EP2378065B1 - Procédé de réparation d'un agencement de rotor d'une turbomachine. - Google Patents

Procédé de réparation d'un agencement de rotor d'une turbomachine. Download PDF

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Publication number
EP2378065B1
EP2378065B1 EP11161686.8A EP11161686A EP2378065B1 EP 2378065 B1 EP2378065 B1 EP 2378065B1 EP 11161686 A EP11161686 A EP 11161686A EP 2378065 B1 EP2378065 B1 EP 2378065B1
Authority
EP
European Patent Office
Prior art keywords
groove
rotor
ring
notch
recess
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
EP11161686.8A
Other languages
German (de)
English (en)
Other versions
EP2378065A3 (fr
EP2378065A2 (fr
Inventor
Christian Heinzelmaier
Michael Raiche
Knut Werner
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 AG
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Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP2378065A2 publication Critical patent/EP2378065A2/fr
Publication of EP2378065A3 publication Critical patent/EP2378065A3/fr
Application granted granted Critical
Publication of EP2378065B1 publication Critical patent/EP2378065B1/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
    • F01D5/005—Repairing methods or devices
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • 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
    • Y10T29/49318—Repairing or disassembling

Definitions

  • the present invention relates to a method for repairing a rotor assembly of a turbomachine, a ring member for a rotor assembly of a turbomachine and a rotor assembly for a turbomachine.
  • the drawing shows an internally known rotor assembly 2 for a high-pressure compressor.
  • the rotor assembly 2 has, as Fig. 5 to take a rotor 4 on.
  • the rotor assembly 2 further comprises blades 6, 8.
  • Fig. 5 shows by way of example only one blade 6, 8 of a row of blades, each of which is arranged along the circumference of the rotor 4.
  • the blades 6 are respectively held in axial grooves 14 in the rotor 4 in the radial direction in a form-fitting manner, for example by means of a dovetail or pine cone connection.
  • the terms "axial”, “radial” and “circumferentially” refer to a central axis 16 of the rotor 4.
  • retaining plates 18 are arranged in the form of ring sections in a circumferentially extending groove 20 in the rotor 4 and in a circumferentially extending groove 22 of each blade 6, thus ensuring positive engagement in the axial direction between each blade 6 and the rotor 4 Fig. 5
  • a plurality of holding plates 18 arranged along the circumference in the grooves 20 and 22 is shown.
  • a plurality of closing plates are usually provided, which are each arranged in a gap between two retaining plates 18.
  • the locking plates differ essentially from the retaining plates 18 in that that the strike plates are not inserted as the retaining plates 18 along the circumference in the grooves 20, 22, but by forming them in the grooves 20 and 22 are driven.
  • the rotor 4 In the second region 12 of the rotor 4 is formed with circumferentially extending grooves 24 which are in the radial direction with the blades 8 positively, for example by means of a dovetail or Pannenzapfenitati in engagement.
  • the rotor 4 has longitudinally extending grooves 26 in front of and behind each row of airfoils 8 in its circumferential direction.
  • the grooves 26 are also in Fig. 6 shown, which is a sectional view A from Fig. 5 shows.
  • a damper ring 28 (English: damper ring) is arranged, such as Fig. 6 refer to.
  • Fig. 6 only illustrates two of the grooves 26 with the damping rings 28 for better understanding.
  • Fig. 7 shows the damping ring 28 in an enlarged plan view B from Fig. 6 .
  • the damping ring 28 is formed for the purpose of its assembly on the rotor 4 over a part of its circumference of time, thereby forming the two ends 30 and 32, which are each rounded.
  • the damping rings 28 move during the rotation of the rotor assembly 2 relative to the rotor 4 and the blades 8. The resulting friction damps unwanted vibrations of the rotor assembly. 2
  • Fig. 8 illustrates an enlarged partial view C from Fig. 6 ,
  • the groove 26 is formed by two opposing collars 34 and 36 and by a bottom 38.
  • the original state of the groove 26 is in Fig. 8 shown in dashed lines.
  • the above-described relative movement between the damping ring 28 and the rotor 4 now leads to the fact that in particular the ends 30 and 32 of the damping ring 28 dig into the collars 34, 36 of the groove 26.
  • the rounded area is in Fig.
  • the damping ring 28 is inserted back into the groove 26 and the rotor assembly 2 is put back into operation. During operation, the ends 30 and 32 of the damping ring 28 are caught entangled in the rounded portion 42, so that it comes within a short time to re-serration or there is a risk that one end of the damping ring 28 in the axial direction of the blades 8 passes by. If there is enough material left for further rounding, the rotor will be repaired again. Otherwise, the rotor may need to be completely replaced. But especially in the latter case, this leads to very high costs, since the rotor body is made of titanium in a very complex process.
  • a method of repairing a rotor assembly of a turbomachine having a rotor with a circumferentially extending groove for receiving a ring portion is provided with the following steps.
  • a notch in the groove is rounded.
  • a recess is incorporated into the groove.
  • the ring portion is inserted into the groove, wherein at least one engaging element formed on the ring portion engages in the recess for forming an anti-rotation in the circumferential direction.
  • the idea underlying the present invention is to prevent a relative movement in the circumferential direction between the ring portion and the groove.
  • the ring portion is formed, for example, as a damping ring
  • this has the advantage that in particular the ends of the damping ring by means of the rotation no longer in the rounded area or a random range can be incorporated, which is extended as a result, the life of the rotor.
  • the ring portion is formed, for example, as a retaining plate or locking plate
