EP0491075B1 - Procédé de préparation d'une aube de turbine en alliage à base de titane - Google Patents
Procédé de préparation d'une aube de turbine en alliage à base de titane Download PDFInfo
- Publication number
- EP0491075B1 EP0491075B1 EP90124757A EP90124757A EP0491075B1 EP 0491075 B1 EP0491075 B1 EP 0491075B1 EP 90124757 A EP90124757 A EP 90124757A EP 90124757 A EP90124757 A EP 90124757A EP 0491075 B1 EP0491075 B1 EP 0491075B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- protective layer
- laser
- titanium alloy
- turbine blade
- 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
Links
Images
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
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C8/00—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals
- C23C8/06—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using gases
- C23C8/08—Solid state diffusion of only non-metal elements into metallic material surfaces; Chemical surface treatment of metallic material by reaction of the surface with a reactive gas, leaving reaction products of surface material in the coating, e.g. conversion coatings, passivation of metals using gases only one element being applied
- C23C8/24—Nitriding
-
- 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
Definitions
- the invention is based on a method for producing a turbine blade made of a titanium base alloy, in which at least one blade portion located in the area of the blade tip and encompassing the blade leading edge by surface treatment of the titanium base alloy with a high-performance energy source with a protective layer made of an opposite one Titanium-based alloy is provided with a more erosion-resistant material.
- a blade manufactured using such a method is preferably used in low-pressure stages of steam turbines, since, despite its size, it meets the requirements placed there on the mechanical strength at temperatures up to approximately 150 ° C.
- the steam entering the turbine contains water droplets which hit the surfaces of the turbine blade exposed to the steam at high speed, such as, in particular, the blade leading edge and the parts of the blade surface which adjoin the blade leading edge on the suction side.
- the water drops can cause erosion damage.
- the blade section located in the area of the blade tip is particularly stressed, since the peripheral speed of the blade is greatest there.
- JP-A-62 165 510 A method of the type mentioned is described in JP-A-62 165 510. This process is used to produce a protective layer of high erosion resistance on a turbine blade made of a titanium-based alloy in the area of the blade tip.
- the protective layer is achieved by implanting carbon or nitrogen ions into the part of the blade surface to be coated using an ion accelerator.
- a protective layer produced in this way generally has a comparatively small thickness of typically 10 to 20 ⁇ m and can therefore be removed relatively quickly by eroding water drops. The production of a thicker layer requires considerable equipment.
- GB-A-1 479 855 and EP-B1-0 249 092 disclose further methods for producing an erosion-resistant turbine blade made of a titanium-based alloy.
- a protective body made of titanium carbide is soldered on the blade tip by means of a silver or copper solder in the area of the blade tip.
- Such a protective body is intended to protect particularly vulnerable areas of the turbine blade from erosion damage.
- Manufacturing and applying the protective body to the turbine blade, which is free of protective bodies are comparatively complex.
- difficulties with the adhesion of the protective body to the titanium-based alloy of the turbine body-free turbine blade cannot be ruled out.
- the invention has for its object to provide a method of the type mentioned, with which an erosion-resistant turbine blade in an inexpensive and suitable for mass production can be produced, which is characterized by a long service life even under difficult operating conditions.
- a sufficiently thick protective layer of the treated blade section and thus effective protection against drop erosion is achieved in a single method step, namely a surface treatment of the unprotected titanium base alloy by remelting by means of a laser.
- This protection against erosion is particularly safe, since the surface treatment as a result of diffusion processes on the one hand forms a protective layer firmly connected to the titanium-based alloy.
- this protective layer is also characterized by low crack resistance that is comparable to that of the titanium-based alloy.
- the device shown in the figure contains a support table 1 which can be displaced in a horizontal plane with a support plate 3 which carries a turbine blade 2 and which can be displaced in the direction of a coordinate axis x, and with a support plate 4 which supports the support plate 3 and which is perpendicular to the axis y X-axis is movable.
