EP0249092B1 - Plaquette de protection pour aube en titane et procédé de brasage d'une telle plaquette - Google Patents

Plaquette de protection pour aube en titane et procédé de brasage d'une telle plaquette Download PDF

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Publication number
EP0249092B1
EP0249092B1 EP87107673A EP87107673A EP0249092B1 EP 0249092 B1 EP0249092 B1 EP 0249092B1 EP 87107673 A EP87107673 A EP 87107673A EP 87107673 A EP87107673 A EP 87107673A EP 0249092 B1 EP0249092 B1 EP 0249092B1
Authority
EP
European Patent Office
Prior art keywords
blade
tip
temperature
titanium
shield
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 - Lifetime
Application number
EP87107673A
Other languages
German (de)
English (en)
Other versions
EP0249092A1 (fr
Inventor
André Coulon
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.)
Alstom Holdings SA
Original Assignee
GEC Alsthom SA
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 GEC Alsthom SA filed Critical GEC Alsthom SA
Priority to AT87107673T priority Critical patent/ATE50824T1/de
Publication of EP0249092A1 publication Critical patent/EP0249092A1/fr
Application granted granted Critical
Publication of EP0249092B1 publication Critical patent/EP0249092B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C33/00—Making ferrous alloys
    • C22C33/02—Making ferrous alloys by powder metallurgy
    • C22C33/0257—Making ferrous alloys by powder metallurgy characterised by the range of the alloying elements
    • C22C33/0278—Making ferrous alloys by powder metallurgy characterised by the range of the alloying elements with at least one alloying element having a minimum content above 5%
    • C22C33/0292—Making ferrous alloys by powder metallurgy characterised by the range of the alloying elements with at least one alloying element having a minimum content above 5% with more than 5% preformed carbides, nitrides or borides
    • 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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • 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
    • Y10T29/49336—Blade making
    • Y10T29/49337—Composite blade

Definitions

  • the present invention relates to a titanium alloy blade comprising a protective plate. Titanium alloy blades for steam turbines are particularly interesting for the last low pressure stages where the blades must be large. However in these latter stages the water vapor comprises drops of water which strike the movable blades whose peripheral speed is high.
  • Titanium carbide has a coefficient of expansion and a shear modulus identical to titanium.
  • the binder consists of cobalt and chromium which have a high intrinsic resistance to erosion and nickel which improves the ductility of the assembly.
  • Iron constitutes the basic matrix in which the titanium carbides integrate without difficulty.
  • the structure of the wafer is a nickel martensite which has a high resistance to wear due to the presence of chromium and cobalt and a relatively high toughness due to the presence of nickel.
  • the soldering between the blade, the copper strip and the plate is simultaneous and optimal.
  • there is at least partial dissolution of the titanium carbide thus giving the wafer a hardness greater than 50 HRC.
  • This additional step allows almost complete solution of the titanium carbide and simultaneously provides an expansion heat treatment.
  • the steam turbine blade shown in FIG. 1 has a foot 1 and a twisted blade 2 comprising a leading edge 3 and a trailing edge 4. At the top of the blade, we deposited along the edge of attack 3 on the upper surface side a plate 5. This plate extends over about a third of the width of the blade 2. Between the blade and the plate is disposed a copper-based strip 6 (fig. 2 and 3).
  • Composition 2 33% 14% 9% 5% 6% 0.8% Supplement.
  • the wafer is obtained by sintering and mechanical compacting from powders followed by machining.
  • the plate will have a length equal to the part of the blade to be protected (up to 500 mm), an adequate width, will be flat or left, with or without angle or rounded, in order to adapt to the shape of the edge blade attack.
  • the machining must be done with sufficient precision so that the residual clearance between the blade 2 and the plate 5 is everywhere less than 1 / 10th of a mm.
  • the blade 2 is then prepared and the plate 5 is brazed onto the blade 2 by inserting between the two a strip 6 made of copper with a thickness of between 7 and 15/100 th of a mm.
  • the blade 2 provided with the plate 5 is placed in an oven, the latter being held in place by two or three molybdenum clamps.
  • the temperature is raised to a temperature between 900 ° C and 950 ° C. This temperature is maintained for 30 to 75 minutes depending on the thickness of the leading edge of the blade, then the oven is allowed to cool to ambient.
  • This treatment allows in addition to brazing to achieve structural hardening of the wafer 5 by dissolving a large part of the titanium carbide.
  • the plate 5 then has a hardness of 50 to 55 HRC.
  • the latter is subjected to the following additional treatment.
  • the temperature of the oven is raised to 450-500C and it is maintained for 4 to 6 hours, which results in almost complete dissolution of the titanium carbide. In addition, this allows simultaneous relaxation treatment to be carried out.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Organic Chemistry (AREA)
  • Metallurgy (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Ceramic Products (AREA)
  • Polishing Bodies And Polishing Tools (AREA)
  • Superconductors And Manufacturing Methods Therefor (AREA)
  • Coating With Molten Metal (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)

