EP0513407A1 - Method of manufacture of a turbine blade - Google Patents

Method of manufacture of a turbine blade Download PDF

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Publication number
EP0513407A1
EP0513407A1 EP91107707A EP91107707A EP0513407A1 EP 0513407 A1 EP0513407 A1 EP 0513407A1 EP 91107707 A EP91107707 A EP 91107707A EP 91107707 A EP91107707 A EP 91107707A EP 0513407 A1 EP0513407 A1 EP 0513407A1
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EP
European Patent Office
Prior art keywords
blade
hot
cast body
turbine blade
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
EP91107707A
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German (de)
French (fr)
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EP0513407B1 (en
Inventor
Mohamed Dr. Nazmy
Markus Staubli
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 Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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Publication date
Priority to DE59106047T priority Critical patent/DE59106047D1/en
Application filed by ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Priority to EP91107707A priority patent/EP0513407B1/en
Priority to JP4116420A priority patent/JPH07166802A/en
Priority to CA002068504A priority patent/CA2068504A1/en
Priority to US07/880,036 priority patent/US5299353A/en
Priority to PL92294502A priority patent/PL168950B1/en
Priority to SU925011799A priority patent/RU2066253C1/en
Priority to KR1019920008009A priority patent/KR920021236A/en
Priority to CN92103469A priority patent/CN1025358C/en
Publication of EP0513407A1 publication Critical patent/EP0513407A1/en
Application granted granted Critical
Publication of EP0513407B1 publication Critical patent/EP0513407B1/en
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C14/00—Alloys based on titanium
    • 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
    • C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
    • C22F1/18—High-melting or refractory metals or alloys based thereon
    • C22F1/183—High-melting or refractory metals or alloys based thereon of titanium 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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49318—Repairing or disassembling
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making

Definitions

  • the invention is based on a turbine blade, which contains a blade body, blade root and, if appropriate, a cast body comprising an alloy on the basis of a gamma-titanium aluminide containing dopant.
  • the invention is also based on a method for producing such a turbine blade.
  • Gamma titanium aluminides have properties which favor their use as a material for turbine blades exposed to high temperatures. This includes, among other things, their low density compared to commonly used superalloys, which is more than twice as large, for example, with Ni superalloys.
  • a turbine blade of the type mentioned at the beginning is known from G. Sauthoff, "Intermetallic phases", materials between metal and ceramic, magazine new materials 1/89, pp. 15-19.
  • the material of this turbine blade has one comparatively high heat resistance, but the ductility of this material at room temperature is comparatively low, so that damage to parts of the turbine blade that are subjected to bending stresses cannot be excluded with certainty.
  • the invention is based on the object of specifying a turbine blade of the type mentioned which is distinguished by a long service life when used in a turbine operated at medium and high temperatures, and at the same time a way to point, which makes it possible to manufacture such a turbine blade in a simple and suitable for mass production.
  • the turbine blade according to the invention is distinguished from comparable turbine blades according to the prior art by a long service life even when subjected to high stress, in particular on bending. This is made possible by the fact that the differently stressed parts of the turbine blade have differently specified modifications of the gamma titanium aluminide used as the material. It proves to be particularly advantageous from a manufacturing point of view that the turbine blade is merely molded out of an inexpensive, one-piece cast body. In addition, this method can be easily implemented for mass production through the use of common means, such as casting molds, ovens, presses and mechanical and electrochemical processing devices.
  • the annealed, hot-isostatically pressed, thermoformed and heat-treated cast body shown in the figure has the essential material and shape properties of the turbine blade according to the invention. It contains an elongated airfoil 1, a blade root 2 formed on one end of the airfoil 1 and a blade cover band 3 formed on the opposite end of the airfoil.
  • the turbine blade according to the invention is produced from this cast body by slight machining.
  • the material-lifting processing essentially consists in adapting the dimensions of the cast body to the desired dimensions of the turbine blade. In the case of the blade root 2 and the blade cover band 3, this is advantageously done by grinding and polishing.
  • the fastening grooves 4 of the blade root 2 which are shown in dashed lines in the figure, can also be formed.
  • the airfoil is preferably adapted to the desired airfoil shape by electrochemical processing.
  • the cast body shown in the figure consists essentially of an alloy based on a dopant-containing gamma-titanium aluminide. At least in Parts of the airfoil 1, this alloy is in the form of a material with a coarse-grained structure and with a structure that leads to high tensile and creep strength. At least in parts of the blade root 2 and the blade shroud 3, the alloy is in the form of a material with a fine-grained structure and with a higher ductility than the material in the blade 1. This ensures a long service life for the airfoil.
  • the turbine blade according to the invention can be used advantageously at medium and high temperatures, i. H. Use at temperatures between 200 and 1000 ° C, especially in gas turbines and in compressors.
  • the blade cover sheet 3 may be present or omitted.
  • protective gas such as argon, or under vacuum
  • Suitable alloys are gamma titanium aluminides in which at least one or more of the elements B, Co, Cr, Ge, Hf, Mn, Mo, Nb, Pd, Si, Ta, V, Y, W and Zr are contained as dopant.
  • the amount of dopant added is preferably 0.5 to 8 atomic percent.
  • the melt is poured into a mold corresponding to the turbine blade to be manufactured.
  • the cast body formed can then advantageously be annealed at approximately 1100 ° C. for 10 hours in an argon atmosphere, for example, and cooled to room temperature.
  • the cast skin and scale layer are then removed by, for example, removing a surface layer approximately 1 mm thick by mechanical or chemical means.
  • the descaled cast body is inserted into a suitable capsule made of soft carbon steel and the latter welded gas-tight.
  • the encapsulated cast body is then hot isostatically pressed and cooled at a temperature of 1260 ° C. for 3 hours under a pressure of 120 MPa.
  • the annealing of the alloy should be carried out at temperatures between 1000 and 1100 ° C for at least half and for a maximum of thirty hours.
  • hot isostatic pressing which should advantageously be carried out at temperatures between 1200 and 1300 ° C and a pressure between 100 and 150 MPa for at least one and at most five hours.
  • thermoforming of the part of the annealed and hot-isostatically pressed cast body corresponding to the blade root 2 and / or the blade shroud 3, forming the material with a fine-grained structure, and heat treating at least the part of the annealed and hot corresponding to the airfoil 1 -isostatically pressed cast body before or after the isothermal thermoforming to form the material with a coarse-grained structure.
  • the annealed and hot-isostatically pressed cast body is heat-treated prior to the isothermal thermoforming to form the material with a coarse-grained structure
  • the part of the annealed and hot-isostatically pressed cast body after the isothermal hot-working is heat-treated to form the material with a coarse-grained structure. It has proven to be expedient to heat the annealed and hot-isostatically pressed cast body to the temperature required for the hot forming at a rate of between 10 and 50 ° C./min before the isothermal thermoforming.
  • the parts to be thermoformed such as the blade root 2 and possibly also the blade cover band 3
  • the parts to be thermoformed can first be kneaded in the forging press by upsetting in at least two directions transverse to the longitudinal axis of the turbine blade and then pressed to the final shape.
  • the finished pressed parts have a fine-grained structure with one compared to that in the airfoil located material on increased ductility.
  • the tensile strength or the ductility of the material in the airfoil 1 is 390 MPa or 0.3% and in the blade root 2 and in the blade cover band 3 is 370 MPa or 1.3%.
  • the cast body is heated to 1100 ° C., for example, at a heating rate of 10 to 50 ° C./min and is kept at this temperature.
  • the blade root 2 and / or the blade shroud 3 are forged at 1100 ° C. in accordance with the previously described method.
  • the forged parts also have a fine-grained structure with a higher ductility than the material in the airfoil 1.
  • the airfoil is then heated to a temperature of 1200 to 1400 ° C. and, depending on the heating temperature and alloy composition, heat-treated for between 0.5 and 25 hours. When cooling, another 1 to 5 h heat treatment can be carried out. After the heat treatment, the airfoil predominantly has a coarse-grained structure and a structure that leads to high tensile and creep resistance. In such a turbine blade manufactured in this way, the tensile strength and ductility of the material in the airfoil 1 or in the blade root 2 and in the blade shroud 3 have almost the same values as in the turbine blade produced by the previously described method.

