EP3219921B1 - Adjustable turboengine lead rotor, turbo-machine and process of manufacture - Google Patents

Adjustable turboengine lead rotor, turbo-machine and process of manufacture Download PDF

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Publication number
EP3219921B1
EP3219921B1 EP16160548.0A EP16160548A EP3219921B1 EP 3219921 B1 EP3219921 B1 EP 3219921B1 EP 16160548 A EP16160548 A EP 16160548A EP 3219921 B1 EP3219921 B1 EP 3219921B1
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EP
European Patent Office
Prior art keywords
airfoil
guide vane
vane
produced
adjustable guide
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.)
Active
Application number
EP16160548.0A
Other languages
German (de)
French (fr)
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EP3219921A1 (en
Inventor
Alexander Klötzer
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
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MTU Aero Engines AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP16160548.0A priority Critical patent/EP3219921B1/en
Priority to ES16160548T priority patent/ES2797733T3/en
Priority to US15/450,143 priority patent/US20170268378A1/en
Publication of EP3219921A1 publication Critical patent/EP3219921A1/en
Application granted granted Critical
Publication of EP3219921B1 publication Critical patent/EP3219921B1/en
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Classifications

    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • 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
    • F05D2230/10—Manufacture by removing material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/239—Inertia or friction welding
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes

