EP1650405B1 - Rotor d'une turbomachine, notamment rotor d'une turbine à gaz - Google Patents

Rotor d'une turbomachine, notamment rotor d'une turbine à gaz Download PDF

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Publication number
EP1650405B1
EP1650405B1 EP05022065A EP05022065A EP1650405B1 EP 1650405 B1 EP1650405 B1 EP 1650405B1 EP 05022065 A EP05022065 A EP 05022065A EP 05022065 A EP05022065 A EP 05022065A EP 1650405 B1 EP1650405 B1 EP 1650405B1
Authority
EP
European Patent Office
Prior art keywords
rotor
blade
blades
hump
channel
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.)
Not-in-force
Application number
EP05022065A
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German (de)
English (en)
Other versions
EP1650405A1 (fr
Inventor
Hermann Klingels
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 EP1650405A1 publication Critical patent/EP1650405A1/fr
Application granted granted Critical
Publication of EP1650405B1 publication Critical patent/EP1650405B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides

Definitions

  • the invention relates to a rotor of a turbomachine, in particular a gas turbine rotor, according to the preamble of patent claim 1.
  • 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 circumferential groove thereof.
  • the present invention relates to a rotor of a turbomachine, in particular a gas turbine rotor, in which the rotor blades are fastened via their blade roots in a circumferential groove of the rotor base body, that is in a circumferential groove.
  • the circumferential grooves In rotors in which the blades are mounted with their blade roots in so-called circumferential grooves, the circumferential grooves have at least two diametrically opposed filler openings to introduce the blade roots of the blade in the corresponding circumferential groove.
  • the filling openings are formed in the state of the art by constrictions in the region of groove wall limbs of the circumferential groove, wherein in operation abut the blade roots with support flanks on the Nutwandschenkeln. Notches are formed on the groove wall limbs through the filling openings, which are exposed to a high voltage level during operation of the rotor. As a result, the life of the rotor is reduced.
  • a rotor with a blade attachment which solves the basic problems of the constructions described above.
  • the circumferential groove on the rotor and the blade roots are shaped and dimensioned such that the blade roots can be inserted into the groove by a tilting or pivoting movement without having to widen the groove in one place and thus weaken it.
  • the width of the blade roots in the circumferential direction may be about as large as the width of the blade platform, whereby the mechanical strength and the life of the unit rotor body / blades can be significantly increased.
  • the blades After insertion into the circumferential groove on the rotor base body, the blades must be held in a radially upright position via suitable spacers in order to prevent unthreading out of the groove by unintentional tilting or pivoting.
  • suitable spacers can be integrally formed on the rotor base body or designed as separate additional elements.
  • the blades and the separate spacers must be secured against wandering in the circumferential direction, for which form-fitting elements are suitable.
  • the spacers, whether integral or separate, are here designed to extend virtually completely around the circumference of the rotor. This results in a relevant additional weight for the rotor as a whole.
  • the present invention is based on the problem to provide a strength and life-optimized rotor of a turbomachine.
  • a plurality of hump-like projections are positioned at a distance from one another on both groove wall legs of the groove in the circumferential direction, with two rotor blades each being mounted with their blade platforms on two mutually opposite projections positioned on different groove wall legs of the groove.
  • a securing element which defines a relative position between the rotor blades and the rotor body in the circumferential direction, preferably extends through two mutually opposite, hump-shaped projections positioned on different groove wall limbs.
  • FIG. 1 Before describing the present invention in greater detail below with reference to FIGS. 2 to 9, it will be described in advance, with reference to FIG. 1, a prior art gas turbine rotor having blades guided in a circumferential groove.
  • FIG. 1 shows a detail of a gas turbine rotor 10 according to the prior art, the gas turbine rotor 10 being formed by a rotor main body 11 and a plurality of rotor blades 12.
  • the rotor blades 12 each have an airfoil 13 and a blade root 14, wherein a blade platform 15 is formed between the airfoil 13 and the blade root 14.
  • the rotor blades 12 are fastened or guided in a circumferentially extending groove 16 of the rotor base body 11 via their blade roots 14.
