EP1910647A1 - Element de fixation d'aubes mobiles - Google Patents

Element de fixation d'aubes mobiles

Info

Publication number
EP1910647A1
EP1910647A1 EP06761823A EP06761823A EP1910647A1 EP 1910647 A1 EP1910647 A1 EP 1910647A1 EP 06761823 A EP06761823 A EP 06761823A EP 06761823 A EP06761823 A EP 06761823A EP 1910647 A1 EP1910647 A1 EP 1910647A1
Authority
EP
European Patent Office
Prior art keywords
rotor
securing element
base body
tool
securing
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
EP06761823A
Other languages
German (de)
English (en)
Other versions
EP1910647B1 (fr
Inventor
Alexander Böck
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1910647A1 publication Critical patent/EP1910647A1/fr
Application granted granted Critical
Publication of EP1910647B1 publication Critical patent/EP1910647B1/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • 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
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Definitions

  • the invention relates to a securing element for securing the position of rotor blades in at least predominantly axially extending grooves of a rotor body of a turbomachinery rotor. Furthermore, the invention relates to a method for mounting a securing element on a turbomachine rotor, in particular on a gas turbine rotor, and a turbomachine rotor.
  • Rotors of a turbomachine such as gas turbine rotors
  • the blades can either be an integral part of the rotor body or be anchored via blade roots in one or more grooves of the rotor body.
  • Rotors with integral blading are referred to as blisk or bling, depending on whether a disk-shaped or an annular rotor body is present.
  • blisk or bling depending on whether a disk-shaped or an annular rotor body is present.
  • rotors in which the blades are anchored via blade roots in a groove a distinction is made between rotors in which the blade roots of the blades are mounted either in so-called axial grooves of the rotor body or in a so-called circumferential groove thereof.
  • the present invention relates to a rotor of a turbomachine, in particular a gas turbine rotor, in which the blades are fastened via their blade roots in grooves which run at least predominantly in the axial direction of the rotor body, ie in axial grooves.
  • the locking elements are in turn secured in position in the annular grooves via at least one securing element or a locking plate, wherein the or each securing element is inflected into the annular grooves of the rotor body and the rotor blades in a free space between two adjacent locking elements.
  • fuse elements known from the prior art, there is the problem that they spring back after mounting in the annular grooves and then lie undefined on the rotor base body. This affects the function of the fuse elements.
  • the present invention is based on the problem of providing a novel securing element for securing the position of moving blades. This problem is solved by a fuse element according to claim 1.
  • the securing element according to the invention has a plate-shaped base body, wherein the base body has an approximately central recess which is formed between two end portions of the base body and defines a central portion extending between the two end portions of the base body, and wherein the two end portions have mutually parallel bearing surfaces.
  • the securing element according to the invention it is ensured that the same after mounting in the annular grooves of the rotor base body and blades with bearing surfaces which are formed on the end portions of the main body of the securing element, flat or flat against the rotor body.
  • the fuse elements according to the invention allow a very defined and reproducible mounting of the same in the annular grooves of the rotor body and blades. This ensures the full functionality of the security elements.
  • FIG. 1 shows a detail of a gas turbine rotor according to the prior art in a perspective side view
  • FIG. 2 shows a further detail of a gas turbine rotor according to the prior art in front view
  • FIG. 3a-3b views for illustrating the known from the prior art assembly of fuse elements in a gas turbine rotor according to Figures 1 and 2 ..; 4 shows an inventive securing elements in side view;
  • Fig. 5 the fuse element according to the invention in an intermediate position during mounting, namely after the bending of the same in annular grooves of the rotor body and blades;
  • FIG. 6 shows the securing element according to the invention in a further intermediate position during assembly together with a tool
  • FIG. 7 the securing element according to the invention in mounted position
  • Fig. 8 the securing element according to the invention also in the mounted position.