  • the advantage of the invention especially comes into play especially when already a rounded portion is present in the groove in which the ends of the damping ring or the corners and edges of the retaining plates or locking plates can dig, so it is according to the invention also intended to provide the rotor assembly from the beginning with the rotation between the ring portion and the rotor and not form them first in the repair process.
  • a "ring section" is to be understood, in particular, as meaning a damping ring, a holding plate for a blade or a striking plate, in each case for a rotor arrangement of a turbomachine.
  • a "notch” is understood as meaning, in particular, a defect in the material of the rotor, which, if it is not repaired, can lead to failure of the rotor.
  • a "recess" is preferably to be understood as meaning a pocket or a breakthrough.
  • the at least one engagement element is mounted prior to insertion of the ring portion in the groove on this, in particular welded or soldered.
  • the existing ring section is not replaced by a new ring section to which the at least one engagement element is attached. Rather, the existing ring portion is first removed from the groove, thereafter the notch rounded, incorporated the recess and then the provided with the one engagement member ring portion are re-inserted into the groove.
  • one, two or four engagement elements can be provided.
  • the at least one engagement element is formed by means of reshaping, in particular bending, of a partial region of the annular section.
  • the at least one engagement element is formed by the ring portion itself, whereby additional components can be saved.
  • the recess is incorporated into a collar of the groove opposite the notch such that a tool for rounding the notch is substantially rectilinearly movable through the recess to the notch.
  • the recess has a double function: On the one hand, it provides good accessibility for a tool, for example for a milling head, to the notch in order to round it. On the other hand, it serves as a counterpart for the engagement element and thereby ensures the described rotation.
  • the at least one engagement element is designed as a bump, which extends in the axial direction of the ring portion thereof.
  • a hump is well suited to having a corresponding recess in the waistband the groove cooperate.
  • the ring portion is formed with two first, spaced apart engagement elements, which are adapted to abut after insertion of the ring portion in the groove against opposite ends of the recess.
  • the aim is to provide an anti-rotation in both circumferential directions, ie clockwise and counterclockwise. Since the area to be rounded in some cases extends over a comparatively large circumferential length and the recess is therefore correspondingly long, it would be appropriate to provide a correspondingly long engagement element as well.
  • the ring portion is formed as a damping ring, retaining plate for at least one blade of the rotor assembly or striking plate of the rotor assembly.
  • Fig. 1 is based on a perspective view D Fig. 8 , It is therefore with regard to the following explanations at least partially to the principalsgen in connection with the Fig. 5 to 8 directed.
  • a contour of the state of the rotor 4 with the notch 40, as in Fig. 8 is shown in Fig. 1 shown in dashed lines.
  • the damping ring 28 is already out of the groove 26 in Fig. 1 taken from. This condition is assumed for the following description.
  • the groove 26 is usually cleaned and inspected for notches 40. Will a notch 40, as in Fig. 1 shown, found, so in a next step, a continuous recess 44, for example by means of a milling head 46 in the collar 34 opposite the collar 36, which has the notch 40, milled.
  • the extent of the recess 44 in the circumferential direction preferably corresponds at least to the extent of the region 42 to be rounded in the circumferential direction.
  • the milling head 46 or another tool, such as a grinding head in the in Fig. 1 shown arrow direction 48 through the formed recess 44 through substantially at right angles to the collar 36 driven to round the notch 40 and thus to form the rounded portion 42.
  • two engagement elements 48 in the form of bumps are welded or soldered to the damping ring 28 after its removal from the groove 26, as in FIG Fig. 2 is shown.
  • the bumps 48 extend from a side surface 50 of the damping ring 28, preferably in the axial direction in their welded state. Further, the bumps 48 on different sides of a disconnection point, not shown, for opening the damping ring 28, as above in connection with Fig. 7 described, arranged.
  • the damping ring 28 forms a ring element 54 together with the engagement elements 48.
  • the engagement elements can each be produced by bending a portion 49 of the damping ring 28, for example in the axial direction, as in FIG Fig. 2 shown.
  • the bent portion 49 is in Fig. 2 dashed and shown only at one point of the damping ring 28.
  • it is just as possible to produce several bent portions for example, according to the arrangement of the bumps 48 in Fig. 2 ,
  • the damping ring 28 may be formed with two further engagement elements 60, for example in the form of bumps or bent-over portions, as in FIG Fig. 4 shown.
  • the engagement elements 60 engage in a recess 44 correspondingly formed and substantially opposite recess (not shown) in the collar 34 a.
  • the engagement elements 48 or 49 and 60 are arranged according to this embodiment mirror-symmetrically with respect to two the Ftingstoffddling 61 intersecting and perpendicular to each other arranged axes 62, 64 on the damping ring 28 and have approximately the same masses. As a result, an imbalance due to otherwise unevenly distributed masses can be advantageously avoided.
  • the ring member 54 is again inserted into the rotor body 4, that is, the damping ring 28 is inserted into the groove 26, in which case the bumps 48 (or the bent portions 49) engage in the recess 44 and against opposite ends 56 of Recess 44 abut.
  • the bumps 48 thereby prevent the damping ring 28 from rotating in the counterclockwise direction in the circumferential direction 58.
  • the rotor 2 can now be put into operation again.