Abstract

Turbine blade consisting of a casting made of an alloy based on a dopant-containing gamma titanium aluminide and comprising a blade vane (1), a blade root (2) and, if required, a shroud band (3). <??>At least in some parts of the blade vane (1), the material has a coarse-grained structure which gives a high tensile strength and long-time rupture strength. In certain parts of the blade root (2) and/or the shroud band (3) which may be provided, the material has a fine-grained structure with a higher ductility than the material in the blade root (1). <IMAGE>

Description

TECHNISCHES GEBIETTECHNICAL AREA

Bei der Erfindung wird ausgegangen von einer Turbinenschaufel, enthaltend einen Schaufelblatt, Schaufelfuss und gegebenenfalls Schaufeldeckband aufweisenden Gusskörper aus einer Legierung auf der Basis eines dotierstoffhaltigen gamma-Titanaluminids. Die Erfindung geht ferner aus von einem Verfahren, um eine solche Turbinenschaufel herzustellen.The invention is based on a turbine blade, which contains a blade body, blade root and, if appropriate, a cast body comprising an alloy on the basis of a gamma-titanium aluminide containing dopant. The invention is also based on a method for producing such a turbine blade.

STAND DER TECHNIKSTATE OF THE ART

Gamma-Titanaluminide haben Eigenschaften, welche deren Einsatz als Werkstoff für hohen Temperaturen ausgesetzte Turbinenschaufeln begünstigen. Dazu gehört unter anderem ihre gegenüber üblicherweise verwendeten Superlegierungen niedrige Dichte, die beispielsweise bei Ni-Superlegierungen mehr als doppelt so gross ist.Gamma titanium aluminides have properties which favor their use as a material for turbine blades exposed to high temperatures. This includes, among other things, their low density compared to commonly used superalloys, which is more than twice as large, for example, with Ni superalloys.

Aus G. Sauthoff, "Intermetallische Phasen", Werkstoffe zwischen Metall und Keramik, Magazin neue Werkstoffe 1/89, S. 15-19 ist eine Turbinenschaufel der eingangs genannten Art bekannt. Der Werkstoff dieser Turbinenschaufel weist eine vergleichsweise hohe Warmfestigkeit auf, jedoch ist die Duktilität dieses Werkstoffs bei Raumtemperatur vergleichsweise gering, so dass an biegebeanspruchten Teilen der Turbinenschaufel Beschädigungen nicht mit Sicherheit auszuschliessen sind.A turbine blade of the type mentioned at the beginning is known from G. Sauthoff, "Intermetallic phases", materials between metal and ceramic, magazine new materials 1/89, pp. 15-19. The material of this turbine blade has one comparatively high heat resistance, but the ductility of this material at room temperature is comparatively low, so that damage to parts of the turbine blade that are subjected to bending stresses cannot be excluded with certainty.

