EP0249092A1 - Schutzschild für eine Turbinenschaufel aus Titan und Lötverfahren für ein solches Schutzschild - Google Patents

Schutzschild für eine Turbinenschaufel aus Titan und Lötverfahren für ein solches Schutzschild Download PDF

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Publication number
EP0249092A1
EP0249092A1 EP87107673A EP87107673A EP0249092A1 EP 0249092 A1 EP0249092 A1 EP 0249092A1 EP 87107673 A EP87107673 A EP 87107673A EP 87107673 A EP87107673 A EP 87107673A EP 0249092 A1 EP0249092 A1 EP 0249092A1
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EP
European Patent Office
Prior art keywords
blade
plate
temperature
titanium
wafer
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
EP87107673A
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English (en)
French (fr)
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EP0249092B1 (de
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
Alstom SA
GEC Alsthom SA
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Filing date
Publication date
Application filed by Alstom SA, GEC Alsthom SA filed Critical Alstom SA
Priority to AT87107673T priority Critical patent/ATE50824T1/de
Publication of EP0249092A1 publication Critical patent/EP0249092A1/de
Application granted granted Critical
Publication of EP0249092B1 publication Critical patent/EP0249092B1/de
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 protective plate for a turbine blade made of titanium alloy.
  • 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 includes drops of water which strike the movable blades, the peripheral speed of which is high.
  • a plate comprising the following components is fixed by welding or soldering to these leading edges: TiC: 28 to 40% Cr + Co: 12 to 26% MB: 1 to 6% Ni: 3 to 8% Cu: 0.3 to 1.5% Fe complement.
  • 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 invention also relates to a method for brazing the wafer, characterized in that it comprises the following steps: - Installation of the plate on the blade with interposition between the two of a copper-based strip with a thickness of between 7 and 15 / 100th of a mm. - Rise to a temperature between 900 ° and 950 ° C of dawn with its plate in a vacuum oven or in an inert atmosphere and maintenance of this temperature for a time between 30 and 75 minutes. - Cooling down to room temperature.
  • 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.
  • a wafer with a hardness greater than 60 HRC is desired, after cooling to ambient temperature, it rises to the temperature up to 450 ° C - 500 ° C and is maintained for 4 to 6 hours before being brought back down to 'to the ambient.
  • This additional step allows almost complete solution of the titanium carbide and simultaneously provides an expansion heat treatment.
  • Figure 1 shows a plate according to the invention fixed on a titanium carbide blade.
  • FIG. 2 represents a top view of the blade of FIG. 1.
  • FIG. 3 represents a section of the dawn of FIG. 1.
  • 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).
  • the blade is made of titanium alloy and the plate 5 has the following composition:
  • 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 wafer 5 then has a hardness of 50 to 55 HRC.
  • the latter is subjected to the following additional treatment.
  • the temperature of the furnace is raised to 450-500 ° C. 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)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Superconductors And Manufacturing Methods Therefor (AREA)
  • Coating With Molten Metal (AREA)
  • Polishing Bodies And Polishing Tools (AREA)
EP87107673A 1986-05-28 1987-05-26 Schutzschild für eine Turbinenschaufel aus Titan und Lötverfahren für ein solches Schutzschild Expired - Lifetime EP0249092B1 (de)

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

Publications (2)

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

Family

ID=9335746

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87107673A Expired - Lifetime EP0249092B1 (de) 1986-05-28 1987-05-26 Schutzschild für eine Turbinenschaufel aus Titan und Lötverfahren für ein solches Schutzschild

Country Status (11)

Country Link
US (1) US4795313A (de)
EP (1) EP0249092B1 (de)
JP (1) JPS62297442A (de)
CN (1) CN1009472B (de)
AT (1) ATE50824T1 (de)
CS (3) CS276725B6 (de)
DE (1) DE3761833D1 (de)
ES (1) ES2013272B3 (de)
FR (1) FR2599425B1 (de)
GR (1) GR3000501T3 (de)
ZA (1) ZA873837B (de)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4310896C1 (de) * 1993-04-02 1994-03-24 Thyssen Industrie Verfahren zum Herstellen von verschleißfesten Kanten an Turbinenschaufeln
EP0605152A1 (de) * 1992-12-30 1994-07-06 General Electric Company Verfahren zur Herstellung einer Turbinenschaufel mit Schutz gegen Wasserströpfchenerosion und entsprechendes Produkt
EP0780187A1 (de) * 1995-12-22 1997-06-25 Gec Alsthom Electromecanique Sa Herstellungsverfahren einer Schaufel aus Alpha-Beta Titan mit einem Einssatz aus metastablen Beta Titan und durch solch ein Verfahren hergestellte Schaufel
WO2011039075A1 (de) * 2009-09-30 2011-04-07 Siemens Aktiengesellschaft Endstufenlaufschaufel einer dampfturbine
CN103603695A (zh) * 2011-12-31 2014-02-26 无锡透平叶片有限公司 一种叶片合金槽及其加工方法
FR3123380A1 (fr) * 2021-05-28 2022-12-02 Safran Aircraft Engines Bouclier de bord d'attaque amélioré

