EP1702498B1 - Method for heating components - Google Patents

Method for heating components 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
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EP
European Patent Office
Prior art keywords
energy
machining region
static
heating
laser
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EP04802922.7A
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German (de)
French (fr)
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EP1702498A1 (en
Inventor
Erwin Bayer
Wolfgang Becker
Bernd Stimper
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MTU Aero Engines AG
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MTU Aero Engines AG
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    • 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.

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  • 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)

Description

Die Erfindung betrifft ein Verfahren zur Erwärmung von Bauteilen vor und/oder während und/oder nach einer weiteren Bearbeitung derselben.The invention relates to a method for heating components before and / or during and / or after further processing thereof.

Bauteile, wie zum Beispiel Turbinenschaufeln von Gasturbinen, müssen bei der Produktion bzw. Instandhaltung oder Reparatur derselben zur Durchführung verschiedenster Bearbeitungsverfahren erwärmt werden. Diese Erwärmung wird auch als Vorwärmung bezeichnet. Auch ist es üblich Gasturbinenbauteile im Anschluss an ein Bearbeitungsverfahren im Sinne einer Wärmebehandlung zu erwärmen.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.

Bei der Instandhaltung von Turbinenschaufeln kommt zum Beispiel das sogenannte Auftragschweißen zur Anwendung. Im Zusammenhang mit dem Auftragschweißen ist die Vorwärmung eines Bearbeitungsbereichs bzw. Schweißbereichs der zu schweißenden Turbinenschaufeln auf eine gewünschte Prozesstemperatur erforderlich. Nur dann, wenn die zu schweißende Turbinenschaufel zumindest am Bearbeitungsbereich auf die Prozesstemperatur erwärmt worden ist und während des Auftragschweißens auf der gewünschten Prozesstemperatur gehalten wird, kann ein zuverlässiges Auftragschweißen durchgeführt werden.In the maintenance of turbine blades, for example, so-called build-up welding is used. In the context of 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.

Nach dem Stand der Technik werden zur Erwärmung bzw. zur Vorwärmung von Bauteilen sogenannte induktive Systeme verwendet. Bei solchen induktiven Systemen kann es sich zum Beispiel um Spulen handeln, die auf Grundlage induktiver Energieeinbringung das Bauteil erwärmen. Die Erwärmung bzw. Vorwärmung von Bauteilen mittels induktiver Systeme verfügt über den Nachteil, dass sich bei der Erwärmung bzw. Vorwärmung hohe Temperaturtoleranzen von bis zu 50°C am zu erwärmenden Bauteil einstellen können. Eine solch ungenaue Temperaturverteilung am zu erwärmenden Bauteil ist nachteilig. Weiterhin verbrauchen derartige induktive Systeme sehr viel Energie. Ein weiterer Nachteil induktiver Systeme liegt darin, dass sich bei der Erwärmung bzw. Vorwärmung im Inneren des Bauteils höhere Temperaturen einstellen können als an der Oberfläche des Bauteils. Dies kann zu Beschädigungen am Bauteil führen.According to the prior art so-called 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. Furthermore, such 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.

Das Dokument EP-A-0 836 905 offenbart ein Verfahren zur temperaturgeregelten Oberflächenbehandlung von Werkstückoberflächen mittels Laserstrahlung, die von mehreren Laserdioden erzeugt und in Form mehrerer Energiestrahlen auf den Behandlungsbereich gerichtet wird. Dabei erfolgt eine gerichtete Relativbewegung zwischen den zu einer Einheit gebündelten Laserdioden und der Werkstückoberfläche.The document 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.

Hiervon ausgehend liegt der vorliegenden Erfindung das Problem zu Grunde, ein neuartiges Verfahren zur Erwärmung von Bauteilen zu schaffen, welches eine besonderes gute und homogene Erwärmung ermöglicht.On this basis, 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.