Landscapes

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

Claims (4)

  1. Procédé de réparation d'un dispositif de rotor (2) d'une turbomachine, lequel comprend un rotor (4) avec une rainure (26) s'étendant dans la direction périphérique (58) de celui-ci pour la réception d'un arc d'anneau (18 ; 28), une entaille (40) étant prévue dans la rainure (26) comprenant les étapes suivantes :
    - arrondissement de l'entaille (40) dans la rainure (26) ;
    - usinage d'un évidement (44) dans la rainure (26) ; et
    - mise en place de l'arc d'anneau (18 ; 28) dans la rainure (26), au moins un élément d'engrènement (48 ; 49) formé sur l'arc d'anneau (18 ; 28) s'engageant dans l'évidement (44) pour assurer un blocage contre la rotation dans la direction périphérique (58).
  2. Procédé selon la revendication 1,
    caractérisé en ce que
    ledit au moins un élément d'engrènement (48) est appliqué, en particulier par soudage ou par brasage, dans la rainure (26) sur l'arc d'anneau (18 ; 28) avant la mise en place de celui-ci.
  3. Procédé selon la revendication 1,
    caractérisé en ce que
    ledit au moins un élément d'engrènement (49) est réalisé par déformation, en particulier par cintrage d'une zone partielle de l'arc d'anneau (18 ; 28).
  4. Procédé selon au moins une des revendications précédentes,
    caractérisé en ce que
    l'évidement (44) est ménagé en face de l'entaille (40) dans un épaulement (36) de la rainure (26), de sorte qu'un outil (46) pour arrondir l'entaille (40) peut être déplacé sensiblement en ligne droite vers l'entaille (40) au travers de l'évidement (44).
EP11161686.8A 2010-04-19 2011-04-08 Procédé de réparation d'un agencement de rotor d'une turbomachine. Not-in-force EP2378065B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE201010015404 DE102010015404B4 (de) 2010-04-19 2010-04-19 Verfahren zur Reparatur einer Rotoranordnung einer Turbomaschine, Ringelement für eine Rotoranordnung einer Turbomaschine sowie Rotoranordnung für eine Turbomaschine

Publications (3)

Publication Number Publication Date
EP2378065A2 EP2378065A2 (fr) 2011-10-19
EP2378065A3 EP2378065A3 (fr) 2015-02-11
EP2378065B1 true EP2378065B1 (fr) 2016-03-23

Family

ID=44533437

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11161686.8A Not-in-force EP2378065B1 (fr) 2010-04-19 2011-04-08 Procédé de réparation d'un agencement de rotor d'une turbomachine.

Country Status (4)

Country Link
US (1) US8899919B2 (fr)
EP (1) EP2378065B1 (fr)
CA (1) CA2737676A1 (fr)
DE (1) DE102010015404B4 (fr)

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EP2604792B1 (fr) * 2011-12-15 2015-11-04 MTU Aero Engines GmbH Procédé de réparation d'un composant d'une turbomachine et composant réparé associé
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
FR3021064B1 (fr) * 2014-05-16 2020-05-29 Safran Aircraft Engines Disque et procede d'equilibrage
FR3027071B1 (fr) * 2014-10-13 2019-08-23 Safran Aircraft Engines Procede d'intervention sur un rotor et clinquant associe
US11098729B2 (en) 2016-08-04 2021-08-24 General Electric Company Gas turbine wheel assembly, method of modifying a compressor wheel, and method of mounting a blade to a gas turbine wheel
CN115213627B (zh) * 2022-07-20 2023-05-05 华能国际电力股份有限公司 一种用于修复菌型叶根轮盘损伤的装置及装配方法
CN115194402A (zh) * 2022-07-20 2022-10-18 华能国际电力股份有限公司 一种轮盘部件修复方法
CN114986078B (zh) * 2022-07-20 2023-05-05 华能国际电力股份有限公司 一种用于修复t型叶根轮盘损伤的装置及装配方法
CN115106715B (zh) * 2022-07-20 2023-05-05 华能国际电力股份有限公司 一种用于修复叉型叶根轮盘损伤的装置及装配方法
CN115178962A (zh) * 2022-07-20 2022-10-14 华能国际电力股份有限公司 一种用于修复枞树型叶根轮盘损伤的装置及装配方法

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Also Published As

Publication number Publication date
DE102010015404A1 (de) 2011-10-20
DE102010015404B4 (de) 2012-02-16
CA2737676A1 (fr) 2011-10-19
EP2378065A3 (fr) 2015-02-11
EP2378065A2 (fr) 2011-10-19
US20110255980A1 (en) 2011-10-20
US8899919B2 (en) 2014-12-02

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