KURZE DARSTELLUNG DER ERFINDUNGSUMMARY OF THE INVENTION

Der Erfindung, wie sie in den Patentansprüchen 1 und 4 angegeben ist, liegt die Aufgabe zugrunde, eine Turbinenschaufel der eingangs genannten Art anzugeben, welche sich bei Einsatz in einer bei mittleren und hohen Temperaturen betriebenen Turbine durch eine hohe Lebensdauer auszeichnet, und gleichzeitig einen Weg zu weisen, der es ermöglicht, eine solche Turbinenschaufel in einfacher und für eine Massenfertigung geeigneten Weise herzustellen.The invention, as specified in claims 1 and 4, is based on the object of specifying a turbine blade of the type mentioned which is distinguished by a long service life when used in a turbine operated at medium and high temperatures, and at the same time a way to point, which makes it possible to manufacture such a turbine blade in a simple and suitable for mass production.

Die Turbinenschaufel nach der Erfindung zeichnet sich gegenüber vergleichbaren Turbinenschaufeln nach dem Stand der Technik selbst bei hoher, insbesondere auf Biegung erfolgender, Beanspruchung durch eine hohe Lebensdauer aus. Dies ist dadurch ermöglicht, dass die unterschiedlich beanspruchten Teilen der Turbinenschaufel unterschiedlich spezifizierte Modifikationen des als Werkstoff verwendeten gamma-Titanaluminids aufweisen. Hierbei erweist es sich fertigungstechnisch von besonderem Vorteil, dass die Turbinenschaufel lediglich aus einem preisgünstig herzustellenden, einstückigen Gusskörper herausgeformt wird. Zudem kann dieses Verfahren durch den Einsatz gängiger Mittel, wie Giessformen, Öfen, Pressen und mechanische und elektrochemische Bearbeitungsvorrichtungen, in einfacher Weise für eine Massenfertigung ausgebildet werden.The turbine blade according to the invention is distinguished from comparable turbine blades according to the prior art by a long service life even when subjected to high stress, in particular on bending. This is made possible by the fact that the differently stressed parts of the turbine blade have differently specified modifications of the gamma titanium aluminide used as the material. It proves to be particularly advantageous from a manufacturing point of view that the turbine blade is merely molded out of an inexpensive, one-piece cast body. In addition, this method can be easily implemented for mass production through the use of common means, such as casting molds, ovens, presses and mechanical and electrochemical processing devices.

Bevorzugte Ausführungsbeispiele der Erfindung und die damit erzielbaren Vorteile werden nachfolgend anhand einer Zeichnung näher erläutert.Preferred exemplary embodiments of the invention and the advantages which can be achieved thereby are explained in more detail below with reference to a drawing.

KURZE BESCHREIBUNG DER ZEICHNUNGBRIEF DESCRIPTION OF THE DRAWING

In der einzigen Figur ist ein geglühter, heiss-isostatisch gepresster, warmverformter und wärmebehandelter Gusskörper dargestellt, aus dem durch materialabhebende Bearbeitung die Turbinenschaufel nach der Erfindung hergestellt wird.In the single figure, an annealed, hot-isostatically pressed, thermoformed and heat-treated cast body is shown, from which the turbine blade according to the invention is produced by material-removing processing.

WEGE ZUR AUSFÜHRUNG DER ERFINDUNGWAYS OF CARRYING OUT THE INVENTION

Der in der Figur dargestellte geglühte, heiss-isostatisch gepresste, warmverformte und wärmebehandelte Gusskörper weist die wesentlichen Material-und Formeigenschaften der Turbinenschaufel nach der Erfindung auf. Er enthält ein langgestrecktes Schaufelblatt 1, einen am einen Ende des Schaufelblattes 1 angeformten Schaufelfuss 2 sowie ein am entgegengesetzten Ende des Schaufelblattes angeformtes Schaufeldeckband 3. Aus diesem Gusskörper wird durch geringfügige materialabhebende Bearbeitung die Turbinenschaufel nach der Erfindung hergestellt. Die materialabhebende Bearbeitung besteht im wesentlichen in einer Anpassung der Abmessungen des Gusskörpers an die erwünschten Abmessungen der Turbinenschaufel. Beim Schaufelfuss 2 und beim Schaufeldeckband 3 erfolgt dies mit Vorteil durch Schleifen und Polieren. Hierbei können zugleich auch die in der Figur gestrichelt dargestellten tannenbaumartig angeordneten Befestigungsnuten 4 des Schaufelfusses 2 gebildet werden. Das Schaufelblatt wird vorzugsweise durch elektrochemische Bearbeitung an die erwünschte Schaufelblattform angepasst.The annealed, hot-isostatically pressed, thermoformed and heat-treated cast body shown in the figure has the essential material and shape properties of the turbine blade according to the invention. It contains an elongated airfoil 1, a blade root 2 formed on one end of the airfoil 1 and a blade cover band 3 formed on the opposite end of the airfoil. The turbine blade according to the invention is produced from this cast body by slight machining. The material-lifting processing essentially consists in adapting the dimensions of the cast body to the desired dimensions of the turbine blade. In the case of the blade root 2 and the blade cover band 3, this is advantageously done by grinding and polishing. At the same time, the fastening grooves 4 of the blade root 2, which are shown in dashed lines in the figure, can also be formed. The airfoil is preferably adapted to the desired airfoil shape by electrochemical processing.