Description

  • La présente invention concerne une aube en alliage de titane comprenant une plaquette de protection. Les aubes en alliage de titane pour turbines à vapeur sont particulièrement intéressantes pour les derniers étages à basse pression où les aubes doivent être grandes. Toutefois dans ces derniers étages la vapeur d'eau comporte des gouttes d'eau qui viennent frapper les aubes mobiles dont la vitesse périphérique est grande.
  • Pour protéger les bords d'attaque des aubes on fixe par soudage ou brasage sur ces bords d'attaque une plaquette comportant les composants suivants:
    • TiC: 28 à 40%
    • Cr + Co : 12 à 26%
    • Mo: 1 à 6%
    • Ni: 3 à 8%
    • Cu: 0, 3 à 1,5%
    • Fe complément
  • Le carbure de titane possède un coefficient de dilatation et un module de cisaillement identiques au titane. Le liant est constitué de cobalt et de chrome qui présentent une grande résistance intrinsèque à l'érosion et de nickel qui améliore la ductilité de l'ensemble.
  • Le fer constitue la matrice de base dans laquelle les carbures de titane s'intégrent sans difficulté.
  • La structure de la plaquette est une martensite au nickel qui présente une grande résistance à l'usure du fait de la présence de chrome et de cobalt et une ténacité relativement élevée du fait de la présence de nickel.
  • L'invention concerne également un procédé de brasage de la plaquette caractérisé en ce qu'il comporte les étapes suivantes:
    • - Pose de la plaquette sur l'aube avec interposition entre les deux d'un feuillard à base de cuivre d'une épaisseur comprise entre 7 et 15/100ème de mm.
    • - Montée à une température comprise entre 900° et 950°C de l'aube avec sa plaquette dans un four sous vide ou à atmosphère inerte et maintien de cette température pendant un temps compris entre 30 et 75 minutes.
    • - Refroidissement jusqu'à la température ambiante.
  • Grâce à ce procédé, le brasage entre l'aube, le feuillard à base de cuivre et la plaquette est simultané et optimal. De plus il y a mise en solution au moins partielle du carbure de titane conférant ainsi à la plaquette une dureté supérieure à 50 HRC.
  • Il est connu du document GB-A 1 479 855 de braser une couche protection en carbure de titane sur une aube de turbine en titane en utilisant de l'argent mais la résistance à la traction d'une telle brasure n'est pas optimale.
  • Si on désire une plaquette de dureté supérieure à 60 HRC on remonte, après le refroidissement à l'ambiante, à la température jusqu'à 450°C-500°C et on la maintient pendant 4 à 6 heures avant de la refaire redescendre jusqu'à l'ambiante.
  • Cette étape supplémentaire permet la mise en solution quasi-totale du carbure de titane et simultanément assure un traitement thermique de détente.
  • L'invention va maintenant être décrite plus en détail en se référant à un mode de réalisation particulier cité à titre d'exemple non limitatif et représenté par les dessins annexés.
    • La figure 1 représente une plaquette selon l'invention fixée sur une aube en carbure de titane.
    • La figure 2 représente une vue de dessus de l'aube de la figure 1.
    • La figure 3 représente une coupe de l'aube de la figure 1.
  • L'aube de turbine à vapeur représentée à la figure 1 comporte un pied 1 et une pale vrillée 2 comprenant un bord d'attaque 3 et un bord de fuite 4. A la partie haute de l'aube on a déposé le long du bord d'attaque 3 côté extrados une plaquette 5. Cette plaquette s'étend sur environ un tiers de la largeur de la pale 2. Entre la pale et la plaquette est disposé un feuillard à base de cuivre 6 (fig. 2 et 3).
  • L'aube est en alliage de titane et la plaquette 5 a la composition suivante:
    • TiC = 28 à 40% Mo: 1 à 6%
    • Cr+Co=12à26% Ni=3à 8%
    • Fe = complément Cu = 0,3 à 1,5%
  • Deux compositions particulières ont donné de bons résultats.
    • TiC Cr Co Mo Ni Cu Fe
  • Composition 1 32% 20% 0% 2% 3% 1 % Complément
  • Composition 2 33% 14% 9% 5% 6% 0,8%Complément.
  • On obtient la plaquette par frittage et compactage mécanique à partir de poudres suivis d'un usinage. La plaquette aura une longueur égale à la partie de la pale à protéger (jusqu'à 500 mm), une largeur adéquate, sera de forme plane ou gauche, avec ou sans angle ou arrondi, en vue de son adaptation à la forme du bord d'attaque de la pale.
  • L'usinage doit être fait avec suffisamment de précision pour que le jeu résiduel entre la pale 2 et la plaquette 5 soit partout inférieur à 1/10ème de mm.
  • On prépare ensuite la pale 2 et on brase la plaquette 5 sur la pale 2 en intercalant entre les deux un feuillard 6 à base de cuivre d'une épaisseur comprise entre 7 et 15/100 ème de mm.
  • Pour réaliser l'opération de brasage on met la pale 2 munie de la plaquette 5 dans un four, celle-ci étant maintenue en place par deux ou trois pinces en molybdène.
  • On monte la température jusqu'à une température comprise entre 900°C et 950°C. Cette température est maintenue pendant 30 à 75 minutes suivant l'épaisseur du bord d'attaque de l'aube, puis on laisse refroidir le four jusqu'à l'ambiante.
  • Ce traitement permet en plus du brasage de réaliser un durcissement structural de la plaquette 5 par mise en solution d'une partie importante du carbure de titane. La plaquette 5 a alors une dureté de 50 à 55 HRC.
  • Pour augmenter encore la dureté de la plaquette 5 on fait subir à celle-ci le traitement additional suivant.
  • On remonte la température du four jusqu'à 450-500C et on la maintient pendant 4 à 6 heures ce qui entraîne une mise en solution quasi-totale du carbure de titane. De plus cela permet de réaliser simultanément un traitement de détente.