- 5 denotes a light of the wavelength ⁇ generating laser. The light generated by the laser is focused on the turbine blade in a treatment head 6. Of the Treatment head 6 can be displaced perpendicular to the support plate 3 in the direction of a coordinate axis z and, if necessary, can also be pivoted about the x and y axes.
- the coordination of the movements of the treatment head 6, which is firmly connected to the high-performance energy source, and of the support table 1 can take place via a memory-programmed control unit, not shown, which acts on the servo motors which cause the pushing and swiveling movements.
- Tubes 7 are attached to the treatment head 6, which contain a nitrogen-argon gas mixture, but possibly a mixture of nitrogen with one or more noble gases, from a storage container (not shown) to a point of irradiation 8 of the high-performance energy source on the suction-side surface 9 or the blade leading edge 10 of the turbine blade 2 leads.
- the supplied gas is free of oxygen and flows around the radiation point 8 forming the tracks 11 in such a way that surrounding atmospheric oxygen cannot enter.
- the tubes 7 are arranged such that the point of irradiation 8 is flushed with the gas from several sides, for example from the suction and pressure sides of the turbine blade 2. This ensures that the beam point 8 remains free of oxygen even in the area of the blade leading edge 10.
- the increased gas supply ensures improved cooling of the irradiated area located at the blade leading edge 10.
- the laser 5 used as a high-power energy source is moved cyclically with respect to the turbine blade 2.
- a cyclic movement can - as can be seen from the figure - be a back and forth movement along the coordinate axis y, whereby at the Reversal points each have a slight feed in the direction of the coordinate axis x.
- the part of the surface of the titanium base alloy located in the point of irradiation 8 is melted and alloy elements are introduced into the melt from the gas supplied through the tubes 7.
- nitrogen is introduced as the alloying element, which forms extremely hard titanium nitride with the titanium of the melted base alloy.
- titanium boride and / or titanium carbide can also be formed accordingly.
- the protective layer formed by remelting alloys in this surface treatment has a much greater erosion resistance to water droplets than the unprotected surface of the titanium-based alloy.
- the protective layer should be at least 0.1 mm thick, since otherwise unprotected surface areas may remain due to unevenness that cannot be ruled out during the re-alloying process.
- the thickness of the protective layer should not exceed 1 mm, since only then is a particularly good crack resistance and thus particularly good erosion protection guaranteed.
- the formation of undesirable cracks with layer thicknesses between 0.4 and 1 mm is avoided with great certainty if the laser parameters are set in such a way that the protective layer formed has a Vickers hardness of at most 900, preferably 500 to 700, HV.
- the traces 11 formed in the titanium-base alloy when the protective layer is produced by the laser 5 should be placed in such a way that they overlap by 50 to 90%, preferably 75 to 85%, since then a particularly good alloying of the alloy elements, such as in particular the Nitrogen in the formation of titanium nitride is guaranteed.
- the following operating parameters of the laser 5 are typical when producing an erosion-resistant protective layer of approx. 0.6 to 0.7 mm thickness and a Vickers hardness of 500 to 700 HV: Power: 1-10 kW Feed in track direction: 1-2 m / min Track overlap: 75-85% Spot diameter: approx. 2 mm Composition of the gas: Volume fractions N2: Ar approx. 3: 2 Amount of gas: approx. 50 l / min
- a blade section of the turbine blade 2 contains the protective layer, which lies in the region of the blade tip and comprises the blade leading edge 11 and a surface located on the suction side.
- This area is generally delimited by the blade leading edge 11 and the blade tip and in each case extends at most by a third of the width or length of the blade from the blade leading edge 11 or the blade tip to the blade leading edge or to the blade root.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Metallurgy (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Organic Chemistry (AREA)
- Laser Beam Processing (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Solid-Phase Diffusion Into Metallic Material Surfaces (AREA)
- Other Surface Treatments For Metallic Materials (AREA)
- Electrical Discharge Machining, Electrochemical Machining, And Combined Machining (AREA)
Claims (7)
- Procédé de préparation d'une aube de turbine (2) en alliage à base de titane, lors duquel au moins une section d'aube, se trouvant dans la zone du bout de l'aube et englobant le bord d'attaque de l'aube (10) est pourvue, grâce à un traitement de surface de l'alliage à base de titane, par l'entremise d'une source d'énergie haute puissance, d'une couche de protection en un matériau plus résistant à l'érosion par rapport à l'alliage à base de titane, caractérisé en ce que la couche de protection est formée par une opération de formation d'alliage par refusion, et en ce que l'on utilise dans ce but en tant que source d'énergie haute puissance un laser (5).
