EP1818510A1 - Turbine blade, especially for a gas turbine or a steam turbine - Google Patents

Turbine blade, especially for a gas turbine or a steam turbine Download PDF

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Publication number
EP1818510A1
EP1818510A1 EP06002584A EP06002584A EP1818510A1 EP 1818510 A1 EP1818510 A1 EP 1818510A1 EP 06002584 A EP06002584 A EP 06002584A EP 06002584 A EP06002584 A EP 06002584A EP 1818510 A1 EP1818510 A1 EP 1818510A1
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EP
European Patent Office
Prior art keywords
turbine
blade
airfoil
solidification
solidification direction
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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.)
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EP06002584A
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German (de)
French (fr)
Inventor
Ahmad Fathi
Pan Dr. Ying
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Siemens AG
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Siemens AG
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Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP06002584A priority Critical patent/EP1818510A1/en
Publication of EP1818510A1 publication Critical patent/EP1818510A1/en
Withdrawn legal-status Critical Current

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    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D27/00—Treating the metal in the mould while it is molten or ductile ; Pressure or vacuum casting
    • B22D27/04—Influencing the temperature of the metal, e.g. by heating or cooling the mould
    • B22D27/045—Directionally solidified castings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition

Definitions

  • the invention relates to a blade for a turbine, in particular a guide vane of a gas turbine or a steam turbine, with an airfoil, which has a flow inlet edge and a flow outlet edge and is formed from a directionally solidified metallic material having a predetermined solidification direction.
  • the invention further relates to a device for casting the blade.
  • the rotor blades of turbines such as engines of aircraft or gas turbines for power generation in power plants, are exposed, inter alia, high temperatures and heavy mechanical loads. This also applies to the vanes of such turbines, which, due to the hot flowing gases, with which they come into contact, among other things, are exposed to high thermal loads. Accordingly, the materials used to make blades and vanes must have, among other things, high resistance to creep and thermal fatigue in order to realize acceptable fatigue life and operating times.
  • the casting mold of the casting apparatus is usually located in a heated chamber in which the temperature of the casting mold is raised above the melting point of the alloy to be cast.
  • the alloy which is heated to well above the melting point, is filled into the mold through a pouring orifice.
  • a cooling plate which is coupled to the mold at one end of the mold, supplied coolant.
  • the invention has for its object to provide a blade for a gas turbine or a steam turbine, which can withstand high loads, especially high thermal loads.
  • the blade can withstand high loads, especially high thermal loads in the form of temperature gradients, which are directed perpendicular to the longitudinal direction of the airfoil, which would lead to significant material fatigue without the solidification direction formed, which significantly reduces the life or possibly may cause a blade breakage.
  • the invention is particularly advantageous for guide vanes, which are exposed during operation - due to the installation situation in the respective turbine - thermal gradients, which are aligned perpendicular to the solidification direction.
  • the elongated, columnar grain structure forming in the solidification direction during the directional solidification has coarse and thus comparatively large grains which bring about a high creep resistance. Furthermore, since the grain boundaries also run parallel to the selected solidification direction and there are no grain boundaries which reduce the creep resistance and extend perpendicular to the solidification direction, the blade leaf is characterized by high strength in the solidification direction with a high modulus of elasticity.
  • an outer and / or an inner platform are provided.
  • the platforms adjacent the outer and inner ends of the airfoil, which serve to secure the entire airfoil to a housing structure of the turbine, are preferably formed of a fine-grained material. Fine-grained materials are characterized by increased creep at high temperatures, which ultimately results in comparatively high yield strengths for the platform material.
  • thermal load changes in the form of temperature changes is a fine-grained formation of the vane platforms in terms of life the platforms of advantage.
  • a high yield strength of the platform material which occurs as a result of the high temperatures in turbine operation, against the background of the known Wöhler curve, ensures that the platform material does not tire prematurely as a result of the thermal load changes.
  • the adjustment of a desired grain size can be achieved by grain refining alloying elements. Also conceivable is a thermomechanical treatment of the platform material.
  • the blade and the platforms are integrally formed from a cast.
  • the platform material in a casting device designed for this purpose can be impressed with a direction of solidification extending transversely to the longitudinal direction of the blade, which brings about the advantages described above.
  • FIG. 1 shows a schematic representation of a guide vane according to the invention.
  • the figure shows schematically a guide vane 10 according to the invention of a turbine.
  • the vane 10 includes a profiled airfoil 12, an outer platform 14 and an inner platform 16 relative to the mounting position of the vane 10 in the turbine.
  • the profiled airfoil 12 has a flow inlet edge 20 and a flow outlet edge 18.
  • the airfoil 12 is made of a directionally solidified, metallic Material formed, wherein the solidification direction perpendicular to the longitudinal axis (z-direction) of the airfoil 12 (and thus in the X direction) between the flow inlet edge 20 and the flow outlet edge 18 extends.
  • Thermal gradients which act as a result of a corresponding flow of hot gases perpendicular to the longitudinal axis of the airfoil 12, cause a thermal load on the airfoil material, which is oriented in the direction of solidification. Since the airfoil 12 along the solidification direction has a significantly higher resistance to thermal and mechanical loads than a conventionally - ie without a predetermined solidification direction - cast airfoil, the airfoil 12 can be exposed to very high thermal gradient, without causing material fatigue or even comes to the material break.
  • the outer and inner platforms 14, 16 are formed of a fine-grained metallic material which has a high yield strength due to its fine graininess at high temperatures. Fine-grained materials are characterized by an increased creep at high temperatures, resulting in the end relatively high yield strengths for the platform material, with a concomitant high fatigue strength against thermal load changes.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Blade (12) is made from a metallic material which solidifies in a direction perpendicular to the longitudinal direction of the blade. An independent claim is also included for a device for casting a blade.