Dieses Problem wird durch ein Verfahren mit den Merkmalen des Patentanspruchs 1 gelöst. Dabei wird der Bearbeitungsbereich zur Erwärmung von mehreren Laserquellen bestrahlt, wobei jede Laserquelle einen Energiestrahl derart auf den Bearbeitungsbereich richtet, dass jede Laserquelle jeweils einen Energiefleck auf dem Bearbeitungsbereich erzeugt, die zusammen den Bearbeitungsbereich erwärmen. Erfindungsgemäß erzeugt jede der Laserquellen einen statischen oder quasistatischen Energiefleck auf dem Bearbeitungsbereich, derart, dass die Position des jeweiligen Energieflecks auf dem Bearbeitungsbereich statisch oder quasistatisch ist. Hierdurch lassen sich Probleme, die bei der induktiven Erwärmung auftreten, vermeiden. Weiterhin können Schwierigkeiten, die sich bei bewegten Energieflecken infolge der Bewegung der Laserquelle einstellen können, vermieden werden.This problem is solved by a method having the features of claim 1. In this case, 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. According to the invention, 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.

Nach einer vorteilhaften Ausgestaltung der Erfindung wird jeder Laserquelle eine Temperaturmesseinrichtung zugeordnet, welche die von der jeweiligen Laserquelle bzw. dem Energiefleck der jeweiligen Laserquelle bewirkte Erwärmung des Bearbeitungsbereichs misst und mit einem entsprechenden Temperatur-Sollwert vergleicht, wobei abhängig hiervon für jede der Laserquellen individuell die Strahlungsleistung des jeweiligen Energiestrahls festgelegt wird. Hierdurch sind optimale Voraussetzungen gegen, um die Erwärmung des Bauteils bzw. Bearbeitungsbereichs an sich ändernde Bauteilquerschnitte anzupassen.According to an advantageous embodiment of the invention, 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. As a result, optimal conditions are in order to adapt to the heating of the component or processing area to changing component cross-sections.

Vorzugsweise erzeugt jede der Laserquellen einen quasistatischen Energiefleck auf dem Bearbeitungsbereich, derart, dass die Position des jeweiligen Energieflecks auf dem Bearbeitungsbereich sich maximal zwischen den jeweils benachbarten Energieflecken verändert, um so den Übergangsbereich zwischen zwei benachbarten Energieflecken zu erwärmen. Hierdurch lässt sich eine noch homogenere Erwärmung des Bearbeitungsbereichs bei gleichzeitiger Vermeidung der Probleme bewegter Systeme erzielen.Preferably, 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.

Bevorzugte Weiterbildungen der Erfindung ergeben sich aus den abhängigen Unteransprüchen und der nachfolgenden Beschreibung. Ausführungsbeispiele der Erfindung werden, ohne hierauf beschränkt zu sein, an Hand der Zeichnung näher erläutert. Dabei zeigen:

Fig. 1
eine stark schematisierte Anordnung mit einem zu erwärmenden Bauteil im Querschnitt zur Verdeutlichung einer ersten Ausführungsform des erfindungsgemäßen Verfahrens;
Fig. 2
eine stark schematisierte Anordnung mit dem zu erwärmenden Bauteil in Seitenansicht zur weiteren Verdeutlichung der ersten Ausführungsform des erfindungsgemäßen Verfahrens; und
Fig. 3
eine stark schematisierte Anordnung mit einem zu erwärmenden Bauteil im Querschnitt zur Verdeutlichung einer zweiten Ausführungsform des erfindungsgemäßen Verfahrens.
Preferred embodiments of the invention will become apparent from the dependent subclaims and the following description. Embodiments of the invention will be described, without being limited thereto, with reference to the drawings. Showing:
Fig. 1
a highly schematic arrangement with a component to be heated in cross section to illustrate a first embodiment of the method according to the invention;
Fig. 2
a highly schematic arrangement with the component to be heated in side view to further illustrate the first embodiment of the method according to the invention; and
Fig. 3
a highly schematic arrangement with a component to be heated in cross section to illustrate a second embodiment of the method according to the invention.