Claims (2)

1. Aube (1) de turbine en titane comprenant une plaquette de protection (5), caractérisée en ce que la plaquette comporte les composants suivants :
TiC 28 à 40%
Cr + Co 12 à 26%
Mo 1 à 6%
Ni 3 à 8%
Cu 0,3 à 1,5%
Fe complément.
2. Procédé de fabrication de l'aube (1) selon la revendication 1, caractérisé en ce qu'il comporte les étapes suivantes :
- Pose d'une plaquette (5) avec les composants suivants:
TiC 28 à 40%
Cr + Co 12 à 26%
Mo 1 à 6%
Ni 3 à8%
Cu 0,3 à 1,5%
Fe complément

sur l'aube (1) avec interposition entre les deux d'un feuillard (6) à base de cuivre d'une épaisseur comprise entre 7 et 15/1 OOème de mm.
- Montée à une température comprise entre 900°C et 950°C de l'aube (1) avec sa plaquette (5) dans un four sous vide ou à atmosphère inerte et maintien de cette température pendant un temps compris entre 30 et 75 minutes.
- Refroidissement jusqu'à l'ambiante.
EP87107673A 1986-05-28 1987-05-26 Plaquette de protection pour aube en titane et procédé de brasage d'une telle plaquette Expired - Lifetime EP0249092B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT87107673T ATE50824T1 (de) 1986-05-28 1987-05-26 Schutzschild fuer eine turbinenschaufel aus titan und loetverfahren fuer ein solches schutzschild.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8607661A FR2599425B1 (fr) 1986-05-28 1986-05-28 Plaquette de protection pour aube en titane et procede de brasage d'une telle plaquette.
FR8607661 1986-05-28

Publications (2)

Publication Number Publication Date
EP0249092A1 EP0249092A1 (fr) 1987-12-16
EP0249092B1 true EP0249092B1 (fr) 1990-03-07

Family

ID=9335746

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87107673A Expired - Lifetime EP0249092B1 (fr) 1986-05-28 1987-05-26 Plaquette de protection pour aube en titane et procédé de brasage d'une telle plaquette

Country Status (11)

Country Link
US (1) US4795313A (fr)
EP (1) EP0249092B1 (fr)
JP (1) JPS62297442A (fr)
CN (1) CN1009472B (fr)
AT (1) ATE50824T1 (fr)
CS (3) CS276857B6 (fr)
DE (1) DE3761833D1 (fr)
ES (1) ES2013272B3 (fr)
FR (1) FR2599425B1 (fr)
GR (1) GR3000501T3 (fr)
ZA (1) ZA873837B (fr)

Cited By (2)

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US5366345A (en) * 1990-12-19 1994-11-22 Asea Brown Boveri Ltd. Turbine blade of a basic titanium alloy and method of manufacturing it
US5448828A (en) * 1993-04-02 1995-09-12 Thyssen Industrie Ag Process for preparing wear-resistant edges on turbine blades