Description

Die Erfindung betrifft eine Schaufel für eine Turbine, insbesondere eine Leitschaufel einer Gasturbine oder einer Dampfturbine, mit einem Schaufelblatt, das eine Strömungseintrittskante und eine Strömungsaustrittskante aufweist und aus einem gerichtet erstarrten metallischen Material mit einer vorgegebenen Erstarrungsrichtung gebildet ist. Die Erfindung betrifft ferner eine Vorrichtung zum Gießen der Schaufel.The invention relates to a blade for a turbine, in particular a guide vane of a gas turbine or a steam turbine, with an airfoil, which has a flow inlet edge and a flow outlet edge and is formed from a directionally solidified metallic material having a predetermined solidification direction. The invention further relates to a device for casting the blade.

Die Rotorschaufeln von Turbinen, wie Triebswerkturbinen von Flugzeugen oder Gasturbinen zur Energiegewinnung in Kraftwerken, sind unter anderem hohen Temperaturen und starken mechanischen Belastungen ausgesetzt. Dies gilt auch für die Leitschaufeln derartiger Turbinen, die, bedingt durch die heißen strömenden Gase, mit denen sie in Berührung kommen, unter anderem hohen thermischen Belastungen ausgesetzt werden. Die für die Herstellung von Schaufeln und Leitschaufeln verwendeten Materialien müssen demnach unter anderem eine hohe Widerstandsfähigkeit gegenüber dem Kriechen und der thermischen Ermüdung aufweisen, um akzeptable bzw. wirtschaftliche Dauerfestigkeiten und Betriebszeiten zu realisieren.The rotor blades of turbines, such as engines of aircraft or gas turbines for power generation in power plants, are exposed, inter alia, high temperatures and heavy mechanical loads. This also applies to the vanes of such turbines, which, due to the hot flowing gases, with which they come into contact, among other things, are exposed to high thermal loads. Accordingly, the materials used to make blades and vanes must have, among other things, high resistance to creep and thermal fatigue in order to realize acceptable fatigue life and operating times.

Bedingt durch das stetige Bestreben, die Wirkungsgrade von Gas- und Dampfturbinen zu steigern, sind große Anforderungen an die jeweils verwendeten Werkstoffe zu stellen, die sich nur durch Entwicklung neuer Materialien oder Verbesserung bekannter Materialien realisieren lassen. Aus dem Stand der Technik sind eine Vielzahl von Werkstoffen in Form metallischer Legierungen, die für die Herstellung von Turbinenkomponenten, insbesondere für Leitschaufeln und Rotorschaufeln verwendet werden, bekannt.Due to the constant effort to increase the efficiencies of gas and steam turbines, great demands are placed on the materials used in each case, which can be realized only by developing new materials or improving known materials. From the prior art, a variety of materials in the form of metallic alloys, which are used for the production of turbine components, in particular for vanes and rotor blades known.