Der in der Figur dargestellte Gusskörper besteht im wesentlichen aus einer Legierung auf der Basis eines dotierstoffhaltigen gamma-Titanaluminids. Zumindest in Teilen des Schaufelblattes 1 liegt diese Legierung in Form eines Werkstoffs mit grobkörniger Struktur und mit einem zu hoher Zug- und Zeitstandfestigkeit führendem Gefüge vor. Zumindest in Teilen des Schaufelfusses 2 und des Schaufeldeckbandes 3 liegt die Legierung in Form eines Werkstoffs mit feinkörniger Struktur und mit einer gegenüber dem im Schaufelblatt 1 befindlichen Werkstoff erhöhten Duktilität vor. Hierdurch wird eine hohe Lebensdauer des Schaufelblattes erreicht. Dies ist zum einen dadurch bedingt, dass das bei Betrieb der Turbine auf hohen Temperaturen befindliche Schaufelblatt aufgrund seiner grobkörnigen Struktur und seines Gefüges eine gute Zug- und Zeitstandfestigkeit aufweist, wohingegen seine bei tiefen Temperaturen vorhandene geringe Duktilität ohne Bedeutung ist. Zum anderen ist dies auch dadurch bedingt, dass sich bei Betrieb der Turbine der Schaufelfuss und das Schaufeldeckband auf vergleichsweise tiefen Temperaturen befinden und dann aufgrund ihrer feinkörnigen Struktur und ihres Gefüges eine verglichen mit dem im Schaufelblatt vorgesehenen Material eine hohe Duktilität aufweisen. Vom Schaufelfuss und vom Schaufeldeckband können so über einen grossen Zeitraum vergleichsweise grosse Torsions- und Biegekräfte aufgenommen werden, ohne dass Spannungsrisse gebildet werden.The cast body shown in the figure consists essentially of an alloy based on a dopant-containing gamma-titanium aluminide. At least in Parts of the airfoil 1, this alloy is in the form of a material with a coarse-grained structure and with a structure that leads to high tensile and creep strength. At least in parts of the blade root 2 and the blade shroud 3, the alloy is in the form of a material with a fine-grained structure and with a higher ductility than the material in the blade 1. This ensures a long service life for the airfoil. On the one hand, this is due to the fact that the blade, which is in operation at high temperatures, has good tensile and creep resistance due to its coarse-grained structure and structure, whereas its low ductility, which is present at low temperatures, is of no importance. On the other hand, this is also due to the fact that when the turbine is in operation, the blade root and the blade shroud are at comparatively low temperatures and then, owing to their fine-grained structure and structure, have a high ductility compared to the material provided in the blade. Comparatively large torsional and bending forces can be absorbed by the blade root and the blade shroud over a long period of time without stress cracks being formed.

Die Turbinenschaufel nach der Erfindung lässt sich mit Vorteil bei mittleren und hohen Temperaturen, d. h. bei Temperaturen zwischen 200 und 1000°C, insbesondere in Gasturbinen und in Verdichtern, einsetzen. Je nach Ausführungsform der Gasturbine oder des Verdichters kann hierbei das Schaufeldeckblatt 3 vorhanden sein oder entfallen.The turbine blade according to the invention can be used advantageously at medium and high temperatures, i. H. Use at temperatures between 200 and 1000 ° C, especially in gas turbines and in compressors. Depending on the embodiment of the gas turbine or the compressor, the blade cover sheet 3 may be present or omitted.

Der Gusskörper gemäss der Figur wird wie folgt hergestellt: Unter Schutzgas, wie etwa Argon, oder unter Vakuum wird in einem Induktionsofen folgende Legierung auf der Basis eines gamma-Titanaluminids mit Chrom als Dotierstoff erschmolzen:
Al = 48 At.-%
Cr = 3 At.-%
Ti = Rest.The cast body according to the figure is produced as follows: In protective gas, such as argon, or under vacuum, in the following alloy was melted in an induction furnace on the basis of a gamma titanium aluminide with chromium as dopant:
Al = 48 at .-%
Cr = 3 at .-%
Ti = rest.

Andere geeignete Legierungen sind gamma-Titanaluminide in denen als Dotierstoff mindestens eines oder mehrere der Elemente B, Co, Cr, Ge, Hf, Mn, Mo, Nb, Pd, Si, Ta, V, Y, W sowie Zr enthalten sind. Die Menge an zugesetztem Dotierstoff beträgt vorzugsweise 0,5 bis 8 Atomprozent.Other suitable alloys are gamma titanium aluminides in which at least one or more of the elements B, Co, Cr, Ge, Hf, Mn, Mo, Nb, Pd, Si, Ta, V, Y, W and Zr are contained as dopant. The amount of dopant added is preferably 0.5 to 8 atomic percent.

