtung resultiert, wobei die axialen Kräfte (F1, F2) entlang von Linien angelegt werden, die radial beiderseits einer axialen Linie (24) angeordnet sind, die durch einen Schwerpunkt (G) des Halteringes verläuft, wobei die zweite axiale Kraft (F2) radial nach außen zur ersten axialen Kraft (F1) versetzt ist, und eine radial äußere Seite (21) aufweist, die an einer radial inneren Seite (25) der Basis (13) der Schaufeldeckplatte (3) anliegt, was in einer radialen Kraft (F3) mit einer im Wesentlichen radialen Richtung resultiert;
    dadurch gekennzeichnet, dass die radial äußere Seite (21) des Halteringes (7) einen ringförmigen Ausschnitt (26) aufweist, der derart angeordnet ist, dass die radiale Kraft (F3) in einer Ebene (27) vorhanden ist, die radial zur Innenseite (20) des Ringes in Bezug zur Radialebene (28) des Ringes, die durch seinen Schwerpunkt (G) verläuft, versetzt ist, um ein mechanisches Gleichgewicht der Kräfte (F1, F2, F3), die an den Haltering angelegt werden, zu erhalten.
  2. Vorrichtung nach Anspruch 1, dadurch gekennzeichnet, dass die Radialebene (27), in der sich die radiale Kraft (F3) befindet, die aus der Abstützung der radial äußeren Seite (21) des Halteringes (7) an der radial inneren Seite (25) der Basis (13) der Schaufeldeckplatte resultiert, zwischen den axial äußeren (19) und inneren (20) Seiten des Halteringes angeordnet ist.
  3. Vorrichtung nach einem der Ansprüche 1 und 2, dadurch gekennzeichnet, dass ein radial innerer Abschnitt des Halteringes (7) in einer Nut (10) angeordnet ist, die hinter dem Flansch (11) der Turbinenscheibe (1) vorgesehen ist.
  4. Turbine einer Turbomaschine, umfassend mindestens eine Haltevorrichtung nach einem der Ansprüche 1 bis 3.
  5. Turbomaschine, umfassend mindestens eine Haltevorrichtung nach einem der Ansprüche 1 bis 3.
EP07105588A 2006-04-10 2007-04-04 Axiale Haltevorrichtung für eine Schaufeldeckplatte einer Turbinenscheibe Active EP1845235B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0651286A FR2899636B1 (fr) 2006-04-10 2006-04-10 Dispositif de retention axiale d'un flasque de disque de rotor de turbomachine

Publications (2)

Publication Number Publication Date
EP1845235A1 EP1845235A1 (de) 2007-10-17
EP1845235B1 true EP1845235B1 (de) 2011-08-03

Family

ID=37654828

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07105588A Active EP1845235B1 (de) 2006-04-10 2007-04-04 Axiale Haltevorrichtung für eine Schaufeldeckplatte einer Turbinenscheibe

Country Status (6)

Country Link
US (1) US7857593B2 (de)
EP (1) EP1845235B1 (de)
JP (1) JP5337349B2 (de)
CA (1) CA2583847C (de)
FR (1) FR2899636B1 (de)
RU (1) RU2426889C2 (de)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2182170A1 (de) * 2008-10-30 2010-05-05 Siemens Aktiengesellschaft Gasturbine mit Dichtplatten an der Turbinenscheibe
FR2939834B1 (fr) * 2008-12-17 2016-02-19 Turbomeca Roue de turbine avec systeme de retention axiale des aubes
US9181810B2 (en) * 2012-04-16 2015-11-10 General Electric Company System and method for covering a blade mounting region of turbine blades
US10662793B2 (en) * 2014-12-01 2020-05-26 General Electric Company Turbine wheel cover-plate mounted gas turbine interstage seal
US10392966B2 (en) * 2016-09-23 2019-08-27 United Technologies Corporation Retaining ring end gap features
DE102018110879A1 (de) * 2018-05-07 2019-11-07 Schaeffler Technologies AG & Co. KG Anordnung zur axialen Lagesicherung eines Sonnenrads einer Planetengetriebestufe auf einer Rotorwelle einer elektrischen Maschine und Verwendung einer solchen Anordnung
US11525471B2 (en) * 2019-08-28 2022-12-13 GM Global Technology Operations LLC Snap ring retention
JP7394979B2 (ja) * 2019-10-18 2023-12-08 シーメンス エナジー グローバル ゲゼルシャフト ミット ベシュレンクテル ハフツング ウント コンパニー コマンディートゲゼルシャフト ２つのロータディスクの間に配置されたロータコンポーネントを有するロータ

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4304523A (en) * 1980-06-23 1981-12-08 General Electric Company Means and method for securing a member to a structure
US4890981A (en) * 1988-12-30 1990-01-02 General Electric Company Boltless rotor blade retainer
US5318405A (en) * 1993-03-17 1994-06-07 General Electric Company Turbine disk interstage seal anti-rotation key through disk dovetail slot
US5622475A (en) * 1994-08-30 1997-04-22 General Electric Company Double rabbet rotor blade retention assembly
JPH1136802A (ja) * 1997-07-25 1999-02-09 Ishikawajima Harima Heavy Ind Co Ltd タービンロータ
GB2332024B (en) * 1997-12-03 2000-12-13 Rolls Royce Plc Rotary assembly
US6884028B2 (en) * 2002-09-30 2005-04-26 General Electric Company Turbomachinery blade retention system
FR2857691B1 (fr) * 2003-07-17 2006-02-03 Snecma Moteurs Retention de flasque de rotor
GB2405183A (en) * 2003-08-21 2005-02-23 Rolls Royce Plc Ring and channel arrangement for joining components

Also Published As

Publication number Publication date
JP2007278292A (ja) 2007-10-25
CA2583847A1 (fr) 2007-10-10
CA2583847C (fr) 2014-03-04
RU2426889C2 (ru) 2011-08-20
FR2899636B1 (fr) 2008-07-04
JP5337349B2 (ja) 2013-11-06
US7857593B2 (en) 2010-12-28
FR2899636A1 (fr) 2007-10-12
US20070237645A1 (en) 2007-10-11
EP1845235A1 (de) 2007-10-17
RU2007113098A (ru) 2008-10-20

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