  • FIGS. 4 to 8 Before the present invention will be described in more detail below with reference to FIGS. 4 to 8, a gas turbine rotor known from the prior art with grooves running in at least predominantly axially direction - so-called axial grooves - shall be described in advance with reference to FIGS. 1 to 3. guided blade feet of blades are described.
  • FIG. 1 and 2 show sections of a known from the prior art gas turbine rotor 10, which has a rotor body 11 and a plurality of rotor blades 12.
  • Each of the rotor blades 12 has an airfoil 13 and a blade root 14.
  • In the rotor base 11 a plurality of axially extending axial grooves 15 are introduced, each rotor blade 12 is anchored with its blade root 14 in such an axial groove 15 in the rotor body 11.
  • Locking elements 16 and securing elements 17 serve to axially fix or axially secure the moving blades 12 introduced into the axial grooves 15.
  • the securing elements 17 are also referred to as locking plates, the locking elements 16 as retaining plates.
  • Radially on the outside, the rotor blades 12 carry sections of an outer shroud 18, wherein the rotor blades 12 are connected to one another in the region of the outer shroud 18 via a so-called Z-toothing.
  • the locking elements 16 and the securing elements 17 are guided in the assembled state of the gas turbine rotor 10 in annular grooves, namely in an annular groove 19 of the rotor base body 11 and in an annular groove 20 of the rotor blades 12th
  • FIG. 4 shows an inventive securing element 23 for securing the position of the rotor blades 12 in the axial grooves 15 of the rotor base body 11 prior to assembly thereof.
  • the securing element 23 according to the invention has a plate-shaped base body 24, wherein the base body 24 has an approximately central recess 25.
  • the recess 25 is formed between two end portions 26 and 27 of the base body 24 and defines a central portion 28 thereof.
  • the securing element 23 according to the invention has mutually parallel bearing surfaces 29 and 30.
  • the two end sections 26 and 27 have alignment surfaces 29 and 20 aligned prior to assembly.
  • the central portion 28 is not arched prior to assembly.
  • Such a securing element 23 according to the invention can be bent in the assembly analogous to FIGS. 3 a to 3 b between annular grooves 19 and 20 of the rotor main body 11 and rotor blades 12 under elastic and plastic deformation of the securing element 23, wherein after the securing element 23 has been bent in, the same as in FIG shown position or shape occupies.
  • the bearing surfaces 29 and 30 are curved, as well as the central portion 28th
  • a punch-like tool 33 is pressed onto the central portion 28 of the securing element 23, wherein the central portion 28 and the punch-like tool 33 are dimensioned such that the punch-like tool 33 exclusively in the central portion 28th at a distance from the end portions 26 and 27 of the securing member 23 is effective on the same.
  • the stamp-like tool 33 With the aid of the stamp-like tool 33, the securing element ment 23 bent back so that the securing element 23 is bent over in the central portion 28, so that after the removal of the punch-like tool 33, the securing element 23 assumes the position shown in Fig. 7.
  • the securing element 23 is plastically deformed in the middle section 28 in regions 34 and 35, at which edge sections of the stamp-like tool 33, to form the overbending section 31 shown in FIG.
  • the bearing surfaces 29 and 30 of the end portions 26 and 27 are parallel again to each other, so that the same cursing again after bending back.
  • the bearing surfaces 29 and 30 of the end portions 26 and 27 accordingly assume the position shown in Fig. 4 after bending back of the securing element 23.
  • the middle section 23 remains after removal of the punch-like tool 33, the already mentioned, curved overbend section 31st
  • the securing element 23 according to the invention has a projection 36 in the region of the end section 27.
  • This projection 36 as can be seen in FIG. 8, is mounted in the annular groove 19 of the rotor base body during assembly of the securing element according to the invention 11 threaded.
  • the projection 36 is dimensioned such that a center of gravity 37 of the securing element 23 according to the invention is offset relative to a radial abutment 38 of the end portion 26 in the annular groove of the blade root 12 such that in operation acting on the securing element 23 centrifugal forces the projection 36 against a sealing surface 32nd Press in the region of the annular groove 19 of the rotor body 11. This results in an optimized sealing effect for the securing element 23 according to the invention.