Die Schmelze wird in einer der herzustellenden Turbinenschaufel entsprechenden Gussform abgegossen. Der gebildete Gusskörper kann hierauf mit Vorteil zu Zwecken seiner Homogenisierung bei ca. 1100°C während beispielsweise 10h in Argonatmosphäre geglüht und auf Raumtemperatur abgekühlt werden. Sodann werden Gusshaut und Zunderschicht entfernt, indem beispielsweise eine Oberflächenschicht von ca. 1 mm Dicke auf mechanischem oder chemischem Wege abgetragen wird. Der entzunderte Gusskörper wird in eine passende Kapsel aus weichem Kohlenstoffstahl eingeschoben und letztere gasdicht verschweisst. Der eingekapselte Gusskörper wird nun bei einer Temperatur von 1260°C während 3 h unter einem Druck von 120 MPa heiss-isostatisch gepresst und abgekühlt.The melt is poured into a mold corresponding to the turbine blade to be manufactured. The cast body formed can then advantageously be annealed at approximately 1100 ° C. for 10 hours in an argon atmosphere, for example, and cooled to room temperature. The cast skin and scale layer are then removed by, for example, removing a surface layer approximately 1 mm thick by mechanical or chemical means. The descaled cast body is inserted into a suitable capsule made of soft carbon steel and the latter welded gas-tight. The encapsulated cast body is then hot isostatically pressed and cooled at a temperature of 1260 ° C. for 3 hours under a pressure of 120 MPa.

Das Glühen der Legierung sollte je nach Zusammensetzung bei Temperaturen zwischen 1000 und 1100 °C während mindestens einer halben und während höchstens dreissig Stunden durchgeführt werden. Entsprechendes gilt für das heiss-isostatische Pressen, welches mit Vorteil bei Temperaturen zwischen 1200 und 1300°C und einem Druck zwischen 100 und 150 MPa mindestens eine und höchstens fünf Stunden lang durchgeführt werden sollte.Depending on the composition, the annealing of the alloy should be carried out at temperatures between 1000 and 1100 ° C for at least half and for a maximum of thirty hours. The same applies to hot isostatic pressing, which should advantageously be carried out at temperatures between 1200 and 1300 ° C and a pressure between 100 and 150 MPa for at least one and at most five hours.

Anschliessend erfolgt ein ein- bis mehrmaliges isothermes Warmverformen des dem Schaufelfuss 2 und/oder dem Schaufeldeckband 3 entsprechenden Teils des geglühten und heiss-isostatisch gepressten Gusskörpers unter Bildung des Werkstoffs mit feinkörniger Struktur und eine Wärmebehandlung zumindest des dem Schaufelblatt 1 entsprechenden Teils des geglühten und heiss-isostatisch gepressten Gusskörpers vor oder nach dem isothermen Warmverformen unter Bildung des Werkstoffs mit grobkörniger Struktur.This is followed by one or more isothermal thermoforming of the part of the annealed and hot-isostatically pressed cast body corresponding to the blade root 2 and / or the blade shroud 3, forming the material with a fine-grained structure, and heat treating at least the part of the annealed and hot corresponding to the airfoil 1 -isostatically pressed cast body before or after the isothermal thermoforming to form the material with a coarse-grained structure.

Hierbei können mit Vorteil zwei Wege beschritten werden. Beim Beschreiten des ersten Weges wird der geglühte und heiss-isostatisch gepresste Gusskörper vor dem isothermen Warmverformen unter Bildung des Werkstoffs mit grobkörniger Struktur wärmebehandelt, wohingegen beim Beschreiten des zweiten Weges der das Schaufelblatt umfassende Teil des geglühten und heiss-isostatisch gepressten Gusskörpers nach dem isothermen Warmverformen unter Bildung des Werkstoffs mit grobkörniger Struktur wärmebehandelt wird.Es hat sich als zweckmässig erwiesen, vor dem isothermen Warmverformen den geglühten und heiss-isostatisch gepressten Gusskörper mit einer Geschwindigkeit zwischen 10 und 50°C/min auf die zum Warmverformen benötigte Temperatur zu erwärmen.There are two ways to do this. When the first route is followed, the annealed and hot-isostatically pressed cast body is heat-treated prior to the isothermal thermoforming to form the material with a coarse-grained structure, whereas when the second route is followed, the part of the annealed and hot-isostatically pressed cast body after the isothermal hot-working is heat-treated to form the material with a coarse-grained structure. It has proven to be expedient to heat the annealed and hot-isostatically pressed cast body to the temperature required for the hot forming at a rate of between 10 and 50 ° C./min before the isothermal thermoforming.

Beim Beschreiten des ersten Weges wird der Gusskörper auf eine Temperatur von 1200 bis 1400°C aufgeheizt und je nach Aufheiztemperatur und Legierungszusammensetzung zwischen 0,5 und 25h wärmebehandelt. Beim Abkühlen kann eine weitere 1 bis 5h dauernde Wärmebehandlung durchgeführt werden. Nach der Wärmebehandlung weist der Gusskörper grobkörnige Struktur und ein zu hoher Zug- und Zeitstandfestigkeit führendes Gefüge auf. Der wärmebehandelte Gusskörper wird auf 1100°C erwärmt und auf dieser Temperatur gehalten. Sodann werden der Schaufelfuss 2 und/oder das Schaufeldeckband 3 bei 1100°C isotherm geschmiedet. Das verwendete Werkzeug ist vorzugsweise eine Schmiedepresse, bestehend etwa aus einer Molybdänlegierung mit dem Handelsnamen TZM mit folgender Zusammensetzung:
Ti = 0,5 Gew.-%
Zr = 0,1 Gew.-%
C = 0,02 Gew.-%
Mo = Rest
Die Fliessgrenze des zu schmiedenden Werkstoffs beträgt ca. 260 MPa bei 1100°C . Die Umformung wird durch Stauchen bis zu einer Verformung ε = 1,3 erreicht, wobei

