EP0697503A1 - Procédure pour la construction d'une aube de turbine en alliage de base (alpha-bêta)-Titane - Google Patents

Procédure pour la construction d'une aube de turbine en alliage de base (alpha-bêta)-Titane Download PDF

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Publication number
EP0697503A1
EP0697503A1 EP94112802A EP94112802A EP0697503A1 EP 0697503 A1 EP0697503 A1 EP 0697503A1 EP 94112802 A EP94112802 A EP 94112802A EP 94112802 A EP94112802 A EP 94112802A EP 0697503 A1 EP0697503 A1 EP 0697503A1
Authority
EP
European Patent Office
Prior art keywords
titanium
blade
nitrogen
gas
carried out
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
EP94112802A
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German (de)
English (en)
Other versions
EP0697503B1 (fr
Inventor
Claus Dr. Gerdes
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.)
ABB AG Germany
Original Assignee
ABB Management AG
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 ABB Management AG filed Critical ABB Management AG
Priority to EP94112802A priority Critical patent/EP0697503B1/fr
Priority to DE59406283T priority patent/DE59406283D1/de
Priority to US08/496,188 priority patent/US5573604A/en
Priority to JP7207201A priority patent/JPH08176767A/ja
Priority to CN95115293.9A priority patent/CN1119698A/zh
Publication of EP0697503A1 publication Critical patent/EP0697503A1/fr
Application granted granted Critical
Publication of EP0697503B1 publication Critical patent/EP0697503B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • 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
    • 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

