EP1524409B1 - Dispositif de verrouillage d'aube - Google Patents

Dispositif de verrouillage d'aube Download PDF

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Publication number
EP1524409B1
EP1524409B1 EP04003299A EP04003299A EP1524409B1 EP 1524409 B1 EP1524409 B1 EP 1524409B1 EP 04003299 A EP04003299 A EP 04003299A EP 04003299 A EP04003299 A EP 04003299A EP 1524409 B1 EP1524409 B1 EP 1524409B1
Authority
EP
European Patent Office
Prior art keywords
retaining ring
blade
retaining
accordance
arrangement
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 - Fee Related
Application number
EP04003299A
Other languages
German (de)
English (en)
Other versions
EP1524409A2 (fr
EP1524409A3 (fr
Inventor
Tim MÖLLER
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1524409A2 publication Critical patent/EP1524409A2/fr
Publication of EP1524409A3 publication Critical patent/EP1524409A3/fr
Application granted granted Critical
Publication of EP1524409B1 publication Critical patent/EP1524409B1/fr
Anticipated expiration legal-status Critical
Expired - Fee Related 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
    • F01D5/32—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
    • 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
    • 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
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity

Definitions

  • the invention relates to a blade restraint according to the preamble of the main claim.
  • the invention relates to a blade restraining device for the axial fixation of blades on a disc of a gas turbine, wherein connected to the blade, provided with a profiled blade root is inserted into an appropriate axial profile of the profile of the disc and axially by means of a split retaining ring is fixed, wherein the retaining ring is at least partially received in a groove of the Schaufelfu ⁇ es.
  • a bucket restraint device for example, shows the US 6,234,756 B1 ,
  • the DE 18 30 030 U discloses a blade retention device having a retaining ring which has a substantially rectangular cross-section and is inserted in a circumferential annular groove of the disc.
  • the annular groove has a radially outer bearing surface for the retaining ring.
  • the invention has for its object to provide a blade retaining device of the type mentioned, which is easy to assemble with a simple structure and simple, cost-effective applicability and has a low space requirement.
  • the disc is provided with a circumferential annular groove which has an axially inner bearing surface for the retaining ring and that the retaining ring is elastically deformable at least in the axial direction.
  • the blade restraining device according to the invention is characterized by a number of significant advantages.
  • the blade restraining device according to the invention also allows installation in a multi-stage welded rotor in which at least one stage consists of blades which have an outlet opening in the blade root (micro-turbine).
  • the invention enables a favorable introduction of the centrifugal forces below the blade root and thus a low weight of blade and disc. This also extends the life of the entire arrangement.
  • the retaining ring can be configured as a sheet metal part, in comparison to the expensive forged parts known from the prior art.
  • Another significant advantage results from an easier and faster installation and removal and the resulting cost savings.
  • the installation of the blade restraint device according to the invention ensures a high repeatability and thus a high component reliability.
  • the annular groove is provided with at least one insertion opening. Through this insertion, the retaining ring can be inserted or removed easily and without damage.
  • the retaining ring consists of two or more layers of a metallic material, which are interconnected at one end of the retaining ring. As a result, the elasticity of the retaining ring is considerably increased. This in turn means that the retaining ring can be inserted into the groove and remains free of deformation in this.
  • the retaining ring is provided with an anti-rotation device in order to prevent the retaining ring from wandering in the circumferential direction.
  • the rotation is preferably formed in the form of a radially directed approach of the retaining ring, which is preferably provided at one end of the retaining ring.
  • the retaining ring can be inserted and fixed by means of the rotation.
  • the retaining ring has a strip-shaped cross section. By such a rectangular cross-section sufficient penetration of the retaining ring is ensured in the groove of the blade root or the disc.
  • the retaining ring according to the invention may be divided in the scope of several segments, for example in six segments.
  • the Fig. 1 shows a simplified representation of a rotatably mounted disc 2 of a gas turbine engine, to which a plurality of blades 1 are attached. Adjacent stator blades are provided with the reference numeral 10. Incidentally, reference may be made to the general structure of the prior art, so that it can be dispensed with its description.
  • the blades 1 each have a blade root 3, which is provided with a profile which is insertable into a profiled axial groove 5 of the disc 2.
  • a blade root 3 which is provided with a profile which is insertable into a profiled axial groove 5 of the disc 2.
  • the lower portions of the blade roots 3 are each provided with a circumferential groove 6.
  • the blade restraining device further comprises a divided into individual segments retaining ring 4, which is provided at its free end with a radially outwardly facing lug 9 (see in particular Fig. 6 ).
  • the annular groove 7 has one or more insertion openings 8, which are realized by an interruption of the abutment leg 11. Through these insertion 8, it is possible to insert the elastically deformable in the axial direction retaining ring 4, as can be seen from the illustrations of FIGS. 2 and 3 results.
  • upper disc grooves are also formed on the so-called disc fingers 12 (not shown), then the upper disc grooves would also have to be provided with corresponding insertion openings.
  • the retaining ring 4 After the retaining ring 4 has been threaded, this snaps by its elasticity in the grooves 6 and 7 and is thus secured.
  • This spring elasticity is caused in particular by the multi-layered design of the retaining ring 4.
  • the retaining ring 4 consists of two or more layers, which are all connected at one end, for example, welded.
  • the Versch discloseen can be done, for example, at the end at which the rotation is formed by means of the approach 9.