Zur Verbesserung der Widerstandsfähigkeit dieser Werkstoffe gegenüber den auf sie einwirkenden Belastungen, ist es seit längerem bekannt, einzelne Komponenten einer Turbine, die mittels eines Gießverfahrens hergestellt werden, unter Einbeziehung einer vorgegebenen Erstarrungsrichtung zu gießen. So ist beispielsweise aus der Offenlegungsschrift DE 14 26 378 bekannt, Rotorschaufeln und Leitschaufeln von Gasturbinen in einer Gießvorrichtung zu gießen, mit der ein gerichtetes Erstarren des verwendeten Schaufelmaterials möglich ist.To improve the resistance of these materials to the stresses acting on them, it has long been known to cast individual components of a turbine, which are produced by means of a casting process, involving a predetermined solidification direction. For example, from the published patent application DE 14 26 378 It is known to cast rotor blades and vanes of gas turbines in a casting apparatus with which a directed solidification of the blade material used is possible.

Die Gießform der Gießvorrichtung befindet sich in der Regel in einer geheizten Kammer, in welcher die Temperatur der Gießform über den Schmelzpunkt der zu gießenden Legierung hinaus erhöht wird. Wenn eine geeignete vorgegebene Temperatur erreicht ist, wird die Legierung, welche deutlich über dem Schmelzpunkt erhitzt wird, durch eine Gießöffnung in die Gießform eingefüllt. Zur Ausbildung eines starken Temperaturgefälles in der Gießform wird beispielsweise einer Kühlplatte, die an einem Ende der Gießform an die Gießform gekoppelt ist, Kühlmittel zugeführt. So lässt sich eine gerichtet erstarrte Leitschaufel herstellen, die entlang der Erstarrungsrichtung eine deutlich höhere Widerstandsfähigkeit gegenüber thermischen und mechanischen Belastungen aufweist als eine in üblicherweise gegossene Leitschaufel.The casting mold of the casting apparatus is usually located in a heated chamber in which the temperature of the casting mold is raised above the melting point of the alloy to be cast. When a suitable predetermined temperature is reached, the alloy, which is heated to well above the melting point, is filled into the mold through a pouring orifice. To form a strong temperature gradient in the mold, for example, a cooling plate, which is coupled to the mold at one end of the mold, supplied coolant. Thus, a directionally solidified vane can be produced, which along the solidification direction has a significantly higher resistance to thermal and mechanical loads than a conventionally cast vane.

Der Erfindung liegt die Aufgabe zugrunde, eine Schaufel für eine Gasturbine oder eine Dampfturbine zu schaffen, die hohen Belastungen, insbesondere hohen thermischen Belastungen standhalten kann.The invention has for its object to provide a blade for a gas turbine or a steam turbine, which can withstand high loads, especially high thermal loads.

Diese Aufgabe ist erfindungsgemäß mit der eingangs genannten Schaufel für eine Turbine, insbesondere eine Gasturbine oder Dampfturbine gelöst, bei der sich die Erstarrungsrichtung im Wesentlichen senkrecht zur Längsrichtung des Schaufelblatts, insbesondere über die gesamte Strecke zwischen der Strömungseintrittskante und der Strömungsaustrittskante des Schaufelblatts, erstreckt.This object is achieved according to the invention with the initially mentioned blade for a turbine, in particular a gas turbine or steam turbine, in which the solidification direction extends substantially perpendicular to the longitudinal direction of the blade, in particular over the entire distance between the flow inlet edge and the flow outlet edge of the blade.

Durch eine so erfindungsgemäß gerichtete Erstarrungsrichtung kann das Schaufelblatt hohen Belastungen, insbesondere hohen thermischen Belastungen in Form von Temperaturgradienten, die senkrecht zur Längsrichtung des Schaufelblatts gerichtet sind, standhalten, die ohne die ausgebildete Erstarrungsrichtung zu einer deutlichen Materialermüdung führen würden, welche eine deutliche Verringerung der Lebensdauer oder gegebenenfalls einen Schaufelbruch zur Folge haben kann.By so inventively directed solidification direction, the blade can withstand high loads, especially high thermal loads in the form of temperature gradients, which are directed perpendicular to the longitudinal direction of the airfoil, which would lead to significant material fatigue without the solidification direction formed, which significantly reduces the life or possibly may cause a blade breakage.

Die Erfindung ist insbesondere für Leitschaufeln von Vorteil, die im Betrieb - infolge der Einbausituation in der jeweiligen Turbine - thermischen Gradienten ausgesetzt werden, die senkrecht zur Erstarrungsrichtung ausgerichtet sind.The invention is particularly advantageous for guide vanes, which are exposed during operation - due to the installation situation in the respective turbine - thermal gradients, which are aligned perpendicular to the solidification direction.