  • the circumferentially extending groove 16 is open radially on the outside and is bounded by two mutually opposite groove wall limbs 17 and 18, respectively.
  • the entire set of blades 12 is displaced by half a blade pitch in the circumferential direction, so that all contact surfaces of the blade roots 14 below the supporting Nutwandschenkel 17th and 18 are therefore not in the region of a recess or notch 19 of the groove wall legs 17, 18. It follows immediately that the blade roots 14 seen in the circumferential direction have only approximately half the width of the blade platforms 15.
  • FIG. 2 to 4 show a first embodiment of a gas turbine rotor 20 according to the invention, which has a rotor base body 21 and a plurality of rotor blades 22.
  • the blades 22 in turn each have an airfoil 23, a blade root 24 and a between the Paddle blade 23 and the blade root 24 arranged blade platform 25.
  • the rotor body 21 has a circumferentially extending groove 26 which is bounded by lateral Nutwandschenkeln 27 and 28, wherein the blades 22 with their blade roots 24 in the circumferentially extending groove 26th are guided.
  • the blade roots 24 bear on the groove wall limbs 27 and 28, forming so-called support flanks 29.
  • the circumferential groove 26 and the blade roots 24 have such a profile that the blade roots 24 of the blades 22 can be inserted into the circumferential groove 26 of the rotor base body 21 by means of a tilting or pivoting movement, without Strength-minimizing constrictions or indentations in the groove wall legs 27 and 28 are required.
  • Fig. 3 visualizes the tilting or pivoting movement of the blade 22 during insertion of the blade root 24 thereof in the circumferential groove 26 with a double arrow 30.
  • the profile of the blade roots 24 of the blades 22 is dimensioned such that in the circumferential direction, a width of the blade roots 24 in about or approximately one width of the respective blade platform 25 of the respective blade 22 corresponds.
  • the inventive profiling of the circumferential groove 26 and the blade roots 24 is achieved, that on the one hand strength minimizing notches in the Nutwandschenkeln 27 and 28 can be omitted, and that on the other hand, the circumferential extent of the support flanks 29 is significantly increased compared to the prior art. As a result, the service life of the gas turbine rotor 20 can be increased.
  • the blades 22 are aligned relative to the rotor body 21 so that the blade roots 24 forming the support flanks 29 on the Nutwandschenkeln 27 and 28 of Groove 26 abut.
  • a relative position between the blades 22 and the rotor body 21 is defined by spacers, wherein the spacers between the circumferentially extending Nutwandschenkeln 27 and 28 and the blade platforms 25 of the blades 22 are positioned.
  • the spacers are formed as a hump-like projections 31 which extend on both sides of the groove 26 and are therefore positioned in the region of both Nutwandschenkel 27 and 28. Seen in the circumferential direction are on both sides of the circumferential groove 26 at a distance from each other more hump-like projections 31st educated. Accordingly, in each case a recess 32 is formed between two circumferentially adjacent, hump-shaped projections 31. In the area of both groove wall limbs 27 and 28, a plurality of hump-like projections 31 are thus positioned at a distance from one another in the circumferential direction.
  • each blade 22 is mounted at one end via its platform 25 to two bump-like projections 31 which are positioned at different Nutwandschenkeln 27 and 28.
  • the opposite ends of the blade platforms 25 they are not mounted on the bump-like projections 31, but rather extend in the region of a recess 32 between circumferentially spaced-apart projections 31st
  • the spacers formed in the embodiment of FIGS. 2 to 4 as hump-like projections 31 accordingly define, in the mounted state of the rotor blades 22, a radial relative position of the rotor blades 22 relative to the rotor main body 21 in such a way that a radially inward displacement of the rotor blades 22 is prevented.
  • the hump-like projections 31 are each an integral part of the corresponding Nutwandschenkels 27 and 28 and extend from the respective Nutwandschenkel 27 and 28 radially outward.
  • the relative position between the blades 22 and the base body 21 of the gas turbine rotor 20 is defined by securing elements 33 which extend through two opposing, at different Nutwandschenkeln 27 and 28 positioned, hump-shaped projections 31.
  • the securing elements 33 are formed as rivets, which are guided in bores 34 of the hump-like projections 31.
  • the securing element 33 formed as a rivet is thereby fixed in its position that a tip 35 of the securing element 33 is bent in the direction of the arrow 36.
  • each blade 22 has on the side at which it is adjacent to the securing element 33, via a recess or recess 37 through which the fuse element 33 can be inserted, and on the other hand, the mounting position of the blades 22 in the rotor body 21 pretends ,