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)

Claims (8)

  1. Dispositif de verrouillage d'aubes (1) destiné à la fixation axiale d'aubes (1) sur un disque (2), comprenant un disque (2), des aubes (1) et un anneau de maintien segmenté (4), sachant qu'un pied d'aube (3) relié à l'aube (1) et doté d'un profil est introduit dans une gorge axiale (5) du disque (2) adaptée au profil, et est fixé dans le sens axial au moyen de l'anneau de maintien segmenté (4), que l'anneau de maintien (4) est logé au moins partiellement dans une gorge (6) du pied d'aube (3), que le disque (2) est muni d'une gorge annulaire circonférentielle (7) qui présente une surface d'appui radiale intérieure pour l'anneau de maintien (4) et que l'anneau de maintien (4) est déformable par élasticité au moins dans le sens axial, caractérisé en ce que l'anneau de maintien (4) est constitué de deux ou plusieurs couches qui sont reliées entre elles à une extrémité de l'anneau de maintien (4).
  2. Dispositif de verrouillage d'aubes selon la revendication n° 1, caractérisé en ce que la gorge annulaire (7) est munie d'au moins un orifice d'insertion (8).
  3. Dispositif de verrouillage d'aubes selon la revendication n° 1 ou n° 2, caractérisé en ce qu'est prévu un dispositif antirotation pour l'anneau de maintien (4).
  4. Dispositif de verrouillage d'aubes selon la revendication n° 3, caractérisé en ce que le dispositif antirotation comprend un talon (9) de l'anneau de maintien (4), qui est orienté dans le sens radial.
  5. Dispositif de verrouillage d'aubes selon une des revendications n° 3 ou n° 4, caractérisé en ce que le dispositif antirotation est prévu sur une extrémité de l'anneau de maintien (4).
  6. Dispositif de verrouillage d'aubes selon une des revendications n° 1 à n° 5, caractérisé en ce que l'anneau de maintien (4) a une section transversale lamellée.
  7. Dispositif de verrouillage d'aubes selon une des revendications n° 1 à n° 6, caractérisé en ce que l'anneau de maintien (4) est divisé en segments dans le sens circonférentiel.
  8. Dispositif de verrouillage d'aubes selon la revendication n° 7, caractérisé en ce que sont prévus six segments.
EP04003299A 2003-10-16 2004-02-13 Dispositif de verrouillage d'aube Expired - Fee Related EP1524409B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10348198A DE10348198A1 (de) 2003-10-16 2003-10-16 Schaufelrückhaltevorrichtung
DE10348198 2003-10-16

