EP1702498B1 - Procede pour chauffer des pieces - Google Patents

Procede pour chauffer des pieces Download PDF

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Publication number
EP1702498B1
EP1702498B1 EP04802922.7A EP04802922A EP1702498B1 EP 1702498 B1 EP1702498 B1 EP 1702498B1 EP 04802922 A EP04802922 A EP 04802922A EP 1702498 B1 EP1702498 B1 EP 1702498B1
Authority
EP
European Patent Office
Prior art keywords
energy
machining region
static
heating
laser
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.)
Not-in-force
Application number
EP04802922.7A
Other languages
German (de)
English (en)
Other versions
EP1702498A1 (fr
Inventor
Erwin Bayer
Wolfgang Becker
Bernd Stimper
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
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Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP1702498A1 publication Critical patent/EP1702498A1/fr
Application granted granted Critical
Publication of EP1702498B1 publication Critical patent/EP1702498B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
    • C21D1/34—Methods of heating
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B3/00—Ohmic-resistance heating
    • H05B3/0033—Heating devices using lamps
    • H05B3/0038—Heating devices using lamps for industrial applications
    • 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
    • C21D2221/00—Treating localised areas of an article
    • 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
    • C21D2261/00—Machining or cutting being involved

Definitions

  • the invention relates to a method for heating components before and / or during and / or after further processing thereof.
  • Components such as turbine blades of gas turbines, must be heated in the production or maintenance or repair of the same for performing a variety of machining processes. This warming is also known as preheating. It is also customary to heat gas turbine components following a machining process in the sense of a heat treatment.
  • build-up welding In the maintenance of turbine blades, for example, so-called build-up welding is used.
  • build-up welding the preheating of a machining area or welding area of the turbine blades to be welded to a desired process temperature is required. Only when the turbine blade to be welded has been heated to the process temperature at least at the processing area and is maintained at the desired process temperature during build-up welding, reliable build-up welding can be performed.
  • inductive systems are used for heating or for preheating of components.
  • Such inductive systems may be, for example, coils that heat the component based on inductive energy input.
  • the heating or preheating of components by means of inductive systems has the disadvantage that during the heating or preheating high temperature tolerances of up to 50 ° C can be set on the component to be heated. Such an inaccurate temperature distribution on the component to be heated is disadvantageous.
  • inductive systems consume a great deal of energy.
  • Another disadvantage of inductive systems is that higher temperatures can occur in the interior of the component during heating or preheating than at the surface of the component. This can lead to damage to the component.
  • EP-A-0 836 905 discloses a method for temperature-controlled surface treatment of workpiece surfaces by means of laser radiation, which is generated by a plurality of laser diodes and directed in the form of a plurality of energy beams on the treatment area. In this case, a directed relative movement takes place between the laser diodes bundled into a unit and the workpiece surface.
  • the present invention is based on the problem to provide a novel method for heating of components, which allows a particularly good and homogeneous heating.
  • the processing area for heating is irradiated by a plurality of laser sources, each laser source directing an energy beam onto the processing area such that each laser source generates an energy leak on the processing area which together heat the processing area.
  • each of the laser sources generates a static or quasistatic energy leak on the processing area, such that the position of the respective energy leak on the processing area is static or quasi-static. This can avoid problems that occur during inductive heating. Furthermore, difficulties that may arise with moving energy debris due to the movement of the laser source can be avoided.
  • each laser source is associated with a temperature measuring device which measures the heating of the processing area caused by the respective laser source or the energy leak of the respective laser source and compares it with a corresponding temperature setpoint, depending on the radiation power individually for each of the laser sources of the respective energy beam is determined.
  • each of the laser sources generates a quasi-static energy leak on the processing area such that the position of the respective energy leak on the processing area varies maximally between the respective adjacent energy spots so as to heat the transition area between two adjacent energy spots. This allows even more homogeneous heating of the processing area while avoiding the problems of moving systems.