Die sich bei der gerichteten Erstarrung in Erstarrungsrichtung bildende langgestreckte, säulenförmige Kornstruktur, weist grobe und damit vergleichsweise große Körner auf, die einen hohen Kriechwiderstand mit sich bringen. Da ferner auch die Korngrenzen parallel zu der gewählten Erstarrungsrichtung verlaufen und keine den Kriechwiderstand verringernde, sich senkrecht zur Erstarrungsrichtung erstreckende Korngrenzen vorliegen, zeichnet sich das Schaufelblatt durch eine hohe Festigkeit in Erstarrungsrichtung mit einem einhergehenden hohen Elastizitätsmodul aus.The elongated, columnar grain structure forming in the solidification direction during the directional solidification has coarse and thus comparatively large grains which bring about a high creep resistance. Furthermore, since the grain boundaries also run parallel to the selected solidification direction and there are no grain boundaries which reduce the creep resistance and extend perpendicular to the solidification direction, the blade leaf is characterized by high strength in the solidification direction with a high modulus of elasticity.

Bei einer vorteilhaften Weiterbildung der Erfindung sind eine äußere und/oder eine innere Plattform vorgesehen. Die an das äußere und innere Ende des Schaufelblatts angrenzenden Plattformen, welche der Befestigung der gesamten Schaufel an einer Gehäusestruktur der Turbine dienen, sind vorzugsweise aus einem feinkörnigen Material gebildet. Feinkörnige Materialien zeichnen sich durch eine erhöhte Kriechneigung bei hohen Temperaturen aus, woraus sich letztlich vergleichsweise hohe Streckgrenzen für das Plattform-Material ergeben. Da insbesondere die Plattformen der erfindungsgemäßen Schaufel im Turbinenbetrieb thermischen Lastwechseln in Form von Temperaturänderungen ausgesetzt werden, ist eine feinkörnige Ausbildung der Leitschaufel-Plattformen im Hinblick auf die Lebensdauer der Plattformen von Vorteil. Eine sich infolge der hohen Temperaturen im Turbinenbetrieb einstellende hohe Streckgrenze des Plattform-Materials stellt vor dem Hintergrund der bekannten Wöhlerkurve sicher, dass das Plattform-Material infolge der thermischen Lastwechsel nicht zu früh ermüdet. Die Einstellung einer erwünschten Korngröße kann durch kornverfeinernde Legierungselemente erzielt werden. Denkbar ist auch eine thermomechanische Behandlung des Plattformmaterials.In an advantageous embodiment of the invention, an outer and / or an inner platform are provided. The platforms adjacent the outer and inner ends of the airfoil, which serve to secure the entire airfoil to a housing structure of the turbine, are preferably formed of a fine-grained material. Fine-grained materials are characterized by increased creep at high temperatures, which ultimately results in comparatively high yield strengths for the platform material. In particular, since the platforms of the blade according to the invention are exposed in the turbine operation thermal load changes in the form of temperature changes, is a fine-grained formation of the vane platforms in terms of life the platforms of advantage. A high yield strength of the platform material which occurs as a result of the high temperatures in turbine operation, against the background of the known Wöhler curve, ensures that the platform material does not tire prematurely as a result of the thermal load changes. The adjustment of a desired grain size can be achieved by grain refining alloying elements. Also conceivable is a thermomechanical treatment of the platform material.

Bei einer alternativen Weiterbildung der Erfindung sind die Schaufel und die Plattformen einstückig aus einem Guss gebildet. So kann insbesondere auch dem Plattform-Material in einer hierfür ausgebildeten Gießvorrichtung eine sich quer zur Längsrichtung des Schaufelblatts erstreckende Erstarrungsrichtung aufgeprägt werden, welche die oben beschrieben Vorteile mit sich bringt.In an alternative development of the invention, the blade and the platforms are integrally formed from a cast. Thus, in particular also the platform material in a casting device designed for this purpose can be impressed with a direction of solidification extending transversely to the longitudinal direction of the blade, which brings about the advantages described above.

Nachfolgend wird ein Ausführungsbeispiel einer erfindungsgemäßen Schaufel anhand der beigefügten schematischen Zeichnung näher erläutert. Es zeigt die Figur eine schematische Darstellung einer erfindungsgemäßen Leitschaufel.An exemplary embodiment of a blade according to the invention will be explained in more detail below with reference to the attached schematic drawing. The figure shows a schematic representation of a guide vane according to the invention.