Figure imgb0001

ho =
ursprüngliche Höhe des Werkstücks und
h =
Höhe des Werkstücks nach Umformung
bedeuten. Die lineare Verformungsgeschwindigkeit (Stempelgeschwindigkeit der Schmiedepresse) beträgt bei Beginn des Schmiedeprozesses 0,1 mm/s. Der Anfangsdruck der Schmiedepresse liegt bei ca. 300 MPa.When the first route is followed, the cast body is heated to a temperature of 1200 to 1400 ° C and, depending on the heating temperature and alloy composition, heat-treated for between 0.5 and 25 hours. When cooling, another 1 to 5 h heat treatment can be carried out. After the heat treatment, the cast body has a coarse-grained structure and a structure that leads to high tensile and creep strength. The heat-treated cast body is heated to 1100 ° C. and kept at this temperature. Then the blade root 2 and / or that Blade cover band 3 isothermally forged at 1100 ° C. The tool used is preferably a forging press, consisting for example of a molybdenum alloy with the trade name TZM with the following composition:
Ti = 0.5% by weight
Zr = 0.1% by weight
C = 0.02% by weight
Mo = rest
The yield point of the material to be forged is approx. 260 MPa at 1100 ° C. The deformation is achieved by upsetting up to a deformation ε = 1.3, whereby
Figure imgb0001
h o =
original height of the workpiece and
h =
Workpiece height after forming
mean. The linear deformation speed (stamping speed of the forging press) is 0.1 mm / s at the start of the forging process. The initial pressure of the forging press is approximately 300 MPa.

In Abhängigkeit von der Legierungszusammemsetzung kann die Warmverformung bei Temperaturen zwischen zwischen 1050 und 1200°C mit einer zwischen 5 · 10⁻⁵s⁻¹ und 10⁻²s⁻¹ gelegenen Verformungsgeschwindigkeit bis zu einer Verformung ε = 1,6 durchgeführt werden. Hierbei können mit Vorteil die warmzuverformenden Teile, wie der Schaufelfuss 2 und gegebenenfalls auch das Schaufeldeckband 3, in der Schmiedepresse durch Stauchen in mindestens zwei quer zur Längsachse der Turbinenschaufel verlaufenden Richtungen zunächst geknetet und dann zur Endform fertiggepresst werden. Die fertiggepressten Teile weisen feinkörnige Struktur mit einer gegenüber dem im Schaufelblatt befindlichen Werkstoff erhöhten Duktilität auf. Bei der wie vorstehend beschrieben hergestellten Turbinenschaufel liegen die Zugfestigkeit bzw. die Duktilität des Werkstoffs im Schaufelblatt 1 bei 390 MPa bzw. bei 0,3% und im Schaufelfuss 2 sowie im Schaufeldeckband 3 bei 370 MPa bzw. 1,3%.Depending on the alloy composition, the hot deformation can be carried out at temperatures between 1050 and 1200 ° C with a deformation rate between 5 · 10⁻⁵s⁻¹ and 10⁻²s⁻¹ up to a deformation ε = 1.6. Advantageously, the parts to be thermoformed, such as the blade root 2 and possibly also the blade cover band 3, can first be kneaded in the forging press by upsetting in at least two directions transverse to the longitudinal axis of the turbine blade and then pressed to the final shape. The finished pressed parts have a fine-grained structure with one compared to that in the airfoil located material on increased ductility. In the turbine blade manufactured as described above, the tensile strength or the ductility of the material in the airfoil 1 is 390 MPa or 0.3% and in the blade root 2 and in the blade cover band 3 is 370 MPa or 1.3%.

Beim Beschreiten des zweiten Weges wird der Gusskörper beispielsweise mit einer Aufheizgeschwindigkeit von 10 bis 50°C/min auf 1100°C erwärmt und auf dieser Temperatur gehalten. Sodann werden der Schaufelfuss 2 und/oder das Schaufeldeckband 3 bei 1100°C entsprechend dem zuvor beschriebenen Verfahren isotherm geschmiedet. Die fertiggeschmiedeten Teile weisen ebenfalls feinkörnige Struktur mit einer gegenüber dem im Schaufelblatt 1 befindlichen Werkstoff erhöhten Duktilität auf.When the second path is followed, the cast body is heated to 1100 ° C., for example, at a heating rate of 10 to 50 ° C./min and is kept at this temperature. Then the blade root 2 and / or the blade shroud 3 are forged at 1100 ° C. in accordance with the previously described method. The forged parts also have a fine-grained structure with a higher ductility than the material in the airfoil 1.