  • FIG. 2 is a highly schematic representation of a turbine blade 10 of a high-pressure turbine of an aircraft engine in cross-section, namely by an airfoil 11 of the turbine blade 10.
  • Fig. 2 shows the turbine blade 10 in side view, wherein a subsequent to the blade 11 blade root is denoted by the reference numeral 12. It is within the meaning of the present invention to heat the turbine blade 10 of the high-pressure turbine before and / or during and / or after a further processing thereof, namely at an in Fig. 2 shown processing area 13 of the airfoil 11th
  • Fig. 1 7 shows a total of seven such energy beams 14.
  • the energy beams 14 each generate an energy leak 15 on the turbine blade 10, namely in the processing area 13 thereof.
  • the energy leaks 15 together heat the processing area 13 of the turbine blade 10.
  • the energy leaks 15 are punctiform or circular.
  • the non-illustrated laser sources in the processing area 13 of the turbine blade 10 generate static or quasi-static energy leaks 15.
  • a static energy leak means that the position of the respective energy leaks in the processing area 13 is static, ie does not change. In a quasistatic energy leak, however, a slight movement of the same is possible.
  • the laser source generates static energy leaks, i. the position of the respective energy spots 15 in the processing area 13 does not change. If the distance between such static energy spots chosen low enough, so can a homogeneous heating of the entire processing area 13 can be achieved.
  • the laser sources generate quasi-static energy leaks 15 in the processing area 13.
  • a quasistatic energy leak 15 a slight movement of the same within the processing area 13 is permissible, with a position of an energy leak 15 varying maximally between the immediately adjacent energy leaks 15. This makes it possible to achieve an even more homogeneous heating of the processing area 13, namely preferably in the transition area 18 between adjacent energy spots 15.
  • Each non-illustrated laser device is associated with a non-illustrated temperature measuring device.
  • Each of the temperature measuring devices measures or detects the heating of the processing area 13 of the turbine blades 10 caused by the respective energy source 15 or of the respective energy leak 15.
  • the temperature actual values determined by each of the temperature measuring devices are now associated with a corresponding one Temperature setpoints compared.
  • Each laser device or each energy leak generated by the respective laser device is therefore associated with a separate temperature setpoint.
  • the radiation power of the respective energy beam 14 and thus the power of the respective energy leak 15 are individually adapted for each laser device. In this case, a predefined temperature profile can be set exactly in the processing range 13.
  • the changing cross-section of the turbine blade 10 along the processing area 13 can be taken into account.
  • Fig. 1 shows Fig. 1 in that the cross-sectional profile of the turbine blade 10 changes significantly between two edges 16 and 17.
  • the radiation power can be easily and safely adapted to the changing over the processing area 13 cross-section of the turbine blade 10.
  • the processing area 13 of the turbine blade 10 is heated from one side via non- illustrated laser sources .
  • it is possible to erracer men the processing area 13 from two sides as in the embodiment of the Fig. 3 is shown.
  • energy beams 14 directed to the processing area 13 thereof. This makes it possible to improve the quality of heating again.
  • diode lasers are preferably used as laser sources.
  • the use of diode lasers having a linear output linear output is particularly preferred.
  • Diode lasers make it possible to direct radiant energy with a narrow, specific wavelength onto the turbine blades 10 or the processing area 13 to be heated.
  • the defined wavelength of the diode laser allows a good and defined limitation of the energy propagation and a precise heating of the turbine blade 10 and the processing area 13.
  • other laser sources can be used for heating, for example, here CO 2 laser, Nd laser or YAG Called laser.
  • each laser source is then associated with a pyrometer to detect the heating caused by the corresponding laser source.
  • the invention is preferably used in the heating of turbine blades 10 in connection with a repair or repair thereof. Machining in which heating of the turbine blade is required is, for example, so-called build-up welding.
  • the use of the method according to the invention is not limited to repair work on turbine blades. Rather, it can also be used in other components of a gas turbine, for example in the repair of a housing.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Mechanical Engineering (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Laser Beam Processing (AREA)

Claims (7)