Landscapes

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

Abstract

L'invention concerne un élément de fixation destiné à fixer la position d'aubes mobiles dans des rainures, s'étendant essentiellement de façon axiale, d'un corps de base de rotor d'une turbomachine, comportant un corps de base (24) en forme de plaque. Le corps de base (24) présente un évidement (25) essentiellement central formé entre deux sections terminales (26, 27) du corps de base (24), définissant une section centrale (28) du corps de base (24), s'étendant entre les deux sections terminales (26, 27), les deux sections terminales (26, 27) présentant des surfaces d'appui parallèles (29, 20).
EP06761823A 2005-07-30 2006-07-19 Procédé de montage d'un élément de sécurité sur un rotor de turbomachine Expired - Fee Related EP1910647B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102005035901A DE102005035901A1 (de) 2005-07-30 2005-07-30 Sicherungselement
PCT/DE2006/001246 WO2007014543A1 (fr) 2005-07-30 2006-07-19 Element de fixation d'aubes mobiles

Publications (2)

Publication Number Publication Date
EP1910647A1 true EP1910647A1 (fr) 2008-04-16
EP1910647B1 EP1910647B1 (fr) 2011-09-07

Family

ID=37110385

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06761823A Expired - Fee Related EP1910647B1 (fr) 2005-07-30 2006-07-19 Procédé de montage d'un élément de sécurité sur un rotor de turbomachine

Country Status (4)

Country Link
US (1) US8128374B2 (fr)
EP (1) EP1910647B1 (fr)
DE (1) DE102005035901A1 (fr)
WO (1) WO2007014543A1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2918106B1 (fr) * 2007-06-27 2011-05-06 Snecma Dispositif de retenue axiale d'aubes montees sur un disque de rotor de turbomachine.
DE102008013118B4 (de) * 2008-03-07 2014-03-27 Man Diesel & Turbo Se Anordnung zum Befestigen von Turbinenschaufeln
US8753090B2 (en) * 2010-11-24 2014-06-17 Rolls-Royce Corporation Bladed disk assembly
WO2014137435A2 (fr) * 2013-03-05 2014-09-12 Rolls-Royce North American Technologies, Inc. Procédé de rétention de plaques de capot segmentées de turbine
EP2986824B1 (fr) 2013-04-18 2020-05-27 United Technologies Corporation Amortisseur à minidisque de turbine pour turbine à gaz
GB2511584B (en) 2013-05-31 2015-03-11 Rolls Royce Plc A lock plate
JP6218232B2 (ja) * 2014-03-14 2017-10-25 本田技研工業株式会社 タービンホイール
GB201604473D0 (en) 2016-03-16 2016-04-27 Rolls Royce Plc A bladed rotor arrangement and a lock plate for a bladed rotor arrangement

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3045329A (en) * 1959-07-30 1962-07-24 Gen Electric Method for assembling tongue-and-groove members with locking keys
FR2419389A1 (fr) 1978-03-08 1979-10-05 Snecma Perfectionnements aux flasques de rotors de turbomachines
US5211407A (en) 1992-04-30 1993-05-18 General Electric Company Compressor rotor cross shank leak seal for axial dovetails
GB9302064D0 (en) 1993-02-03 1993-03-24 Rolls Royce Plc Balanced rotor
GB9517369D0 (en) * 1995-08-24 1995-10-25 Rolls Royce Plc Bladed rotor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2007014543A1 *

Also Published As

Publication number Publication date
US20090092497A1 (en) 2009-04-09
WO2007014543A1 (fr) 2007-02-08
DE102005035901A1 (de) 2007-02-01
US8128374B2 (en) 2012-03-06
EP1910647B1 (fr) 2011-09-07

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