EP0249092B1 - 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
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
English (en)
French (fr)
Other versions
EP0249092A1 (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
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/de
Application granted granted Critical
Publication of EP0249092B1 publication Critical patent/EP0249092B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Organic Chemistry (AREA)
  • Metallurgy (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)

Claims (2)

1. Turbinenschaufel (1) aus Titan, mit einer Schutzkappe (5), dadurch gekennzeichnet, daß die Kappe die folgenden Bestandteile aufweist:
TiC: 28 bis 40%
Cr + Co: 12 bis 26%
Mo: 1 bis 6%
Ni: 3 bis 8%
Cu: 0,3 bis 1,5%
Fe Rest
2. Verfahren zur Herstellung der Schaufel (1) nach Anspruch 1, dadurch gekennzeichnet, daß es die folgenden Stufen aufweist:
- Anbringen der Kappe (5) mit den folgenden Bestandteilen:
TiC: 28 bis 40%
Cr + Co: 12 bis 26%
Mo: 1 bis 6%
Ni: 3 bis 8%
Cu: 0,3 bis 1,5%
Fe Rest

auf der Schaufel (1) unter Einfügung eines Blattes auf Kupferbasis mit einer Dicke von 70 bis 150 µm zwischen beiden Teilen;
- Erwärmen der Schaufel (1) mit ihrer Kappe (5) auf eine Temperatur zwischen 900°C und 950°C in einem Ofen unter Vakuum oder inerter Atmosphäre und Aufrechterhaltung dieser Temperatur während einer Dauer zwischen 30 und 75 Minuten; und
-Abkühlung auf Umgebungstemperatur.
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 EP0249092A1 (de) 1987-12-16
EP0249092B1 true 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 (2)

* 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

Families Citing this family (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE69321298T2 (de) * 1992-06-05 1999-04-08 Gec Alsthom Electromecanique S.A., Paris 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
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
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
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
US9470097B2 (en) * 2013-03-14 2016-10-18 Rolls-Royce Corporation 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
FR3123380B1 (fr) * 2021-05-28 2024-10-11 Safran Aircraft Engines Bouclier de bord d'attaque amélioré

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US2661286A (en) * 1950-01-13 1953-12-01 Mallory Sharon Titanium Corp Titanium base alloys containing silicon
GB692867A (en) * 1950-03-24 1953-06-17 Hard Metal Tools Ltd Improvements relating to turbine blades
US2664355A (en) * 1950-10-06 1953-12-29 Battelle Development Corp Ti-mn-fe alloys
FR1146511A (fr) * 1951-12-07 1957-11-13 Sintercast Corp America Aube de turbine
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
US3561886A (en) * 1969-02-07 1971-02-09 Gen Electric Turbine bucket erosion shield attachment
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
GB1479855A (en) * 1976-04-23 1977-07-13 Statni Vyzkumny Ustav Material Protective coating for titanium alloy blades for turbine and turbo-compressor rotors
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
GB2076019B (en) * 1980-05-16 1984-03-28 Metallurg Ind Inc Erosion-resistant alloys
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

Cited By (2)

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

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