- Procédé selon la revendication 1, caractérisé en ce que l'opération de formation d'alliage par refusion est effectuée à l'aide d'un gaz formant avec l'alliage à base de titane un borure, un carbure et/ou un nitrure.
- Procédé selon la revendication 2, caractérisé en ce que l'on utilise en tant que gaz un mélange azote-gaz rare.
- Procédé selon l'une quelconque des revendications 2 à 3, caractérisé en ce que la couche de protection est épaisse d'au moins 0,1 mm et au plus de 1 mm.
- Procédé selon la revendication 4, caractérisé en ce que les paramètres de fonctionnement du laser (5) sont déterminés de manière à ce que la couche de protection présente une épaisseur comprise entre 0,4 et 1 mm et une dureté Vickers d'au plus 900 HV, de préférence de 500 à 700 HV.
- Procédé selon la revendication 5, caractérisé en ce que le laser (5) est déplacé de manière cyclique, et en ce que des traces (11), formées par le laser (5) dans l'alliage à base de titane et formant la couche de protection, sont placées de sorte que des traces avoisinantes (11) se superposent de 50 à 90 %, de préférence de 75 à 85 %.
- Procédé selon la revendication 6, caractérisé en ce que dans la zone du bord d'attaque de l'aube (10), des traces placées (11) sont balayées de plusieurs côtés par le gaz.
Priority Applications (8)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE59009381T DE59009381D1 (de) | 1990-12-19 | 1990-12-19 | Verfahren zur Herstellung einer Turbinenschaufel aus einer Titan-Basislegierung. |
ES90124757T ES2075874T3 (es) | 1990-12-19 | 1990-12-19 | Procedimiento para la fabricacion de un alabe de turbina a partir de una aleacion base de titanio. |
EP90124757A EP0491075B1 (fr) | 1990-12-19 | 1990-12-19 | Procédé de préparation d'une aube de turbine en alliage à base de titane |
US07/802,320 US5366345A (en) | 1990-12-19 | 1991-12-04 | Turbine blade of a basic titanium alloy and method of manufacturing it |
CS913843A CZ282365B6 (cs) | 1990-12-19 | 1991-12-17 | Turbínová lopatka ze slitiny na bázi titanu a způsob její výroby |
SU915010399A RU2033526C1 (ru) | 1990-12-19 | 1991-12-18 | Способ изготовления лопатки турбины из сплава на основе титана |
JP33711491A JP3217414B2 (ja) | 1990-12-19 | 1991-12-19 | チタン基合金から成るタービン羽根の製造方法 |
CN91111855.1A CN1024703C (zh) | 1990-12-19 | 1991-12-19 | 一种制造钛基合金涡轮叶片的方法 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP90124757A EP0491075B1 (fr) | 1990-12-19 | 1990-12-19 | Procédé de préparation d'une aube de turbine en alliage à base de titane |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0491075A1 EP0491075A1 (fr) | 1992-06-24 |
EP0491075B1 true EP0491075B1 (fr) | 1995-07-05 |
Family
ID=8204862
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP90124757A Expired - Lifetime EP0491075B1 (fr) | 1990-12-19 | 1990-12-19 | Procédé de préparation d'une aube de turbine en alliage à base de titane |
Country Status (8)
Country | Link |
---|---|
US (1) | US5366345A (fr) |
EP (1) | EP0491075B1 (fr) |
JP (1) | JP3217414B2 (fr) |
CN (1) | CN1024703C (fr) |
CZ (1) | CZ282365B6 (fr) |
DE (1) | DE59009381D1 (fr) |
ES (1) | ES2075874T3 (fr) |