  • the gas turbine rotor according to the invention has a guide of the blade roots of the rotor blades in a circumferential groove of the rotor main body, in which no strength-minimizing indentations in the Nutwandschenkeln the circumferential groove are required. Rather, the circumferential groove and the blade roots are profiled so that the blade roots can be introduced via a tilting movement in the circumferential groove, and that the width of the blade roots in the circumferential direction approximately corresponds to the width of the respective blade platform and thus compared to the prior art significantly larger support flanks between the Shovel feet and the Nutwandschenkeln be enabled.
  • the relative position between the blades and the rotor disc body is defined by spacers formed as hump-like projections, which in the preferred embodiment are an integral part of the groove wall limbs.
  • the relative position is defined by securing elements, which extend through two opposite, positioned on different Nutenwandschenkeln, hump-like projections.
  • the main advantage of this embodiment of a gas turbine rotor according to the invention over the prior art is that the filling openings required in the prior art in the groove wall limbs, which reduce the strength and the service life of the blade-rotor connection, can be dispensed with.
  • Another major advantage is that significantly larger support flanks are made possible between the blade roots and the groove wall limbs, whereby the surface pressure in the region of the wings and thus the so-called Frettinggefahr is reduced.
  • the gas turbine rotor according to the invention can absorb significantly higher forces during operation than the rotors known from the prior art, which prolongs its service life and widens its range of application.
  • FIG. 5 shows a second exemplary embodiment of a gas turbine rotor 38 according to the invention.
  • the embodiment of FIG. 5 largely corresponds to the embodiment of FIGS. 2 to 4, so that the same reference numerals are used to avoid unnecessary repetitions for the same components.
  • the embodiment of FIG. 5 differs from the embodiment of FIGS. 2 to 4 only by the configuration of the securing element 33, which is designed in the embodiment of FIG. 5 as a symmetrical rivet.
  • FIGS. 6 to 9 Further examples that bleach the understanding of the invention are shown in FIGS. 6 to 9. Again, 39 like reference numerals are used for the same components of the gas turbine rotor and it will be discussed below only on the details that distinguish the examples of Figs. 6 to 9 from the embodiment of FIGS. 2 to 4.
  • the example of Fig. 6 differs from the embodiment of FIGS. 2 to 4 by the configuration of the spacers which define the relative position of the blades 22 to the rotor disc main body 21 in the radial direction.
  • a first spacer is formed on a groove wall limb 27 of the circumferential groove 26 as a projection 40 closed in the circumferential direction of the groove 26.
  • the projection 40 is an integral part of the Nutwandschenkels 27 and extending from the Nutwandschenkel 27 radially outward toward the platform 25 of the blade 22. As already mentioned, the projection 40 is closed in the example of FIG. 6 in the circumferential direction. In the region of the opposite groove wall leg 28 serves as a spacer also closed in the circumferential direction or a circumferentially segmented locking ring 41 which is inserted between the Nutwandschenkel 28 and the platforms 25 of the blade 22 and is fixed in this position via a locking ring 42. The locking ring 41 provides an anti-rotation and tilt protection for the blades 22 ready.
  • FIGS. 7 to 9 differs from the embodiment of FIGS. 2 to 4 again by the configuration of the spacers, which define the relative position of the blades 22 to the rotor disc main body 21 in the radial direction.
  • a first spacer is formed on a groove wall limb 27 of the circumferential groove 26 as a projection 43 closed in the circumferential direction of the groove 26.
  • the projection 43 is an integral part of the Nutwandschenkels 27 and extending from the Nutwandschenkel 27 radially outward toward the platform 25 of the blade 22. As already mentioned, the projection 43 is closed in the example of FIGS. 7 to 9 in the circumferential direction.
  • the relative position in the circumferential direction between the blades 22 and the main body 21 of the gas turbine rotor 20 is defined by a securing element 46.
  • the securing elements 46 are formed by a rivet 47 and a closure member 48 cooperating with the rivet 47 for the opening 45.
  • the securing elements 46 extend according to FIGS. 7 and 8 through the projections 43 and 44 in the region of the groove wall limbs 27 and 28.
  • the projection 44 is preferably interrupted by two or four openings 45, two each Openings 45 are diametrically opposed, and wherein each opening 45 is closed by a closure element 48 of a securing element 46.