Definitions

  • the invention is based on a method for producing an erosion-resistant turbine blade made of an ( ⁇ / ⁇ ) -titanium-based alloy according to the introductory part of patent claim 1.
  • a blade manufactured according to such a method is preferably used in low-pressure stages of steam turbines because it is because of their low density, even with large lengths, meets the requirements placed on the mechanical strength at temperatures up to approx. 150 oC .
  • the water vapor entering the turbine contains drops which hit the surfaces of the turbine blade exposed to the incoming 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 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.
  • EP-A-0 491 075. This process is used to produce a protective layer of high erosion resistance on a turbine blade made of an ( ⁇ / ⁇ ) titanium-based alloy in the area of the blade tip.
  • the protective layer is remelted the ( ⁇ / ⁇ ) -titanium-based alloy is generated on the surface in a boron, carbon or nitrogen-containing gas atmosphere by means of a laser.
  • Such a layer is extremely hard compared to the untreated areas of the blade and effectively protects the underlying titanium base alloy against drop erosion.
  • it has been shown that such an erosion-protected blade material has a lower fatigue strength than the unprotected blade material.
  • the invention is based on the object of specifying a method of the type mentioned at the outset, with which an erosion-resistant turbine blade can be produced in an inexpensive manner and suitable for series production, which can also be subjected to constantly changing loads characterized by a long service life.
  • a turbine blade is created in a few easy-to-carry out process steps, namely a surface treatment of the unprotected ( ⁇ / ⁇ ) titanium base alloy by remelting alloys by means of a high-performance energy source and by subsequent heat treatment, which in the area of its blade tip is characterized by both high erosion resistance and good fatigue resistance.
  • Structural changes that have a particularly favorable effect on the fatigue strength occur when the heat treatment is carried out at temperatures between 650 and 700 ° C. If the heat treatment is carried out for at least one hour, preferably between 2 to 6 hours, homogenization occurs between the ⁇ stabilized phases due to diffusion processes. At the same time, recrystallization occurs in the remelted protective layer and in the heat-affected zone of the adjoining ( ⁇ / ⁇ ) titanium base alloy, grain sizes with a diameter between 20 and 100 ⁇ m being formed. However, the occurrence of evenly distributed, vanadium-rich ⁇ -excretions is of particular importance. The low solubility of vanadium in ⁇ -titanium should particularly promote this.
  • the fatigue strength can additionally be improved by mechanical strengthening, in particular by controlled shot peening, of the heat-treated blade section.
  • a further improvement in fatigue strength can be achieved if the remelting alloying is carried out in a gas atmosphere which contains an inert carrier gas in addition to a boron, carbon and / or nitrogen-containing gas, the ratio of the partial pressures of carrier gas to boron, carbon and / or nitrogenous gas is at least 2: 1.
  • a gas atmosphere is preferred in which the ratio is greater than 2: 1 and at most 4: 1, and in which noble gas, such as argon in particular, and nitrogen are used as gases.
  • FIGS. 1 and 2 each show a diagram in which the erosion resistance or fatigue strength of vane sections which were produced according to the prior art is compared with the erosion resistance or fatigue strength of vane sections which were produced by the method according to the invention were.
  • the uncoated turbine blade is supported on a horizontally displaceable support table.
  • the blade tip is exposed in the area of the blade leading edge to an oxygen-free gas atmosphere containing boron, carbide and / or nitrogen and at the same time is irradiated with a high-performance energy source, in particular with a laser.
  • the turbine blade consisted of a titanium-based alloy with 6 percent by weight aluminum and 4 percent by weight vanadium (Ti-6Al-4V) and became a CO2 gas laser with an output of 1.5 kW and with an energy spectrum according to a Gaussian distribution used.
  • the preferred width of the laser beams was 1.3 mm.
  • the gas atmosphere contained nitrogen and argon and was carried in the form of a gas stream to the point of laser irradiation on the blade surface.
  • a stream of nitrogen was enveloped by a stream of argon.
  • the nitrogen uptake during remelting alloying was dependent on Partial pressure of nitrogen in the gas stream.
  • the ratio of the partial pressures of argon to nitrogen was varied between 2: 1 and 4: 1.
  • the laser was moved on the meandering paths opposite the turbine blade.
  • the part of the surface of the ( ⁇ / ⁇ ) titanium base alloy located at the point of incidence was melted and nitrogen was alloyed into the melt, which formed hard titanium nitride with the titanium of the melted base alloy.
  • titanium boride and / or titanium carbide could also be formed accordingly.
  • the protective layer formed in this way and typically having a thickness between 0.4 and 1 mm essentially contains titanium nitrides, which are embedded in a matrix of ⁇ -titanium .
  • the morphology and distribution of the titanium nitrides depend on the process parameters for remelting alloys and on the nitrogen concentration in the gas atmosphere. Depending on the nitrogen concentration in the gas atmosphere, the titanium nitrides can be plate-shaped or dendritic.
  • the protective layer formed can have a Vickers hardness of 600 to 800 HV, depending on the conditions during remelting alloy, compared to a Vickers hardness of 350 to 370 HV of the ( ⁇ / ⁇ ) titanium base alloy.
  • the erosion resistance and the fatigue strength were measured on such a blade material.
  • the erosion resistance was measured in a test machine which essentially contained a rotating double arm, to the free end of which rectangular samples of the blade material to be examined were attached.
  • the double arm was arranged in a chamber which was evacuated to approx. 25 mbar in order to avoid air friction and to be able to reach high speeds.
  • a droplet generator was attached to the periphery of the chamber, which generated three jets with water droplets of the same size. The water drops hit the surface of the samples perpendicularly.
  • the intensity of each impact was determined by the size of the peripheral speed of the rotating arm at the location of the impact.
  • the droplets generated by the generator typically had a diameter of approximately 0.2 mm.
  • the peripheral speed of the arm at the location of the sample to be examined was constant and varied from sample to sample between 300 and 500 m / s.
  • the volume loss [mm3] of the examined sample was determined as a function of the number of impinging drops at a specified peripheral speed (Fig. 1).
  • the sample was subjected to an alternating bending load in a servo-hydraulic testing machine under four-point bending conditions with a frequency of 30 Hz and with a stress ratio R ( ⁇ min / ⁇ max ) of 0.2 over 10 über cycles.
  • the ( ⁇ / ⁇ ) titanium base alloy has a very low erosion resistance compared to the protective layer produced by remelting with a ratio of the partial pressures argon to nitrogen such as 2: 1.
  • the untreated ( ⁇ / ⁇ ) titanium base alloy is much more ductile and is plastically deformed by the impacting water drops. Therefore, erosion craters form at a very early stage, which later overlap and eventually lead to cracks or the detachment of plate-shaped areas.
  • the protective layer formed by remelting alloys is extremely hard and thus largely prevents it the unwanted crater formation.
  • the great hardness and, accordingly, the low ductility of the protective layer means that the fatigue strength of the protective layer decreases by approximately 70% compared to the ( ⁇ / ⁇ ) titanium base alloy (Fig. 2).
  • the coated blade section was heat-treated at temperatures between 650 and 700 ° C. for 4 hours.
  • above all vanadium-rich and uniformly distributed ⁇ -precipitates were formed in the alloyed protective layer.
  • FIGS. 1 and 2 these structural changes bring about an improvement in the fatigue strength of the protective layer by approximately 10 to 15% (sample A in FIG. 2) while maintaining the erosion resistance of the non-heat-treated protective layer.
  • a further improvement in the fatigue strength practically while maintaining the erosion resistance of the non-heat-treated protective layer was additionally achieved by mechanically strengthening the heat-treated protective layer with controlled shot peening.
  • Typical values of the shot peening used here were a ball diameter of 0.3 and compressed air pressures to accelerate the balls from 3 to 5 bar.
  • Almen intensities of 0.2 mm A the fatigue strength of the protective layer compared to the non-heat-treated and non-shot-peened protective layer was doubled.
  • a further improvement in the fatigue strength of the protective layer while maintaining the good erosion resistance of the non-heat-treated protective layer was also achieved in that the ratio of the partial pressures of argon to nitrogen in the gas atmosphere is greater than 2: 1 and is 4: 1.
  • this measure enabled the fatigue strength to be compared to that also heat-treated Protective layer according to Example A can be increased by approximately 20%. ( Figures 1 and 2).
  • a version of shot peening with at least double full coverage is particularly advantageous for a high fatigue strength of the structure. It is also extremely favorable to choose the intensity for controlled shot peening greater than 0.2 and less than 0.45 mm A. Shot peening with an alpine pasture intensity of approx. 0.3 mm A increased the fatigue strength of the protective layer according to example B compared to the corresponding protective layer, which, however, was only strengthened with shot peening of the alpine pasture intensity 0.2 mm A by approx -20% can be improved, whereby a protective layer has been achieved which has practically the same erosion resistance as the untreated protective layer and which at the same time achieves approx. 85% of the fatigue strength of the titanium-based alloy (Fig. 2).