Mittels einer um das Schaufelblatt 1 angebrachten Induktionsspule wird das Schaufelblatt sodann auf eine Temperatur von 12oo bis 1400°C aufgeheizt und je nach Aufheiztemperatur und Legierungszusammensetzung zwischen 0,5 und 25h wärmebehandelt. Beim Abkühlen kann eine weitere 1 bis 5h dauernde Wärmebehandlung durchgeführt werden. Nach der Wärmebehandlung weist das Schaufelblatt überwiegend grobkörnige Struktur und ein zu hoher Zug- und Zeitstandfestigkeit führendes Gefüge auf. Bei einer solchermassen hergestellten Turbinenschaufel weisen Zugfestigkeit und Duktilität des Werkstoffs im Schaufelblatt 1 bzw. im Schaufelfuss 2 sowie im Schaufeldeckband 3 nahezu die gleichen Werte auf wie bei der nach dem zuvor beschriebenen Verfahren hergestellten Turbinenschaufel.By means of an induction coil fitted around the airfoil 1, the airfoil is then heated to a temperature of 1200 to 1400 ° C. and, depending on the heating temperature and alloy composition, heat-treated for between 0.5 and 25 hours. When cooling, another 1 to 5 h heat treatment can be carried out. After the heat treatment, the airfoil predominantly has a coarse-grained structure and a structure that leads to high tensile and creep resistance. In such a turbine blade manufactured in this way, the tensile strength and ductility of the material in the airfoil 1 or in the blade root 2 and in the blade shroud 3 have almost the same values as in the turbine blade produced by the previously described method.

Claims (15)

Turbinenschaufel, enthaltend einen Schaufelblatt (1), Schaufelfuss (2) und gegebenenfalls Schaufeldeckband (3) aufweisenden Gusskörper aus einer Legierung auf der Basis eines dotierstoffhaltigen gamma-Titanaluminids, dadurch gekennzeichnet, dass die Legierung zumindest in Teilen des Schaufelblattes (1) in Form eines Werkstoff mit grobkörniger Struktur und mit einem zu hoher Zug- und Zeitstandfestigkeit führendem Gefüge vorliegt und zumindest in Teilen des Schaufelfusses (2) und/oder des gegebenenfalls vorgesehenen Schaufeldeckbandes (3) in Form eines Werkstoffs mit feinkörniger Struktur und mit einer gegenüber dem im Schaufelblatt (1) befindlichen Werkstoff erhöhten Duktilität.Turbine blade containing a blade (1), blade root (2) and optionally blade cover band (3) having a cast body made of an alloy based on a dopant-containing gamma-titanium aluminide, characterized in that the alloy is in the form of at least part of the blade (1) Material with a coarse-grained structure and with a structure that leads to a high tensile and creep resistance and is present at least in parts of the blade root (2) and / or the blade shroud (3) that may be provided in the form of a material with a fine-grained structure and with one compared to that in the blade ( 1) located material increased ductility. Turbinenschaufel nach Anspruch 1, dadurch gekennzeichnet, dass als Dotierstoff mindestens eines oder mehrere der Elemente B, Co, Cr, Ge, Hf, Mn, Mo, Nb, Pd, Si, Ta, V, Y, W sowie Zr in der Legierung enthalten sind.Turbine blade according to claim 1, characterized in that contain at least one or more of the elements B, Co, Cr, Ge, Hf, Mn, Mo, Nb, Pd, Si, Ta, V, Y, W and Zr as dopant in the alloy are. Turbinenschaufel nach Anspruch 2, dadurch gekennzeichnet, dass die Legierung mindestens 0,5 und höchstens 8 Atomprozent Dotierstoff aufweist.Turbine blade according to claim 2, characterized in that the alloy has at least 0.5 and at most 8 atomic percent dopant. Verfahren zur Herstellung der Turbinenschaufel nach Patentanspruch 1, dadurch gekennzeichnet, dass folgende Verfahrensschritten durchgeführt werden: - Erschmelzen der Legierung, - Vergiessen der Schmelze zu einem Gusskörper von der Form der Turbinenschaufel, - Heiss-isostatisches Fressen des Gusskörpers, - Ein- bis mehrmaliges isothermes Warmverformen des dem Schaufelfuss (2) und/oder dem Schaufeldeckband (3) entsprechenden Teils des heiss-isostatisch gepressten Gusskörpers unter Bildung des Werkstoffs mit feinkörniger Struktur, - Wärmebehandeln zumindest des dem Schaufelblatt (1) entsprechenden Teils des heiss-isostatisch gepressten Gusskörpers vor oder nach dem isothermen Warmverformen unter Bildung des Werkstoffs mit grobkörniger Struktur, und - Materialabhebendes Bearbeiten des heiss-isostatisch gepressten, warmverformten und wärmebehandelten Gusskörpers zur Turbinenschaufel. A method for producing the turbine blade according to claim 1, characterized in that the following method steps are carried out: Melting the alloy, Pouring the melt into a cast body in the shape of the turbine blade, - hot isostatic seizure of the cast body, - One or more isothermal hot forming of the part of the hot-isostatically pressed cast body corresponding to the blade root (2) and / or the blade shroud (3), forming the material with a fine-grained structure, - Heat treatment of at least that part of the hot-isostatically pressed cast body corresponding to the airfoil (1) before or after the isothermal thermoforming to form the material with a coarse-grained structure, and - Material-lifting processing of the hot-isostatically pressed, thermoformed and heat-treated cast body for the turbine blade. Verfahren nach Anspruch 4, dadurch gekennzeichnet, dass der heiss-isostatisch gepresste Gusskörper vor dem isothermen Warmverformen unter Bildung des Werkstoffs mit grobkörniger Struktur wärmebehandelt wird.A method according to claim 4, characterized in that the hot-isostatically