Landscapes

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

Claims (5)

  1. Rotor d'une machine turbo, en particulier rotor de turbine à gaz, comprenant un corps de base du rotor (21), le corps de base du rotor (21) présentant une rainure (26) s'étendant dans le sens périphérique du corps de base du rotor (21), et plusieurs aubes mobiles (22), chaque aube mobile (22) présentant une ailette (23), une emplanture d'aube (24) et une plate-forme d'aube (25) positionnée entre l'ailette (23) et l'emplanture d'aube (24) et ancrée par son emplanture d'aube (24) dans la rainure (26) du corps de base du rotor (21), la rainure (26) et les emplantures d'aubes (24) présentant un profil tel que les emplantures d'aubes '(24) des aubes mobiles (22) peuvent être introduites par un mouvement de basculement ou de pivotement dans la rainure (26) du corps de base du rotor (21), s'étendant dans le sens périphérique, sachant qu'une largeur de l'emplanture d'aube (24) correspond dans le sens périphérique approximativement à une largeur de la plate-forme d'aube (25) de l'aube mobile (22) concernée, une position relative entre les aubes mobiles (22) et le corps de base du rotor (21) étant définie par des écarteurs dans le sens radial, les écarteurs étant positionnés radialement à l'extérieur de la zone critique au niveau de la charge de la rainure (26) entre des branches de paroi de rainure (27, 28) agencées dans le sens périphérique et les plates-formes d'aubes (25) des aubes mobiles (22), les écarteurs étant conçus comme des saillies (31) en forme de bosse et étant positionnés à distance les uns des autres de telle sorte que entre respectivement deux saillies voisines en forme de bosse, un évidement (32) est réalisé pour l'introduction des emplantures d'aubes (24) par un mouvement de basculement ou de pivotement dans la rainure (26), caractérisé en ce que, sur lesdites branches de la paroi de rainure (27, 28) plusieurs saillies (31) en forme de bosse sont positionnées dans le sens périphérique à distance les unes des autres, sachant que à chaque fois deux aubes mobiles (22) avec leurs plates-formes d'aubes (25) sont logées sur respectivement deux saillies (31) se faisant face et positionnées sur différentes branches de paroi de rainure (27, 28).
  2. Rotor selon la revendication 1, caractérisé en ce qu'à travers à chaque fois deux saillies (31) en forme de bosse, se faisant face, positionnées sur différentes branches de paroi de rainure (27, 28) s'étend un élément de sécurité (33), qui définit dans le sens périphérique une position relative entre les aubes mobiles (22) et le corps de base du rotor (21).
  3. Rotor selon la revendication 2, caractérisé en ce que les éléments de sécurité (33) sont conçus comme des rivets.
  4. Rotor selon l'une quelconque des revendications 1 à 3, caractérisé en ce que les saillies (31) en forme de bosse sont une partie intégrale des branches de paroi de rainure (27, 28) concernées et s'étendent à partir de la branche de paroi de rainure (27, 28) concernée radialement vers l'extérieur.
  5. Turbine à gaz, en particulier groupe motopropulseur, comprenant au moins un rotor selon l'une quelconque des revendications 1 à 4.
EP05022065A 2004-10-20 2005-10-10 Rotor d'une turbomachine, notamment rotor d'une turbine à gaz Not-in-force EP1650405B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102004051116A DE102004051116A1 (de) 2004-10-20 2004-10-20 Rotor einer Turbomaschine, insbesondere Gasturbinenrotor

Publications (2)

Publication Number Publication Date
EP1650405A1 EP1650405A1 (fr) 2006-04-26
EP1650405B1 true EP1650405B1 (fr) 2007-12-05

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EP05022065A Not-in-force EP1650405B1 (fr) 2004-10-20 2005-10-10 Rotor d'une turbomachine, notamment rotor d'une turbine à gaz

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US (1) US7708529B2 (fr)
EP (1) EP1650405B1 (fr)
DE (2) DE102004051116A1 (fr)

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US8414268B2 (en) * 2009-11-19 2013-04-09 United Technologies Corporation Rotor with one-sided load and lock slots
FR2961847B1 (fr) * 2010-06-25 2012-08-17 Snecma Roue mobile a aubes en materiau composite pour moteur a turbine a gaz a liaison pied d'aube/disque par serrage
US8651820B2 (en) * 2010-07-14 2014-02-18 General Electric Company Dovetail connection for turbine rotating blade and rotor wheel
US8932023B2 (en) * 2012-01-13 2015-01-13 General Electric Company Rotor wheel for a turbomachine
US9140136B2 (en) 2012-05-31 2015-09-22 United Technologies Corporation Stress-relieved wire seal assembly for gas turbine engines
US20140286782A1 (en) * 2012-08-07 2014-09-25 Solar Turbines Incorporated Turbine blade staking pin
US9828865B2 (en) 2012-09-26 2017-11-28 United Technologies Corporation Turbomachine rotor groove
US20140182293A1 (en) * 2012-12-31 2014-07-03 United Technologies Corporation Compressor Rotor for Gas Turbine Engine With Deep Blade Groove
EP2818638B1 (fr) 2013-06-27 2016-04-27 MTU Aero Engines GmbH Assemblage aubes-disque, procédé et turbomachine
GB2516973B (en) * 2013-08-09 2015-12-23 Rolls Royce Plc Aerofoil Blade
DE102013223607A1 (de) 2013-11-19 2015-05-21 MTU Aero Engines AG Rotor einer Strömungsmaschine
DE102013223583A1 (de) 2013-11-19 2015-05-21 MTU Aero Engines AG Schaufel-Scheiben-Verbund, Verfahren und Strömungsmaschine
GB201502612D0 (en) * 2015-02-17 2015-04-01 Rolls Royce Plc Rotor disc
DE102015203290A1 (de) 2015-02-24 2016-09-29 MTU Aero Engines AG Sicherungselement und Strömungsmaschine
US10767498B2 (en) * 2018-04-03 2020-09-08 Rolls-Royce High Temperature Composites Inc. Turbine disk with pinned platforms

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Publication number Publication date
US20060083621A1 (en) 2006-04-20
US7708529B2 (en) 2010-05-04
DE102004051116A1 (de) 2006-04-27
EP1650405A1 (fr) 2006-04-26
DE502005002145D1 (de) 2008-01-17

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