Nachfolgend wird das erfindungsgemäße Verfahren zur Erwärmung bzw. Vorwärmung von Bauteilen an der Vorwärmung einer Turbinenschaufel einer Gasturbine unter Bezugnahme auf Fig. 1 bis 3 im Detail beschrieben.Hereinafter, the method according to the invention for heating or preheating components on the preheating of a turbine blade of a gas turbine with reference to Fig. 1 to 3 described in detail.

Fig. 1 zeigt stark schematisiert eine Turbinenschaufel 10 einer Hochdruckturbine eines Flugtriebwerks im Querschnitt, nämlich durch ein Schaufelblatt 11 der Turbinenschaufel 10. Fig. 2 zeigt die Turbinenschaufel 10 in Seitenansicht, wobei ein sich an das Schaufelblatt 11 anschließender Schaufelfuß mit der Bezugsziffer 12 gekennzeichnet ist. Es liegt im Sinne der hier vorliegenden Erfindung, die Turbinenschaufel 10 der Hochdruckturbine vor und/oder während und/oder nach einer weiteren Bearbeitung derselben zu erwärmen, nämlich an einem in Fig. 2 gezeigten Bearbeitungsbereich 13 des Schaufelblatts 11. Fig. 1 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

Im Sinne der hier vorliegenden Erfindung wird die Turbinenschaufel 10 zur Erwärmung des Bearbeitungsbereichs 13 im Sinne der Fig. 1 und 2 von einer Seite her von mehreren Laserquellen bestrahlt, wobei jede der nicht-dargestellten Laserquellen einen Energiestrahl 14 auf den Bearbeitungsbereich 13 der Turbinenschaufel 10 richtet. Fig. 1 zeigt insgesamt sieben derartige Energiestrahlen 14. Die Energiestrahlen 14 erzeugen auf der Turbinenschaufel 10, nämlich im Bearbeitungsbereich 13 derselben, jeweils einen Energiefleck 15. Die Energieflecke 15 erwärmen zusammen den Bearbeitungsbereich 13 der Turbinenschaufel 10. Die Energieflecke 15 sind punktförmig bzw. kreisförmig.For the purposes of the present invention, the turbine blade 10 for heating the processing area 13 in the sense of Fig. 1 and 2 irradiated from one side by a plurality of laser sources, wherein each of the non-illustrated laser sources directs an energy beam 14 on the processing area 13 of the turbine blade 10. 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.

Im Sinne der hier vorliegenden Erfindung erzeugen die nicht-dargestellten Laserquellen im Bearbeitungsbereich 13 der Turbinenschaufel 10 statische oder quasistatische Energieflecke 15. Unter einem statischen Energiefleck ist zu verstehen, dass die Position des jeweiligen Energieflecks im Bearbeitungsbereich 13 statisch ist, sich also nicht verändert. Bei einem quasistatischen Energiefleck ist hingegen eine geringfügige Bewegung desselben möglich.For the purposes of the present invention, 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.

Nach einer ersten Alternative der hier vorliegenden Erfindung erzeugen die Laserquelle statische Energieflecke, d.h. dass sich die Position der jeweiligen Energieflecke 15 im Bearbeitungsbereich 13 nicht verändert. Wird der Abstand zwischen derart statischen Energieflecken gering genug gewählt, so lässt sich eine homogene Erwärmung des gesamten Bearbeitungsbereichs 13 erzielen.According to a first alternative of the present invention, 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.

Nach einer Alternative der hier vorliegenden Erfindung erzeugen die Laserquellen quasistatische Energieflecke 15 im Bearbeitungsbereich 13. Bei einem quasistatischen Energiefleck 15 ist eine geringfügige Bewegung desselben innerhalb des Bearbeitungsbereichs 13 zulässig, wobei sich eine Position eines Energieflecks 15 maximal zwischen den jeweils unmittelbar benachbarten Energieflecken 15 verändert. Hierdurch lässt sich eine noch homogenere Erwärmung des Bearbeitungsbereichs 13 erzielen, nämlich vorzugsweise im Übergangsbereich 18 zwischen benachbarten Energieflecken 15.According to an alternative of the present invention, the laser sources generate quasi-static energy leaks 15 in the processing area 13. In 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.