RU (1) | RU2033526C1 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2006005527A1 (fr) | 2004-07-09 | 2006-01-19 | Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. | Procede de fabrication de couches marginales resistantes a l'usure et a la fatigue a partir d'alliages de titane et composants ainsi fabriques |
Families Citing this family (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2696759B1 (fr) * | 1992-10-09 | 1994-11-04 | Alsthom Gec | Procédé de nitruration d'une pièce en alliage de titane et dispositif de projection d'azote et de gaz neutre. |
GB9320003D0 (en) * | 1993-09-28 | 1993-11-17 | Secr Defence | Improved method for the surface treatment of metals |
DE59406283D1 (de) * | 1994-08-17 | 1998-07-23 | Asea Brown Boveri | Verfahren zur Herstellung einer Turbinenschaufel aus einer (alpha-Beta)-Titan-Basislegierung |
EP0852164B1 (fr) * | 1995-09-13 | 2002-12-11 | Kabushiki Kaisha Toshiba | Procede de fabrication de pales de turbine en alliage de titane et pales de turbines en alliage de titane |
US5889254A (en) * | 1995-11-22 | 1999-03-30 | General Electric Company | Method and apparatus for Nd: YAG hardsurfacing |
DE19637450C1 (de) * | 1996-09-13 | 1998-01-15 | Fraunhofer Ges Forschung | Verschleißbeständiger, mechanisch hochbelastbarer und reibungsarmer Randschichtaufbau für Titan und dessen Legierungen sowie Verfahren zu seiner Herstellung |
GB2328221A (en) * | 1997-08-15 | 1999-02-17 | Univ Brunel | Surface treatment of titanium alloys |
DE19751337A1 (de) | 1997-11-19 | 1999-05-27 | Fraunhofer Ges Forschung | Verschleißbeständiger, mechanisch hochbelastbarer und reibungsarmer Randschichtaufbau für Titan oder seine Legierungen sowie Verfahren zu seiner Herstellung |
JPH11182204A (ja) * | 1997-12-15 | 1999-07-06 | Toshiba Corp | タービン動翼 |
DE19920567C2 (de) * | 1999-05-03 | 2001-10-04 | Fraunhofer Ges Forschung | Verfahren zur Beschichtung eines im wesentlichen aus Titan oder einer Titanlegierung bestehenden Bauteils |
GB0504576D0 (en) * | 2005-03-05 | 2005-04-13 | Alstom Technology Ltd | Turbine blades and methods for depositing an erosion resistant coating on the same |
US8203095B2 (en) | 2006-04-20 | 2012-06-19 | Materials & Electrochemical Research Corp. | Method of using a thermal plasma to produce a functionally graded composite surface layer on metals |
DE102006050799A1 (de) * | 2006-10-27 | 2008-05-08 | Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. | Verfahren und Vorrichtung zum Randschichthärten formkomplizierter Bauteile |
US20080181808A1 (en) | 2007-01-31 | 2008-07-31 | Samuel Vinod Thamboo | Methods and articles relating to high strength erosion resistant titanium alloy |
JP5411120B2 (ja) * | 2010-12-27 | 2014-02-12 | 株式会社日立製作所 | チタン合金製タービン翼 |
AU2013218795B2 (en) * | 2012-02-09 | 2017-04-13 | Kinetic Elements Pty Ltd | Surface |
JP2015532695A (ja) | 2012-07-30 | 2015-11-12 | ゼネラル・エレクトリック・カンパニイ | 金属前縁保護ストリップ、対応する翼形部および製造方法 |
JP5936530B2 (ja) | 2012-12-19 | 2016-06-22 | 三菱日立パワーシステムズ株式会社 | タービンの動翼の製造方法 |
US10078136B2 (en) * | 2014-03-25 | 2018-09-18 | Amazon Technologies, Inc. | Sense and avoid for automated mobile vehicles |