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US5165859A (en) * 1992-06-26 1992-11-24 Hudson Products Corporation Leading edge protection for fan blade
US5351395A (en) * 1992-12-30 1994-10-04 General Electric Company Process for producing turbine bucket with water droplet erosion protection
US5449273A (en) * 1994-03-21 1995-09-12 United Technologies Corporation Composite airfoil leading edge protection
CN1041642C (zh) * 1994-06-17 1999-01-13 株式会社日立制作所 高韧性13Cr5Ni系不锈钢及其用途
GB2293631B (en) * 1994-09-30 1998-09-09 Gen Electric Composite fan blade trailing edge reinforcement
US5531570A (en) * 1995-03-06 1996-07-02 General Electric Company Distortion control for laser shock peened gas turbine engine compressor blade edges
IL117347A (en) * 1995-03-06 1999-10-28 Gen Electric Laser shock peened gas turbine engine compressor airfoil edges
FR2742689B1 (fr) * 1995-12-22 1998-02-06 Gec Alsthom Electromec Procede pour fabriquer une aube en titane alpha beta comprenant un insert de titane beta metastable, et aube realisee par un tel procede
DE10326541A1 (de) * 2003-06-12 2005-01-05 Mtu Aero Engines Gmbh Verfahren zur Schaufelspitzenpanzerung der Laufschaufeln eines Gasturbinentriebwerkes und Vorrichtung zur Durchführung des Verfahrens
US7222422B2 (en) * 2004-02-16 2007-05-29 General Electric Company Method for refurbishing surfaces subjected to high compression contact
US7841834B1 (en) * 2006-01-27 2010-11-30 Florida Turbine Technologies, Inc. Method and leading edge replacement insert for repairing a turbine engine blade
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US7780419B1 (en) 2007-03-06 2010-08-24 Florida Turbine Technologies, Inc. Replaceable leading edge insert for an IBR
US20090068446A1 (en) * 2007-04-30 2009-03-12 United Technologies Corporation Layered structures with integral brazing materials
DE102008047043A1 (de) * 2008-09-13 2010-03-18 Mtu Aero Engines Gmbh Ersatzteil für eine Gasturbinen-Schaufel einer Gasturbine, Gasturbinen-Schaufel sowie ein Verfahren zur Reparatur einer Gasturbinen-Schaufel
DE102009047798A1 (de) * 2009-09-30 2011-04-14 Siemens Aktiengesellschaft Turbinenschaufel, insbesondere Endstufenlaufschaufel für eine Dampfturbine
CN102107306B (zh) * 2009-12-23 2013-06-05 沈阳黎明航空发动机(集团)有限责任公司 一种涡轮导向叶片缺陷的修补方法
US8376712B2 (en) * 2010-01-26 2013-02-19 United Technologies Corporation Fan airfoil sheath
US9151173B2 (en) 2011-12-15 2015-10-06 General Electric Company Use of multi-faceted impingement openings for increasing heat transfer characteristics on gas turbine components
CN103603695B (zh) * 2011-12-31 2016-06-22 无锡透平叶片有限公司 一种叶片合金槽及其加工方法
EP2971522B1 (fr) * 2013-03-14 2018-07-18 Rolls-Royce Corporation Profil aérodynamique avec renfort de bord d'attaque
US10428657B2 (en) 2013-06-21 2019-10-01 Pratt & Whitney Canada Corp. Method for repairing a blade
US9682449B2 (en) * 2014-05-09 2017-06-20 United Technologies Corporation Repair material preform
EP3020925A1 (fr) 2014-10-29 2016-05-18 Alstom Technology Ltd Pale de rotor avec protection des bords
FR3041684B1 (fr) * 2015-09-28 2021-12-10 Snecma Aube comprenant un bouclier de bord d'attaque et procede de fabrication de l'aube
GB2549113A (en) * 2016-04-05 2017-10-11 Rolls Royce Plc Composite bodies and their manufacture
JP7245215B2 (ja) * 2020-11-25 2023-03-23 三菱重工業株式会社 蒸気タービン動翼
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5366345A (en) * 1990-12-19 1994-11-22 Asea Brown Boveri Ltd. Turbine blade of a basic titanium alloy and method of manufacturing it
US5448828A (en) * 1993-04-02 1995-09-12 Thyssen Industrie Ag Process for preparing wear-resistant edges on turbine blades

Also Published As

Publication number Publication date
ZA873837B (en) 1987-11-24
ATE50824T1 (de) 1990-03-15
CS276857B6 (en) 1992-08-12
FR2599425A1 (fr) 1987-12-04
FR2599425B1 (fr) 1988-08-05
CS276725B6 (en) 1992-08-12
EP0249092A1 (fr) 1987-12-16
ES2013272B3 (es) 1990-05-01
CN1009472B (zh) 1990-09-05
CS382790A3 (en) 1992-01-15
CN87104497A (zh) 1987-12-16
CS389287A3 (en) 1992-03-18
GR3000501T3 (en) 1991-07-31
JPS62297442A (ja) 1987-12-24
US4795313A (en) 1989-01-03
DE3761833D1 (de) 1990-04-12

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