Jeder nicht-dargestellten Lasereinrichtung ist eine nicht-dargestellte Temperaturmesseinrichtung zugeordnet. Jede der Temperaturmesseinrichtungen misst bzw. erfasst die von der jeweiligen Laserquelle bzw. die von dem jeweiligen Energiefleck 15 bewirkte Erwärmung des Bearbeitungsbereichs 13 der Turbinenschaufeln 10. In einer ebenfalls nicht-dargestellten Steuerungseinrichtung werden nun die von jeder der Temperaturmesseinrichtungen ermittelten Temperatur-Istwerte mit einem entsprechenden Temperatur-Sollwerten verglichen. Jeder Lasereinrichtung bzw. jedem von der jeweiligen Lasereinrichtung erzeugten Energiefleck ist demnach ein separater Temperatur-Sollwert zugeordnet. Auf Basis dieses Temperatur-Sollwerts wird für jede Lasereinrichtung die Strahlungsleistung des jeweiligen Energiestrahls 14 und damit die Leistung des jeweiligen Energieflecks 15 individuell angepasst. Hierbei lässt sich im Beareitungsbereich 13 ein vordefiniertes Temperaturprofil exakt einstellen. Des weiteren kann auf diese Art und Weise dem sich ändernden Querschnitt der Turbinenschaufel 10 entlang des Bearbeitungsbereichs 13 Rechnung getragen werden. So zeigt nämlich Fig. 1, dass sich das Querschnittsprofil der Turbinenschaufel 10 zwischen zwei Kanten 16 und 17 deutlich verändert. Insofern kann mit der hier vorliegenden Erfindung die Strahlungsleistung auf den sich über den Bearbeitungsbereich 13 verändernden Querschnitt der Turbinenschaufel 10 leicht und sicher angepasst werden.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. In a control device, likewise not shown, 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. On the basis of this temperature target value, 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. Furthermore, in this way, the changing cross-section of the turbine blade 10 along the processing area 13 can be taken into account. So shows Fig. 1 in that the cross-sectional profile of the turbine blade 10 changes significantly between two edges 16 and 17. In this respect, with the present invention, the radiation power can be easily and safely adapted to the changing over the processing area 13 cross-section of the turbine blade 10.

Im Ausführungsbeispiel der Fig. 1 und 2 wird der Bearbeitungsbereich 13 der Turbinenschaufel 10 von einer Seite her über nicht-dargestellte Laserquellen erwärmt. Im Unterschied hierzu ist es möglich, den Bearbeitungsbereich 13 von zwei Seiten her zu erwärmen, wie dies im Ausführungsbeispiel der Fig. 3 dargestellt ist. So werden im Ausführungsbeispiel der Fig. 3 von beiden Seiten der Turbinenschaufel 10 Energiestrahlen 14 auf den Bearbeitungsbereich 13 derselben gerichtet. Hierdurch lässt sich die Erwärmungsqualität nochmals verbessern. In the embodiment of Fig. 1 and 2 For example , the processing area 13 of the turbine blade 10 is heated from one side via non- illustrated laser sources . In contrast, it is possible to erwär men the processing area 13 from two sides , as in the embodiment of the Fig. 3 is shown. Thus, in the exemplary embodiment of the Fig. 3 From both sides of the turbine blade 10 energy beams 14 directed to the processing area 13 thereof. This makes it possible to improve the quality of heating again.

Im Sinne der hier vorliegenden Erfindung werden als Laserquellen vorzugsweise Diodenlaser verwendet. Die Verwendung von Diodenlasern, die eine lineare Leistungsabgabe bei linearer Ansteuerung aufweisen, ist besonders bevorzugt. Diodenlaser ermöglichen Strahlungsenergie mit einer eng begrenzten, spezifischen Wellenlänge auf die zu erwärmende Turbinenschaufeln 10 bzw. den Bearbeitungsbereich 13 zu richten. Die definierte Wellenlänge der Diodenlaser ermöglicht eine gute sowie definierte Begrenzung der Energieausbreitung und eine präzise Erwärmung der Turbinenschaufel 10 bzw. des Bearbeitungsbereichs 13. Alternativ können jedoch auch andere Laserquellen zur Erwärmung verwendet werden, beispielhaft seien hier CO2-Laser, Nd-Laser oder YAG-Laser genannt.For the purposes of the present invention, 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. Alternatively, however, other laser sources can be used for heating, for example, here CO 2 laser, Nd laser or YAG Called laser.