CN113529008B (zh) * | 2021-07-15 | 2022-08-19 | 西北有色金属研究院 | 一种在钛或钛合金表面制备梯度复合耐磨涂层的方法 |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3637320A (en) * | 1968-12-31 | 1972-01-25 | Texas Instruments Inc | Coating for assembly of parts |
US3784402A (en) * | 1969-05-02 | 1974-01-08 | Texas Instruments Inc | Chemical vapor deposition coatings on titanium |
GB1479855A (en) * | 1976-04-23 | 1977-07-13 | Statni Vyzkumny Ustav Material | Protective coating for titanium alloy blades for turbine and turbo-compressor rotors |
JPS54123600A (en) * | 1978-03-17 | 1979-09-25 | Toyo Soda Mfg Co Ltd | Production of titanium carbonitride |
US4364969A (en) * | 1979-12-13 | 1982-12-21 | United Kingdom Atomic Energy Authority | Method of coating titanium and its alloys |
US4299860A (en) * | 1980-09-08 | 1981-11-10 | The United States Of America As Represented By The Secretary Of The Navy | Surface hardening by particle injection into laser melted surface |
JPS62113802A (ja) * | 1985-11-13 | 1987-05-25 | Toshiba Corp | タ−ビン翼 |
FR2599425B1 (fr) * | 1986-05-28 | 1988-08-05 | Alsthom | Plaquette de protection pour aube en titane et procede de brasage d'une telle plaquette. |
JPH0833998B2 (ja) * | 1986-09-12 | 1996-03-29 | ブラザー工業株式会社 | 磁気記録媒体の製造方法 |
JPH0672521B2 (ja) * | 1987-02-04 | 1994-09-14 | 三菱電機株式会社 | スクロ−ル流体機械 |
FR2612106B1 (fr) * | 1987-03-09 | 1989-05-19 | Alsthom | Procede de pose d'un revetement protecteur sur une aube en alliage de titane et aube ainsi revetue |
US4745033A (en) * | 1987-03-24 | 1988-05-17 | Amax Inc. | Oxidation resistant coatings for molybdenum |
DD276210A3 (de) * | 1987-05-11 | 1990-02-21 | Bergmann Borsig Veb | Verfahren zur herstellung eines erosionsschutzes fuer turbinenschaufeln |
CH672450A5 (fr) * | 1987-05-13 | 1989-11-30 | Bbc Brown Boveri & Cie |
-
1990
- 1990-12-19 ES ES90124757T patent/ES2075874T3/es not_active Expired - Lifetime
- 1990-12-19 EP EP90124757A patent/EP0491075B1/fr not_active Expired - Lifetime
- 1990-12-19 DE DE59009381T patent/DE59009381D1/de not_active Expired - Fee Related
-
1991
- 1991-12-04 US US07/802,320 patent/US5366345A/en not_active Expired - Lifetime
- 1991-12-17 CZ CS913843A patent/CZ282365B6/cs unknown
- 1991-12-18 RU SU915010399A patent/RU2033526C1/ru active
- 1991-12-19 CN CN91111855.1A patent/CN1024703C/zh not_active Expired - Fee Related
- 1991-12-19 JP JP33711491A patent/JP3217414B2/ja not_active Expired - Fee Related
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2006005527A1 (fr) | 2004-07-09 | 2006-01-19 | Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. | Procede de fabrication de couches marginales resistantes a l'usure et a la fatigue a partir d'alliages de titane et composants ainsi fabriques |
Also Published As
Publication number | Publication date |
---|---|
DE59009381D1 (de) | 1995-08-10 |
CN1024703C (zh) | 1994-05-25 |
JP3217414B2 (ja) | 2001-10-09 |
CS384391A3 (en) | 1992-08-12 |
RU2033526C1 (ru) | 1995-04-20 |
ES2075874T3 (es) | 1995-10-16 |
CN1062577A (zh) | 1992-07-08 |
CZ282365B6 (cs) | 1997-07-16 |
EP0491075A1 (fr) | 1992-06-24 |
US5366345A (en) | 1994-11-22 |
JPH05186861A (ja) | 1993-07-27 |
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PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
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