EP0249092A1 - 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 PDFInfo
- 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
- Authority
- 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
Links
- 238000005219 brazing Methods 0.000 title claims abstract description 7
- 238000000034 method Methods 0.000 title claims abstract description 6
- 239000010936 titanium Substances 0.000 title claims abstract description 6
- 229910052719 titanium Inorganic materials 0.000 title claims abstract description 6
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 title claims abstract description 5
- 239000010949 copper Substances 0.000 claims abstract description 9
- 229910052802 copper Inorganic materials 0.000 claims abstract description 7
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 6
- 230000001681 protective effect Effects 0.000 claims abstract description 4
- 238000001816 cooling Methods 0.000 claims description 4
- 230000000295 complement effect Effects 0.000 claims description 2
- 238000009434 installation Methods 0.000 claims description 2
- 229910052759 nickel Inorganic materials 0.000 abstract description 4
- 229910052804 chromium Inorganic materials 0.000 abstract description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 abstract description 3
- 238000005299 abrasion Methods 0.000 abstract 1
- PXHVJJICTQNCMI-UHFFFAOYSA-N nickel Substances [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 7
- MTPVUVINMAGMJL-UHFFFAOYSA-N trimethyl(1,1,2,2,2-pentafluoroethyl)silane Chemical compound C[Si](C)(C)C(F)(F)C(F)(F)F MTPVUVINMAGMJL-UHFFFAOYSA-N 0.000 description 6
- 229910001069 Ti alloy Inorganic materials 0.000 description 3
- 239000011651 chromium Substances 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N iron Substances [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 2
- 239000010941 cobalt Substances 0.000 description 2
- 229910017052 cobalt Inorganic materials 0.000 description 2
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 2
- 238000004090 dissolution Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 238000005476 soldering Methods 0.000 description 2
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 description 1
- 239000011230 binding agent Substances 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 229910000734 martensite Inorganic materials 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 229910052750 molybdenum Inorganic materials 0.000 description 1
- 239000011733 molybdenum Substances 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 238000005245 sintering Methods 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- -1 titanium carbides Chemical class 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
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.
Landscapes
- 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)
Abstract
Description
- La présente invention concerne une plaquette de protection pour aube de turbine en alliage de titane.
- 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.
- 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).
-
-
- 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 450-500°C 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 (3)
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.
- Pose de la plaquette (5) sur l'aube (1) avec interposition entre les deux d'un feuillard (6) à base de cuivre d'une épaisseur comprise entre 7 et 15/100ème de mm.
- Montée à une température comprise entre 900° 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.
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 (fr) | 1987-12-16 |
EP0249092B1 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) | CS276725B6 (fr) |
DE (1) | DE3761833D1 (fr) |
ES (1) | ES2013272B3 (fr) |
FR (1) | FR2599425B1 (fr) |
GR (1) | GR3000501T3 (fr) |
ZA (1) | ZA873837B (fr) |
Cited By (6)
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 (fr) * | 1992-12-30 | 1994-07-06 | General Electric Company | Procédé pour la fabrication d'une aube de turbine avec protection contre l'érosion à gouttelettes d'eau et produit correspondant |
EP0780187A1 (fr) * | 1995-12-22 | 1997-06-25 | Gec Alsthom Electromecanique Sa | Procédé pour fabriquer une aube en titane alphabeta comprenant un insert de titane beta métastable, et aube réalisée par un tel procédé |
WO2011039075A1 (fr) * | 2009-09-30 | 2011-04-07 | Siemens Aktiengesellschaft | Aube mobile d'étage final d'une turbine à vapeur |
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)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0491075B1 (fr) * | 1990-12-19 | 1995-07-05 | Asea Brown Boveri Ag | Procédé de préparation d'une aube de turbine en alliage à base de titane |
EP0578518B1 (fr) * | 1992-06-05 | 1998-09-30 | Gec Alsthom Electromecanique Sa | Procédé de formation d'un insert sur une pièce à revêtir en acier ou en alliage de titane |
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 (fr) * | 2013-03-14 | 2014-10-02 | Hodgson Benedict N | 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 |
Citations (5)
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 (fr) * | 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 |
-
1986
- 1986-05-28 FR FR8607661A patent/FR2599425B1/fr not_active Expired
-
1987
- 1987-05-26 EP EP87107673A patent/EP0249092B1/fr not_active Expired - Lifetime
- 1987-05-26 JP JP62129588A patent/JPS62297442A/ja active Pending
- 1987-05-26 DE DE8787107673T patent/DE3761833D1/de not_active Expired - Fee Related
- 1987-05-26 AT AT87107673T patent/ATE50824T1/de not_active IP Right Cessation
- 1987-05-26 ES ES87107673T patent/ES2013272B3/es not_active Expired - Lifetime
- 1987-05-27 ZA ZA873837A patent/ZA873837B/xx unknown
- 1987-05-28 CN CN87104497A patent/CN1009472B/zh not_active Expired
- 1987-05-28 CS CS873892A patent/CS276725B6/cs unknown
- 1987-05-28 US US07/054,926 patent/US4795313A/en not_active Expired - Fee Related
- 1987-05-28 CS CS903827A patent/CS276857B6/cs unknown
-
1990
- 1990-05-23 GR GR90400323T patent/GR3000501T3/el unknown
- 1990-08-02 CS CS903827A patent/CS382790A3/cs unknown
Patent Citations (5)
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)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0605152A1 (fr) * | 1992-12-30 | 1994-07-06 | General Electric Company | Procédé pour la fabrication d'une aube de turbine avec protection contre l'érosion à gouttelettes d'eau et produit correspondant |
DE4310896C1 (de) * | 1993-04-02 | 1994-03-24 | Thyssen Industrie | Verfahren zum Herstellen von verschleißfesten Kanten an Turbinenschaufeln |
EP0780187A1 (fr) * | 1995-12-22 | 1997-06-25 | Gec Alsthom Electromecanique Sa | Procédé pour fabriquer une aube en titane alphabeta comprenant un insert de titane beta métastable, et aube réalisée par un tel procédé |
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 (fr) * | 2009-09-30 | 2011-04-07 | Siemens Aktiengesellschaft | Aube mobile d'étage final d'une turbine à vapeur |
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 (fr) | 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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