pressed cast body is heat-treated before the isothermal thermoforming to form the material with a coarse-grained structure. Verfahren nach Anspruch 4, dadurch gekennzeichnet, dass der das Schaufelblatt (1) umfassende Teil des heiss-isostatisch gepressten Gusskörpers nach dem isothermen Warmverformen unter Bildung des Werkstoffs mit grobkörniger Struktur wärmebehandelt wird.Method according to claim 4, characterized in that the part of the hot-isostatically pressed cast body comprising the airfoil (1) is heat-treated after the isothermal thermoforming to form the material with a coarse-grained structure. Verfahren nach Anspruch 6, dadurch gekennzeichnet, dass die Wärmebehandlung mit einer Induktionsspule ausgeführt wird.A method according to claim 6, characterized in that the heat treatment is carried out with an induction coil. Verfahren nach einem der Ansprüche 4 bis 7, dadurch gekennzeichnet, dass die Wärmebehandlung zwischen 1200 und 1400°C durchgeführt wird.Method according to one of claims 4 to 7, characterized in that the heat treatment is carried out between 1200 and 1400 ° C. Verfahren nach Anspruch 8, dadurch gekennzeichnet, dass nachfolgend eine weitere Wärmebehandlung zwischen 800 und 1000°C durchgeführt wird.A method according to claim 8, characterized in that a further heat treatment between 800 and 1000 ° C is carried out subsequently. Verfahren nach einem der Ansprüche 4 bis 9, dadurch gekennzeichnet, dass das Warmverformen zwischen 1050 und 1200°C mit einer zwischen 5 · 10⁻⁵s⁻¹ und 10⁻²s⁻¹ gelegenen Verformungsgeschwindigkeit bis zu einer Verformung ε = 1,6 durchgeführt wird, wobei
Figure imgb0002
 ho =   ursprüngliche Höhe des Werkstücks und h =   Höhe des Werkstücks nach Umformung bedeuten. Method according to one of claims 4 to 9, characterized in that the hot forming between 1050 and 1200 ° C is carried out with a deformation rate between 5 · 10⁻⁵s⁻¹ and 10⁻²s⁻¹ up to a deformation ε = 1.6 , in which
Figure imgb0002
 h o = original height of the workpiece and h = height of the workpiece after forming. Verfahren nach Anspruch 10, dadurch gekennzeichnet, dass das Warmverformen in einer Schmiedepresse durchgeführt wird.A method according to claim 10, characterized in that the hot forming is carried out in a forging press. Verfahren nach Anspruch 11, dadurch gekennzeichnet, dass die warmzuverformenden Teile in der Schmiedepresse durch Stauchen in mindestens zwei quer zur Längsachse der Turbinenschaufel verlaufenden Richtungen zunächst geknetet und dann zur Endform fertiggepresst werden.A method according to claim 11, characterized in that the parts to be thermoformed are first kneaded in the forging press by upsetting in at least two directions transverse to the longitudinal axis of the turbine blade and then pressed to the final shape. Verfahren nach einem der Ansprüche 4 bis 12, dadurch gekennzeichnet, dass der heiss-isostatisch gepresste Gusskörper vor dem isothermen Warmverformen auf Raumtemperatur abgekühlt und nachfolgend mit einer Geschwindigkeit zwischen 10 und 50°C/min auf die beim Warmverformen eingestellte Temperatur erwärmt wird.Method according to one of claims 4 to 12, characterized in that the hot-isostatically pressed cast body is cooled to room temperature before the isothermal thermoforming and is subsequently heated to the temperature set during thermoforming at a speed between 10 and 50 ° C / min. Verfahren nach einem der Ansprüche 4 bis 13, dadurch gekennzeichnet, dass der Gusskörper vor dem Warmverformen und dem Wärmebehandeln bei Temperaturen zwischen 1000 und 1100°C homogenisiert wird.Method according to one of claims 4 to 13, characterized in that the cast body is homogenized at temperatures between 1000 and 1100 ° C before the thermoforming and the heat treatment. Verfahren nach einem der Ansprüche 4 bis 14, dadurch gekennzeichnet, dass das heiss-isostatische Pressen bei Temperaturen zwischen 1200 und 1300°C und einem Druck zwischen 100 und 150 MPa durchgeführt wird.Method according to one of claims 4 to 14, characterized in that the hot isostatic pressing is carried out at temperatures between 1200 and 1300 ° C and a pressure between 100 and 150 MPa.
EP91107707A 1991-05-13 1991-05-13 Method of manufacture of a turbine blade Expired - Lifetime EP0513407B1 (en)

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DE59106047T DE59106047D1 (en) 1991-05-13 1991-05-13 Process for manufacturing a turbine blade.
CA002068504A CA2068504A1 (en) 1991-05-13 1992-05-08 Turbine blade and process for producing this turbine blade
US07/880,036 US5299353A (en) 1991-05-13 1992-05-08 Turbine blade and process for producing this turbine blade
JP4116420A JPH07166802A (en) 1991-05-13 1992-05-08 Turbine blade and manufacture of turbine blade thereof
PL92294502A PL168950B1 (en) 1991-05-13 1992-05-11 Turbine blade and method of making same
SU925011799A RU2066253C1 (en) 1991-05-13 1992-05-12 Method of making turbine blades
KR1019920008009A KR920021236A (en) 1991-05-13 1992-05-12 Turbine Blades and Manufacturing Method Thereof
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US5299353A (en) 1994-04-05
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PL294502A1 (en) 1992-11-30
KR920021236A (en) 1992-12-18
CN1066706A (en) 1992-12-02
DE59106047D1 (en) 1995-08-24
PL168950B1 (en) 1996-05-31
CA2068504A1 (en) 1992-11-14
CN1025358C (en) 1994-07-06
EP0513407B1 (en) 1995-07-19

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