Die Figur zeigt schematisch eine erfindungsgemäße Leitschaufel 10 einer Turbine. Die Leitschaufel 10 umfasst ein profiliertes Schaufelblatt 12, ein äußere Plattform 14 und eine innere Plattform 16, bezogen auf die Einbaulage der Leitschaufel 10 in der Turbine.The figure shows schematically a guide vane 10 according to the invention of a turbine. The vane 10 includes a profiled airfoil 12, an outer platform 14 and an inner platform 16 relative to the mounting position of the vane 10 in the turbine.

Von der äußeren und der inneren Plattform 14, 16 erstrecken sich jeweils zwei Eingreifelemente 22, die für den Eingriff in eine Gehäusestruktur der Turbine (nicht dargestellt) bestimmt sind, um die Leitschaufel 10 an der Gehäusestruktur anzubringen.Extending from the outer and inner platforms 14, 16, respectively, are two engagement members 22 intended to engage a housing structure of the turbine (not shown) for attaching the vane 10 to the housing structure.

Das profilierte Schaufelblatt 12 weist eine Strömungseintrittskante 20 und eine Strömungsaustrittskante 18 auf. Das Schaufelblatt 12 ist aus einem gerichtet erstarrten, metallischen Material gebildet, wobei sich die Erstarrungsrichtung senkrecht zur Längsachse (z-Richtung) des Schaufelblatts 12 (und damit in X-Richtung) zwischen der Strömungseintrittskante 20 und der Strömungsaustrittskante 18 erstreckt.The profiled airfoil 12 has a flow inlet edge 20 and a flow outlet edge 18. The airfoil 12 is made of a directionally solidified, metallic Material formed, wherein the solidification direction perpendicular to the longitudinal axis (z-direction) of the airfoil 12 (and thus in the X direction) between the flow inlet edge 20 and the flow outlet edge 18 extends.

Thermische Gradienten, die infolge einer entsprechenden Anströmung heißer Gase senkrecht zur Längsachse des Schaufelblatts 12 wirken, bewirken eine thermische Belastung des Schaufelblattmaterials, die in Richtung der Erstarrungsrichtung orientiert ist. Da das Schaufelblatt 12 entlang der Erstarrungsrichtung eine deutlich höhere Widerstandsfähigkeit gegenüber thermischen und mechanischen Belastungen aufweist als ein in üblicherweise - also ohne eine vorgegebene Erstarrungsrichtung - gegossenes Schaufelblatt, kann das Schaufelblatt 12 sehr hohen thermischen Gradienten ausgesetzt werden, ohne dass es zu einer Materialermüdung oder gar zum Materialbruch kommt.Thermal gradients, which act as a result of a corresponding flow of hot gases perpendicular to the longitudinal axis of the airfoil 12, cause a thermal load on the airfoil material, which is oriented in the direction of solidification. Since the airfoil 12 along the solidification direction has a significantly higher resistance to thermal and mechanical loads than a conventionally - ie without a predetermined solidification direction - cast airfoil, the airfoil 12 can be exposed to very high thermal gradient, without causing material fatigue or even comes to the material break.

Die äußere und die innere Plattform 14, 16 sind aus einem feinkörnigen metallischen Material gebildet, das infolge seiner Feinkörnigkeit bei hohen Temperaturen eine hohe Streckgrenze aufweist. Feinkörnige Materialien zeichnen sich durch eine erhöhte Kriechneigung bei hohen Temperaturen aus, woraus sich letztlich vergleichsweise hohe Streckgrenzen für das Plattform-Material ergeben, mit einer einhergehenden hohen Dauerfestigkeit gegenüber thermischen Lastwechseln.The outer and inner platforms 14, 16 are formed of a fine-grained metallic material which has a high yield strength due to its fine graininess at high temperatures. Fine-grained materials are characterized by an increased creep at high temperatures, resulting in the end relatively high yield strengths for the platform material, with a concomitant high fatigue strength against thermal load changes.