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP94112802A 1994-08-17 1994-08-17 Procédure pour la construction d'une aube de turbine en alliage de base (alpha-bêta)-Titane Expired - Lifetime EP0697503B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP94112802A EP0697503B1 (fr) 1994-08-17 1994-08-17 Procédure pour la construction d'une aube de turbine en alliage de base (alpha-bêta)-Titane
DE59406283T DE59406283D1 (de) 1994-08-17 1994-08-17 Verfahren zur Herstellung einer Turbinenschaufel aus einer (alpha-Beta)-Titan-Basislegierung
US08/496,188 US5573604A (en) 1994-08-17 1995-06-28 Process for manufacturing a turbine blade made of an (alpha/beta)-titanium base alloy
JP7207201A JPH08176767A (ja) 1994-08-17 1995-08-14 （α／β）−チタンをベースとした合金からタービン羽根を造るための方法
CN95115293.9A CN1119698A (zh) 1994-08-17 1995-08-16 由(α/β)钛基合金构成的气轮机叶片的制造方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP94112802A EP0697503B1 (fr) 1994-08-17 1994-08-17 Procédure pour la construction d'une aube de turbine en alliage de base (alpha-bêta)-Titane

Publications (2)

Publication Number Publication Date
EP0697503A1 true EP0697503A1 (fr) 1996-02-21
EP0697503B1 EP0697503B1 (fr) 1998-06-17

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EP94112802A Expired - Lifetime EP0697503B1 (fr) 1994-08-17 1994-08-17 Procédure pour la construction d'une aube de turbine en alliage de base (alpha-bêta)-Titane

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Country Link
US (1) US5573604A (fr)
EP (1) EP0697503B1 (fr)
JP (1) JPH08176767A (fr)
CN (1) CN1119698A (fr)
DE (1) DE59406283D1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
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
US8920881B2 (en) 2004-10-16 2014-12-30 MTU Aero Engines AG Method for producing a component covered with a wear-resistant coating