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0491075B1 (de) * 1990-12-19 1995-07-05 Asea Brown Boveri Ag Verfahren zur Herstellung einer Turbinenschaufel aus einer Titan-Basislegierung
EP0578518B1 (de) * 1992-06-05 1998-09-30 Gec Alsthom Electromecanique Sa Verfahren zur Herstellung eines Einsatzes auf einem zu beschichtenden Formkörper aus Stahl oder aus Titanlegierung
US5165859A (en) * 1992-06-26 1992-11-24 Hudson Products Corporation Leading edge protection for fan blade
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
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
US20080181808A1 (en) 2007-01-31 2008-07-31 Samuel Vinod Thamboo Methods and articles relating to high strength erosion resistant titanium alloy
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
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
WO2014158245A1 (en) * 2013-03-14 2014-10-02 Hodgson Benedict N Airfoil with leading edge reinforcement
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 (de) * 2014-10-29 2016-05-18 Alstom Technology Ltd Rotorschaufel mit kantenschutz
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

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB692867A (en) * 1950-03-24 1953-06-17 Hard Metal Tools Ltd Improvements relating to turbine blades
FR1146511A (fr) * 1951-12-07 1957-11-13 Sintercast Corp America Aube de turbine
DE2004724A1 (de) * 1969-02-07 1970-09-03 General Electric Company, Sehenectady, N.Y. (V,St.A.) Turbinenschaufel
GB1479855A (en) * 1976-04-23 1977-07-13 Statni Vyzkumny Ustav Material Protective coating for titanium alloy blades for turbine and turbo-compressor rotors
FR2482627A1 (fr) * 1980-05-16 1981-11-20 Metallurg Ind Inc Alliage metallique resistant a l'erosion

Family Cites Families (13)

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US2661286A (en) * 1950-01-13 1953-12-01 Mallory Sharon Titanium Corp Titanium base alloys containing silicon
US2664355A (en) * 1950-10-06 1953-12-29 Battelle Development Corp Ti-mn-fe alloys
US2714245A (en) * 1951-12-07 1955-08-02 Sintercast Corp America Sintered titanium carbide alloy turbine blade
BE560921A (de) * 1956-09-21
US2903785A (en) * 1957-02-11 1959-09-15 Gen Motors Corp Method of hot working titanium
GB1096294A (en) * 1964-06-12 1967-12-29 English Electric Co Ltd Turbine blades
US4010530A (en) * 1975-07-24 1977-03-08 United Technologies Corporation Method for making blade protective sheaths
JPS52103306A (en) * 1976-02-27 1977-08-30 Mitsubishi Metal Corp Lightweight hard alloy for parts of hot rolling equipment
JPS5560605A (en) * 1978-10-27 1980-05-07 Toshiba Corp Method of manufacturing turbine blade having anti- corrosive plate
JPS5564104A (en) * 1978-11-10 1980-05-14 Hitachi Ltd Rotor blade of turbine
JPS5798651A (en) * 1980-12-11 1982-06-18 Seiko Epson Corp Hard external parts for watch
JPS59126752A (ja) * 1983-01-07 1984-07-21 Taiho Kogyo Co Ltd 鉄系摺動材料およびその製法
JPS60228657A (ja) * 1984-04-26 1985-11-13 Sumitomo Precision Prod Co Ltd アルミニウム合金構造物の製造方法

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB692867A (en) * 1950-03-24 1953-06-17 Hard Metal Tools Ltd Improvements relating to turbine blades
FR1146511A (fr) * 1951-12-07 1957-11-13 Sintercast Corp America Aube de turbine
DE2004724A1 (de) * 1969-02-07 1970-09-03 General Electric Company, Sehenectady, N.Y. (V,St.A.) Turbinenschaufel
GB1479855A (en) * 1976-04-23 1977-07-13 Statni Vyzkumny Ustav Material Protective coating for titanium alloy blades for turbine and turbo-compressor rotors
FR2482627A1 (fr) * 1980-05-16 1981-11-20 Metallurg Ind Inc Alliage metallique resistant a l'erosion

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0605152A1 (de) * 1992-12-30 1994-07-06 General Electric Company Verfahren zur Herstellung einer Turbinenschaufel mit Schutz gegen Wasserströpfchenerosion und entsprechendes Produkt
DE4310896C1 (de) * 1993-04-02 1994-03-24 Thyssen Industrie Verfahren zum Herstellen von verschleißfesten Kanten an Turbinenschaufeln
EP0780187A1 (de) * 1995-12-22 1997-06-25 Gec Alsthom Electromecanique Sa Herstellungsverfahren einer Schaufel aus Alpha-Beta Titan mit einem Einssatz aus metastablen Beta Titan und durch solch ein Verfahren hergestellte Schaufel
FR2742689A1 (fr) * 1995-12-22 1997-06-27 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
WO2011039075A1 (de) * 2009-09-30 2011-04-07 Siemens Aktiengesellschaft Endstufenlaufschaufel einer dampfturbine
CN103603695A (zh) * 2011-12-31 2014-02-26 无锡透平叶片有限公司 一种叶片合金槽及其加工方法
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
FR3123380A1 (fr) * 2021-05-28 2022-12-02 Safran Aircraft Engines Bouclier de bord d'attaque amélioré

Also Published As

Publication number Publication date
EP0249092B1 (de) 1990-03-07
CS276725B6 (en) 1992-08-12
FR2599425B1 (fr) 1988-08-05
US4795313A (en) 1989-01-03
DE3761833D1 (de) 1990-04-12
ATE50824T1 (de) 1990-03-15
ZA873837B (en) 1987-11-24
FR2599425A1 (fr) 1987-12-04
CS389287A3 (en) 1992-03-18
JPS62297442A (ja) 1987-12-24
CN1009472B (zh) 1990-09-05
CS276857B6 (en) 1992-08-12
CN87104497A (zh) 1987-12-16
CS382790A3 (en) 1992-01-15
ES2013272B3 (es) 1990-05-01
GR3000501T3 (en) 1991-07-31

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