EP2876172A1 - Procédé de fabrication et de réparation de composants d'une turbomachine à partir de superalliages à base de nickel - Google Patents

Procédé de fabrication et de réparation de composants d'une turbomachine à partir de superalliages à base de nickel Download PDF

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Publication number
EP2876172A1
EP2876172A1 EP13194500.8A EP13194500A EP2876172A1 EP 2876172 A1 EP2876172 A1 EP 2876172A1 EP 13194500 A EP13194500 A EP 13194500A EP 2876172 A1 EP2876172 A1 EP 2876172A1
Authority
EP
European Patent Office
Prior art keywords
aging annealing
aging
nickel
components
temperature
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.)
Withdrawn
Application number
EP13194500.8A
Other languages
German (de)
English (en)
Inventor
Johannes Gabel
Malogrzata Zielinska
Michael Weiss
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines 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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP13194500.8A priority Critical patent/EP2876172A1/fr
Publication of EP2876172A1 publication Critical patent/EP2876172A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D6/00—Heat treatment of ferrous alloys
    • C21D6/001—Heat treatment of ferrous alloys containing Ni
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D6/00—Heat treatment of ferrous alloys
    • C21D6/02—Hardening by precipitation
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
    • 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
    • F01D5/005—Repairing methods or devices
    • 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
    • F01D5/286—Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion
    • 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
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
    • C21D1/78—Combined heat-treatments not provided for above
    • C21D1/785—Thermocycling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/238—Soldering
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/175—Superalloys

Definitions

  • the invention proposes, in order to reduce the expense in processes for producing and repairing components made of nickel-base superalloys, to carry out the aging annealing not only after completion of the component as the last method step, but already at the earliest point in time of the method, ie at a time, in which still follow at least one or more processing steps on the aging annealing.
  • the aging annealing should be carried out at a time that is at a temperature of more than 1100 ° C after the last heat treatment of the component. This can be avoided that the effect of the Alertungsglühung with the formation of the contribution to the strength and hardness excretion by a subsequently too high Temperature load and corresponding resolution of excretions is nullified.
  • the aging annealing for many components can be carried out under the same conditions, so that the expense and the costs for the aging annealing are reduced.
  • the components with their basic components without additional, later to be attached attachments of aging annealing are exposed, so that also reduces the effort.
  • the aging annealing may be carried out at a temperature of from 1050 ° C to 1080 ° C, in particular in the range of from 1060 ° C to 1070 ° C, preferably around 1060 ° C for one to five hours, preferably two to four hours and more preferably two hours become.
  • the aging annealing may be followed by a defined cooling at a cooling rate of 20 ° C. per minute and more up to a temperature in the range from 500 ° C. to 700 ° C., in particular 600 ° C.
  • heat treatments to detect cracks or soldering attachments to the base component, as well as machining the base component and / or attachments.
  • heat treatments or thermomechanical treatments can be carried out in which the temperature load for the base component or the component does not exceed the temperature of 1100 ° C.
  • repair soldering may be performed prior to aging annealing.
  • the nickel base superalloy may be any suitable nickel base superalloy, such as Inconel 713 (Inconel is a trade name of Special Metals Corporation) or MAR-M-247 (MAR-M-247 is a trademark of Martin Marietta).
  • FIG. 13 shows a flowchart for a repair process of integrated vane rings, with correspondingly provided, integrated vane rings being provided in step 1.
  • step 2 which may be performed alternatively or in addition to step 1, integrated vane rings are also provided, however, for example, newly made by casting and hot isostatic pressing.
  • step 3 the components are subjected to a thermocyclic heat treatment in order to be able to detect cracks possibly present in the components.
  • thermal cycling in the temperature range of up to 1080 ° C for ten minutes to go through. If no cracks are detected for the used, integrated guide blade rings, they are immediately subjected to the treatment according to method step 6, which will be described below.
  • the flowchart of FIG. 1 clearly shows that the precipitation annealing is performed in step 5 at an early stage in the machining process and before two further processing steps before completion of the component, so that a standardized aging annealing can be used.
  • FIG. 2 FIG. 12 shows another example of a repair process which provides in step 8 vanes and blades which after fabrication by casting and hot isostatic pressing in step 9 are subjected to aging annealing at 1060 ° C. for two hours.
  • step 9 Only after the aging annealing in step 9 is a thermocycling treatment carried out at 1080 ° C +/- 14 ° C for seven to twenty minutes in step 10 to make penetration tests.
  • step 11 a honeycomb seal is then soldered again at a temperature of 1060 ° C. in a period of 10 minutes.
  • Such an inner ring 106 is disposed at a vane ring of a stator of a turbomachine at the radially inner end of the vanes 102 opposite to the shaft, as shown in FIG Fig. 3 you can see.
  • the stator ring 106 disposed at the radially inner end of the vane 102 has a honeycomb seal 107 which engages with sealing fins 104 of the rotor to seal the gap between the shaft 100 and the vane 102, thus avoiding flow losses.
  • the stator ring 106 which may be formed as an integrated vane ring, may be manufactured or repaired according to the invention.
  • stator ring 106 is to be regarded as a basic component, for example, and accordingly, the honeycomb seal 107 constitutes an attachment which can be soldered onto the stator ring 106 after aging annealing.
  • the axis of rotation 105 of the turbomachine is in Fig. 3 also shown.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13194500.8A 2013-11-26 2013-11-26 Procédé de fabrication et de réparation de composants d'une turbomachine à partir de superalliages à base de nickel Withdrawn EP2876172A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13194500.8A EP2876172A1 (fr) 2013-11-26 2013-11-26 Procédé de fabrication et de réparation de composants d'une turbomachine à partir de superalliages à base de nickel