  1. Procédé pour chauffer une zone d'usinage (13) d'un composant (10), en particulier d'un composant de turbine à gaz, avant et/ou pendant et/ou après un usinage du composant sur la zone d'usinage, dans lequel on expose la zone d'usinage (13) au rayonnement de plusieurs sources laser pour la chauffer et dans lequel chaque source laser dirige un rayonnement énergétique (14) sur la zone d'usinage de telle manière que chaque source laser produise respectivement une tache d'énergie (15) sur la zone d'usinage (13), dont l'ensemble chauffe la zone d'usinage, caractérisé en ce que chacune des sources laser produit une tache d'énergie statique ou quasi statique (15) sur la zone d'usinage, de telle manière que la position de la tache d'énergie respective sur la zone d'usinage (13) soit statique ou quasi statique.
  2. Procédé selon la revendication 1, caractérisé en ce qu'un dispositif de mesure de température est associé à chaque source laser, lequel mesure le chauffage de la zone d'usinage (13) provoqué par la source laser respective ou par la tache d'énergie (15) de la source d'énergie respective.
  3. Procédé selon la revendication 2, caractérisé en ce que l'on compare une valeur réelle de la température déterminée ainsi par chaque dispositif de mesure de température avec une valeur de consigne de température correspondante de la source laser correspondante, et en ce que, en fonction de cette comparaison, on fixe individuellement pour chacune des sources laser la puissance de rayonnement du rayonnement énergétique respectif (14).
  4. Procédé selon une ou plusieurs des revendications 1 à 3, caractérisé en ce que le chauffage et la mesure de température sont effectués sans contact.
  5. Procédé selon une ou plusieurs des revendications 1 à 4, caractérisé en ce que chacune des sources laser produit une tache d'énergie statique (15) sur la zone d'usinage, de telle manière que la position de la tache d'énergie respective (15) sur la zone d'usinage (13) soit statique ou invariable.
  6. Procédé selon une ou plusieurs des revendications 1 à 4, caractérisé en ce que chacune des sources laser produit une tache d'énergie quasi statique (15) sur la zone d'usinage (13), de telle manière que la position de la tache d'énergie respective (15) sur la zone d'usinage change au maximum entre les taches d'énergie respectivement voisines, afin de chauffer ainsi la zone de transition (18) entre deux taches d'énergie voisines (15).
  7. Procédé selon une ou plusieurs des revendications 1 à 6, caractérisé en ce que l'on utilise des lasers à diode comme sources laser.
EP04802922.7A 2004-01-08 2004-12-11 Procede pour chauffer des pieces Not-in-force EP1702498B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004001276A DE102004001276A1 (de) 2004-01-08 2004-01-08 Verfahren zur Erwärmung von Bauteilen
PCT/DE2004/002717 WO2005067350A1 (fr) 2004-01-08 2004-12-11 Procede pour chauffer des pieces

Publications (2)

Publication Number Publication Date
EP1702498A1 EP1702498A1 (fr) 2006-09-20
EP1702498B1 true EP1702498B1 (fr) 2013-07-31

Family

ID=34716358

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04802922.7A Not-in-force EP1702498B1 (fr) 2004-01-08 2004-12-11 Procede pour chauffer des pieces

Country Status (5)

Country Link
US (1) US8124912B2 (fr)
EP (1) EP1702498B1 (fr)
JP (1) JP4542551B2 (fr)
DE (1) DE102004001276A1 (fr)
WO (1) WO2005067350A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9289854B2 (en) * 2012-09-12 2016-03-22 Siemens Energy, Inc. Automated superalloy laser cladding with 3D imaging weld path control
EP3049212B1 (fr) * 2013-09-24 2023-07-26 IPG Photonics Corporation Procédé de traitement par laser, système de traitement par laser et tête optique capable de dithering
FR3111577B1 (fr) * 2020-06-18 2022-10-07 Safran Chauffage laser pour la fabrication ou la reparation d’aube de turbine

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Also Published As

Publication number Publication date
JP4542551B2 (ja) 2010-09-15
JP2007523285A (ja) 2007-08-16
US20090107968A1 (en) 2009-04-30
EP1702498A1 (fr) 2006-09-20
US8124912B2 (en) 2012-02-28
WO2005067350A1 (fr) 2005-07-21
DE102004001276A1 (de) 2005-08-04

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