Die Erwärmung sowie Messung der Erwärmung an der Turbinenschaufel 10 erfolgt berührungslos. Zur berührungslosen Temperaturmessung kommen insbesondere Pyrometer zum Einsatz. Wie bereits erwähnt, ist jeder Laserquelle dann ein Pyrometer zugeordnet, um die von der entsprechenden Laserquelle bewirkte Erwärmung zu erfassen.The heating and measurement of the heating on the turbine blade 10 takes place without contact. For non-contact temperature measurement in particular pyrometers for use. As already mentioned, each laser source is then associated with a pyrometer to detect the heating caused by the corresponding laser source.

Die Erfindung findet bevorzugt Verwendung bei der Erwärmung von Turbinenschaufeln 10 im Zusammenhang mit einer Reparatur bzw. Instandsetzung derselben. Eine Bearbeitung, bei der eine Erwärmung der Turbinenschaufel erforderlich ist, ist zum Beispiel das sogenannte Auftragsschweißen. Der Einsatz des erfindungsgemäßen Verfahrens ist jedoch nicht auf Reparaturarbeiten an Turbinenschaufeln begrenzt. Vielmehr kann es auch bei anderen Bauteilen einer Gasturbine, zum Beispiel bei der Reparatur eines Gehäuses, zum Einsatz kommen.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. However, 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.

Claims (7)

  1. Method for heating a machining region (13) of a component (10), in particular of a gas-turbine component, before and/or during and/or after machining the component at the machining region, wherein the machining region (13) is irradiated in order to be heated by a plurality of laser sources, and wherein each laser source directs an energy beam (14) at the machining region in such a way that each laser source generates a respective energy spot (15) on the machining region (13), the energy spots (15) together heating the machining region,
    characterised in that
    each of the laser sources generates a static or quasi-static energy spot (15) on the machining region in such a way that the position of the respective energy spot on the machining region (13) is static or quasi-static.
  2. Method according to claim 1,
    characterised in that
    associated with each laser source there is a temperature-measuring device which measures the heating of the machining region (13) brought about by the respective laser source or the energy spot (15) of the respective laser source.
  3. Method according to claim 2,
    characterised in that
    an actual temperature value determined in this manner by each temperature-measuring device is compared with a corresponding desired temperature value of the corresponding laser source, and in that in dependence thereon the radiation power of the respective energy beam (14) is individually determined for each of the laser sources.
  4. Method according to one or more of claims 1 to 3,
    characterised in that
    the heating and the temperature-measurement are effected in a contactless manner.
  5. Method according to one or more of claims 1 to 4,
    characterised in that
    each of the laser sources generates a static energy spot (15) on the machining region in such a way that the position of the respective energy spot (15) on the machining region (13) is static or invariable.
  6. Method according to one or more of claims 1 to 4,
    characterised in that
    each of the laser sources generates a quasi-static energy spot (15) on the machining region (13) in such a way that the position of the respective energy spot (15) on the machining region varies maximally between the respectively adjacent energy spots in order to heat the transition region (18) between two adjacent energy spots (15).
  7. Method according to one or more of claims 1 to 6,
    characterised in that
    diode lasers are used as the laser sources.
EP04802922.7A 2004-01-08 2004-12-11 Method for heating components Not-in-force EP1702498B1 (en)

Applications Claiming Priority (2)

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DE102004001276A DE102004001276A1 (en) 2004-01-08 2004-01-08 Method for heating components
PCT/DE2004/002717 WO2005067350A1 (en) 2004-01-08 2004-12-11 Method for heating components

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EP1702498A1 EP1702498A1 (en) 2006-09-20
EP1702498B1 true EP1702498B1 (en) 2013-07-31

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Also Published As

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

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