Publications (3)

Publication Number Publication Date
EP1524409A2 EP1524409A2 (fr) 2005-04-20
EP1524409A3 EP1524409A3 (fr) 2007-01-24
EP1524409B1 true EP1524409B1 (fr) 2011-08-10

Family

ID=34353443

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04003299A Expired - Fee Related EP1524409B1 (fr) 2003-10-16 2004-02-13 Dispositif de verrouillage d'aube

Country Status (3)

Country Link
US (1) US7244105B2 (fr)
EP (1) EP1524409B1 (fr)
DE (1) DE10348198A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10876429B2 (en) 2019-03-21 2020-12-29 Pratt & Whitney Canada Corp. Shroud segment assembly intersegment end gaps control

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004016977B4 (de) * 2004-04-07 2006-11-23 Mtu Aero Engines Gmbh Rotor für eine Turbomaschine
US8105041B2 (en) * 2005-09-07 2012-01-31 Siemens Aktiengesellschaft Arrangement for axially securing rotating blades in a rotor, sealing element for such an arrangement, and use of such an arrangement
DE102006054154B4 (de) * 2006-11-16 2014-03-13 Man Diesel & Turbo Se Abgasturbolader
US8221083B2 (en) 2008-04-15 2012-07-17 United Technologies Corporation Asymmetrical rotor blade fir-tree attachment
US8162615B2 (en) * 2009-03-17 2012-04-24 United Technologies Corporation Split disk assembly for a gas turbine engine
FR2951224B1 (fr) * 2009-10-13 2011-12-09 Turbomeca Roue de turbine equipee d'un jonc de retenue axiale verrouillant des pales par rapport a un disque
US9051845B2 (en) 2012-01-05 2015-06-09 General Electric Company System for axial retention of rotating segments of a turbine
JP5675674B2 (ja) * 2012-02-29 2015-02-25 三菱重工業株式会社 タービン動翼の抜け止め構造およびこれを備えた回転機械
US9140136B2 (en) 2012-05-31 2015-09-22 United Technologies Corporation Stress-relieved wire seal assembly for gas turbine engines
US9366145B2 (en) 2012-08-24 2016-06-14 United Technologies Corporation Turbine engine rotor assembly
US9790803B2 (en) 2013-03-08 2017-10-17 United Technologies Corporation Double split blade lock ring
US10724384B2 (en) * 2016-09-01 2020-07-28 Raytheon Technologies Corporation Intermittent tab configuration for retaining ring retention

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1830030U (de) * 1961-03-04 1961-04-27 Gen Electric Sicherung der schaufeln in den laeufern von turbinen, kompressoren od. dgl.
US3656865A (en) * 1970-07-21 1972-04-18 Gen Motors Corp Rotor blade retainer
FR2603333B1 (fr) * 1986-09-03 1990-07-20 Snecma Rotor de turbomachine comportant un moyen de verrouillage axial et d'etancheite d'aubes montees dans des brochages axiaux du disque et procede de montage
GB2258273B (en) * 1991-08-02 1994-08-10 Ruston Gas Turbines Ltd Rotor blade locking arrangement
GB9517369D0 (en) * 1995-08-24 1995-10-25 Rolls Royce Plc Bladed rotor

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10876429B2 (en) 2019-03-21 2020-12-29 Pratt & Whitney Canada Corp. Shroud segment assembly intersegment end gaps control

Also Published As

Publication number Publication date
DE10348198A1 (de) 2005-05-12
US7244105B2 (en) 2007-07-17
EP1524409A2 (fr) 2005-04-20
US20050084376A1 (en) 2005-04-21
EP1524409A3 (fr) 2007-01-24

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