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EP0722510B1 (fr) * 1993-10-06 1999-05-12 The University Of Birmingham Procede de preparation d'un produit en alliage de titane
GB2328221A (en) * 1997-08-15 1999-02-17 Univ Brunel Surface treatment of titanium alloys
US6064031A (en) * 1998-03-20 2000-05-16 Mcdonnell Douglas Corporation Selective metal matrix composite reinforcement by laser deposition
US6395327B1 (en) * 1999-03-12 2002-05-28 Zimmer, Inc. Enhanced fatigue strength orthopaedic implant with porous coating and method of making same
GB2365078B (en) 2000-07-27 2004-04-21 Rolls Royce Plc A gas turbine engine blade
SE522722C2 (sv) * 2001-03-28 2004-03-02 Seco Tools Ab Skärverktyg belagt med titandiborid
WO2004003243A1 (fr) * 2002-06-27 2004-01-08 Memry Corporation Procede de fabrication d'articles superelastiques en titane et articles derives
US20040261912A1 (en) * 2003-06-27 2004-12-30 Wu Ming H. Method for manufacturing superelastic beta titanium articles and the articles derived therefrom
US20040168751A1 (en) * 2002-06-27 2004-09-02 Wu Ming H. Beta titanium compositions and methods of manufacture thereof
JP3716236B2 (ja) * 2002-08-09 2005-11-16 三菱重工業株式会社 タービンの付着物除去設備
CA2502575A1 (fr) * 2002-11-15 2004-06-03 University Of Utah Research Foundation Revetements au borure de titane integres appliques sur des surfaces en titane et procedes associes
US8122600B2 (en) * 2003-03-03 2012-02-28 United Technologies Corporation Fan and compressor blade dovetail restoration process
US7509734B2 (en) * 2003-03-03 2009-03-31 United Technologies Corporation Repairing turbine element
GB0412915D0 (en) * 2004-06-10 2004-07-14 Rolls Royce Plc Method of making and joining an aerofoil and root
US7195455B2 (en) * 2004-08-17 2007-03-27 General Electric Company Application of high strength titanium alloys in last stage turbine buckets having longer vane lengths
JP4888628B2 (ja) * 2004-10-01 2012-02-29 Ｎｏｋ株式会社 燃料電池用構成部品の製造方法
US7459105B2 (en) * 2005-05-10 2008-12-02 University Of Utah Research Foundation Nanostructured titanium monoboride monolithic material and associated methods
US20060289088A1 (en) * 2005-06-28 2006-12-28 General Electric Company Titanium treatment to minimize fretting
US7506440B2 (en) * 2005-06-28 2009-03-24 General Electric Company Titanium treatment to minimize fretting
US7931446B2 (en) * 2007-02-14 2011-04-26 X-Treme Aerospace Inc. Treatment of turbine blades to increase hardness
EP2342364A1 (fr) * 2008-09-02 2011-07-13 Zimmer, Inc. Procédé pour améliorer la résistance à la fatigue par frottement d'alliages
EP2329063A4 (fr) * 2008-09-29 2012-03-21 William D Hurst Appareil de formation d un revêtement d alliage et procédé de métalluration
US20100176339A1 (en) * 2009-01-12 2010-07-15 Chandran K S Ravi Jewelry having titanium boride compounds and methods of making the same
GB0906850D0 (en) * 2009-04-22 2009-06-03 Rolls Royce Plc Method of manufacturing an aerofoil
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
US9737933B2 (en) 2012-09-28 2017-08-22 General Electric Company Process of fabricating a shield and process of preparing a component
KR102002239B1 (ko) * 2015-04-17 2019-07-19 미츠비시 히타치 파워 시스템즈 가부시키가이샤 증기 터빈 동익 및 증기 터빈 동익의 제조 방법

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EP0491075A1 (fr) * 1990-12-19 1992-06-24 Asea Brown Boveri Ag Procédé de préparation d'une aube de turbine en alliage à base de titane
JPH04289154A (ja) * 1991-03-18 1992-10-14 Fuji Electric Co Ltd Ｔｉ合金製タービンブレードとその表面改質方法
WO1994014955A1 (fr) * 1992-12-21 1994-07-07 Purdue Research Foundation Deblocage de la voie commune de la synthese d'aminoacide aromatique

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Cited By (3)

* Cited by examiner, † Cited by third party
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
DE102004033342A1 (de) * 2004-07-09 2006-02-02 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Verfahren zur Herstellung von verschleißbeständigen und ermüdungsresistenten Randschichten in Titan-Legierungen und damit hergestellte Bauteile
US8920881B2 (en) 2004-10-16 2014-12-30 MTU Aero Engines AG Method for producing a component covered with a wear-resistant coating

Also Published As

Publication number Publication date
US5573604A (en) 1996-11-12
EP0697503B1 (fr) 1998-06-17
DE59406283D1 (de) 1998-07-23
JPH08176767A (ja) 1996-07-09
CN1119698A (zh) 1996-04-03

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