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13194500.8A EP2876172A1 (fr) 2013-11-26 2013-11-26 Procédé de fabrication et de réparation de composants d'une turbomachine à partir de superalliages à base de nickel

Publications (1)

Publication Number Publication Date
EP2876172A1 true EP2876172A1 (fr) 2015-05-27

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP13194500.8A Withdrawn EP2876172A1 (fr) 2013-11-26 2013-11-26 Procédé de fabrication et de réparation de composants d'une turbomachine à partir de superalliages à base de nickel

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EP (1) EP2876172A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112182779A (zh) * 2020-10-29 2021-01-05 同济大学 一种基于模拟退火算法的汽油机在线标定方法
CN113600950A (zh) * 2021-07-14 2021-11-05 北京科技大学 一种gh4738合金强度稳定性提升的多次钎焊及热处理工艺

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB674723A (en) * 1949-02-17 1952-07-02 Rolls Royce Improvements relating to processes of manufacturing engineering parts from heat resisting alloys
EP1258312A2 (fr) * 2001-05-15 2002-11-20 United Technologies Corporation Procédé de réparation d'articles en superalliage monocristallin à base de nickel
EP1605074A1 (fr) * 2004-06-11 2005-12-14 Kabushiki Kaisha Toshiba Méthode de réparation par traitment thermique d'une pièce usée d'une turbine à gaz
DE69923115T2 (de) * 1998-06-30 2005-12-29 Howmet Research Corp., Whitehall Wärmebehandlungsverfahren für Superlegierung auf Nickelbasis vor dem Schweissen
DE102005058324A1 (de) * 2005-12-07 2007-06-14 Mtu Aero Engines Gmbh Verfahren zum Herstellen eines Einlaufbelags
EP2407565A1 (fr) * 2010-07-12 2012-01-18 Rolls-Royce plc Procédé pour améliorer les propriétés mécaniques d'un composant

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB674723A (en) * 1949-02-17 1952-07-02 Rolls Royce Improvements relating to processes of manufacturing engineering parts from heat resisting alloys
DE69923115T2 (de) * 1998-06-30 2005-12-29 Howmet Research Corp., Whitehall Wärmebehandlungsverfahren für Superlegierung auf Nickelbasis vor dem Schweissen
EP1258312A2 (fr) * 2001-05-15 2002-11-20 United Technologies Corporation Procédé de réparation d'articles en superalliage monocristallin à base de nickel
EP1605074A1 (fr) * 2004-06-11 2005-12-14 Kabushiki Kaisha Toshiba Méthode de réparation par traitment thermique d'une pièce usée d'une turbine à gaz
DE102005058324A1 (de) * 2005-12-07 2007-06-14 Mtu Aero Engines Gmbh Verfahren zum Herstellen eines Einlaufbelags
EP2407565A1 (fr) * 2010-07-12 2012-01-18 Rolls-Royce plc Procédé pour améliorer les propriétés mécaniques d'un composant

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112182779A (zh) * 2020-10-29 2021-01-05 同济大学 一种基于模拟退火算法的汽油机在线标定方法
CN112182779B (zh) * 2020-10-29 2023-08-29 同济大学 一种基于模拟退火算法的汽油机在线标定方法
CN113600950A (zh) * 2021-07-14 2021-11-05 北京科技大学 一种gh4738合金强度稳定性提升的多次钎焊及热处理工艺

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