Claims (5)

Schaufel (10) für eine Turbine,
insbesondere eine Gasturbine oder eine Dampfturbine, mit einem Schaufelblatt (12), das eine Strömungseintrittskante (20) und eine Strömungsaustrittskante (18) aufweist und aus einem gerichtet erstarrten metallischen Material mit einer vorgegebenen Erstarrungsrichtung gebildet ist,
dadurch gekennzeichnet, dass
die Erstarrungsrichtung im Wesentlichen senkrecht zur Längsrichtung des Schaufelblatts (12) gerichtet ist.Blade (10) for a turbine,
in particular a gas turbine or a steam turbine, with an airfoil (12) which has a flow inlet edge (20) and a flow outlet edge (18) and is formed from a directionally solidified metallic material having a predetermined solidification direction,
characterized in that
the solidification direction is directed substantially perpendicular to the longitudinal direction of the airfoil (12). Schaufel (10) nach Anspruch 1,
mit einer äußeren und einer inneren Plattform (14, 16), die sich jeweils an ein äußeres bzw. inneres Ende des Schaufelblatts (12) anschließen,
dadurch gekennzeichnet, dass
die äußere und/oder die innere Plattform (14, 16) aus einem feinkörnigen Material gebildet sind.A blade (10) according to claim 1,
an outer and an inner platform (14, 16), each adjoining an outer or inner end of the airfoil (12),
characterized in that
the outer and / or the inner platform (14, 16) are formed from a fine-grained material. Schaufel nach Anspruch 1 oder 2,
dadurch gekennzeichnet, dass
das Schaufelblatt (12) und die Plattformen (14, 16) einstückig aus einem Guss gebildet sind.A blade according to claim 1 or 2,
characterized in that
the airfoil (12) and the platforms (14, 16) are integrally formed from a cast. Schaufel nach einem der Ansprüche 1 bis 3,
dadurch gekennzeichnet, dass
sich das gerichtet erstarrte Material über die gesamte Strecke zwischen der Strömungseintrittskante (20) und der Strömungsaustrittskante (18) des Schaufelblatts (12) erstreckt.A blade according to any one of claims 1 to 3,
characterized in that
the directionally solidified material extends over the entire distance between the flow inlet edge (20) and the flow outlet edge (18) of the airfoil (12). Vorrichtung zum Gießen einer Schaufel (10) nach einem der Ansprüche 1 bis 4.Device for casting a blade (10) according to one of claims 1 to 4.
EP06002584A 2006-02-08 2006-02-08 Turbine blade, especially for a gas turbine or a steam turbine Withdrawn EP1818510A1 (en)

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Application Number Priority Date Filing Date Title
EP06002584A EP1818510A1 (en) 2006-02-08 2006-02-08 Turbine blade, especially for a gas turbine or a steam turbine

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Application Number Priority Date Filing Date Title
EP06002584A EP1818510A1 (en) 2006-02-08 2006-02-08 Turbine blade, especially for a gas turbine or a steam turbine

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2927270A1 (en) * 2008-02-08 2009-08-14 Snecma Sa PROCESS FOR MANUFACTURING DIRECTED SOLIDIFICATION AUBES

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1426378A1 (en) * 1963-10-21 1969-01-09 United Aircraft Corp Blade of a gas turbine engine that comes into contact with the gas and the casting process for its manufacture
US3790303A (en) * 1971-04-08 1974-02-05 Bbc Brown Boveri & Cie Gas turbine bucket
US4804311A (en) * 1981-12-14 1989-02-14 United Technologies Corporation Transverse directional solidification of metal single crystal articles
US20030150534A1 (en) * 1998-11-05 2003-08-14 Frasier Donald J. Single crystal vane segment and method of manufacture

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1426378A1 (en) * 1963-10-21 1969-01-09 United Aircraft Corp Blade of a gas turbine engine that comes into contact with the gas and the casting process for its manufacture
US3790303A (en) * 1971-04-08 1974-02-05 Bbc Brown Boveri & Cie Gas turbine bucket
US4804311A (en) * 1981-12-14 1989-02-14 United Technologies Corporation Transverse directional solidification of metal single crystal articles
US20030150534A1 (en) * 1998-11-05 2003-08-14 Frasier Donald J. Single crystal vane segment and method of manufacture

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2927270A1 (en) * 2008-02-08 2009-08-14 Snecma Sa PROCESS FOR MANUFACTURING DIRECTED SOLIDIFICATION AUBES
EP2092999A1 (en) * 2008-02-08 2009-08-26 Snecma Method of manufacturing vanes with directional solidification
US8201612B2 (en) 2008-02-08 2012-06-19 Snecma Process for manufacturing directionally solidified blades

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