Definitions

  • the present invention relates to an adjustable guide vane for a turbomachine, in particular a gas turbine, a turbomachine, in particular a gas turbine, with at least one such adjustable guide vane and a method for producing such an adjustable guide vane.
  • the blades of such adjustable guide vanes must often primarily meet different requirements than different blade sections, in particular bearing surfaces and / or interfaces, at which the guide blades are or are coupled to an adjustment device for adjusting the guide blade: while the former interact, in particular, with a working fluid of the turbomachine,
  • the latter are to be claimed in particular by this, for example the latter should have better storage properties and / or, in particular for the production of the interface, be easier to process, in particular be easier to machine.
  • adjustable guide blades are to be used in turbine stages, the guide blade blades must regularly withstand higher temperatures than with compressor stages.
  • heat-resistant materials in particular often have poor (re) storage properties and / or are difficult to machine, in particular poorly machinable, in particular for producing the interface and / or storage surfaces.
  • a Verstellleitschaufel for a compressor in which the airfoil is made of a less hard material than a pivot of the Verstellleitschaufel.
  • Further adjustment guide vanes for a compressor are from the DE4237031C1 and the US2015167490A1 known.
  • An adjustable guide vane for a compressor stage and for a turbine stage with an airfoil comprising plastic is from the WO2015147964A2 known.
  • An object of an embodiment of the present invention is to improve a turbomachine and / or its manufacture.
  • Claim 8 provides protection for a turbomachine, in particular a gas turbine, with at least one adjustable guide vane described here; advantageous embodiments of the invention are the subject of the dependent claims.
  • an adjustable guide vane for a turbomachine in particular a turbine or compressor stage of a gas turbine, in particular at least one adjustable guide vane of a turbomachine, in particular a turbine or compressor stage of a gas turbine, in particular an aircraft engine, has an airfoil, in particular by Adjustment of the guide vane variable, deflection of a working fluid of the turbomachine, and at least one, in particular radial and / or different from the airfoil, in particular radially inside or outside of the airfoil, blade section, in one embodiment two, in particular radial, blade sections on each other radially opposite sides of the airfoil are arranged, which in the present case are referred to as the first airfoil section (s) without restricting generality.
  • the term “radial” relates in particular to a main or rotational axis of the turbomachine or denotes a direction perpendicular to a main or rotational axis of the turbomachine.
  • the airfoil has a front and a rear edge, which are connected to one another by a suction and a pressure side.
  • the airfoil has one or two radially opposite end face (s) which, in a further development, limits / delimits the airfoil, in particular radially.
  • the guide vane has one or two radially opposite platform (s), one or both of which, in a further development (in each case), in particular radially and / or directly, connect / connect the vane blade, in particular delimiting it / limit, and / or communicates with a flow channel of the working fluid or the turbomachine or is / are set up for this purpose.
  • one, or in particular directly and / or radially, is or is located on a side opposite the airfoil radial of the or one or both end faces and / or the or one or both platforms.
  • a further, in particular radial, blade section adjoining the platform is arranged, in particular produced integrally with the airfoil, which in the present case is referred to as a second blade section without restriction of generality and, in a further development, has a bearing surface or at least a part thereof, in particular together with a first blade section, a bearing surface can form.
  • At least one platform and / or a second airfoil section is arranged radially between the airfoil and a first airfoil section.
  • the blade of the guide vane in one development, the or one or both platform (s) and / or the or one or both second blade section (s) of the guide vane is completely or partially made made of a material which in the present case is referred to as a second material without restricting generality.
  • the or one or both first blade section (s) of the guide blade (s) is / are or are / are made according to an embodiment of the present invention from a material different from this second material, which in the present case is without limitation as generality first material is called.
  • a material that is known under the brand name INCONEL® 718 can be used as the first material.
  • a material which is known under the brand name MAR-M-247 TM can be used as the second material.
  • the first material can be a forged material, whereas the second material can be a cast material.
  • the two first vane sections of the guide vane can be produced from the same (first) material that is different from the second material.
  • a first blade section can also be produced from the first material and the other first blade section can be produced from the second material or a (third) material different from the first and second material.
  • the airfoil on the one hand and the first or the other blade section (s) on the other hand can advantageously be adapted to different requirements. Additionally or alternatively, the manufacture of the guide vane can be improved in one embodiment.
  • the second material has high-temperature-resistant metal and / or a superalloy; in particular, it can consist entirely or partially of it.
  • the second can in particular be designed or suitable for use at high temperatures for use at temperatures of at least 500 ° C., in particular at least 800 ° C.
  • the airfoil can interact advantageously with a working fluid of the turbomachine, in particular withstand, or be designed for, thermal stress, in particular, in one embodiment, particularly in a turbine stage.
  • the first material in a further development also the third material, has metal and / or no superalloy and / or is not heat-resistant, in particular not designed or suitable for use temperatures of at least 1000 ° C., in particular at least 800 ° C. .
  • a first blade section made from the first or third material can have particularly advantageous machining and / or storage properties.
  • a yield or 0.2% proof stress (R e or R p, 0.2 [N / mm 2 ]) of the second material is at least 1.1 times, in particular at least 1.5 times, a yield and / or 0.2% proof stress of the first material, in a further development also of the third material.
  • a density ( ⁇ [kg / m 3 ]) of the second material is at least 1.1 times, in particular at least 1.5 times, a density of the first material, in a further development also of the third material.
  • the airfoil on the one hand and the first or the other blade section (s) on the other hand can advantageously be adapted to different requirements.
  • a lighter (or third) material can reduce a weight of the guide vane.
  • the or at least one, in particular made of the first material, first blade section is machined and / or has one or more threads.
  • an advantageous bearing surface and / or interface at which the guide vane is or is coupled to an adjusting device for adjusting the guide vane can be created, in particular standard parts such as nuts or the like can be used for coupling.
  • the or at least one, in particular manufactured from the first material, first blade section, in particular cohesively is joined, in particular with the airfoil, in particular an end face of the airfoil, one, in particular to the Adjoining the airfoil, platform of the guide vane or a second vane section, in particular adjoining the end face or platform, and / or by or by means of welding, in particular friction or rotational welding.
  • a first blade section in particular made of the first material, can also be joined by another welding method, soldering, gluing, pressing, shrinking or the like, in particular with an end face of the blade, one, in particular on the blade adjoining platform of the guide vane or a second vane section, in particular adjoining the end face or platform.
  • a first blade section in particular made of the first material, can also be connected to the end face or platform or the second blade section in a form-fitting and / or frictional manner, in particular screwed, and / or by appropriate material change by means of a generative process together with the blade leaf , the platform or the second blade section are produced.
  • the airfoil and the first airfoil section (s) can be or be connected advantageously, in particular in a simple, rigid, process-reliable and / or reliable manner.
  • the or at least one, in particular made of the first material, first blade section has a radial end of the guide blade and / or an, in particular peripheral, bearing surface of the guide blade and / or an interface of the guide blade , in particular non-destructively detachable and / or positive and / or frictional engagement, coupling an adjusting device for adjusting the guide vane or at least a part thereof.
  • At least one radial end and / or one bearing surface and / or interface of the guide vane can advantageously be designed, in particular machined or be.
  • a joint can advantageously be spaced apart from the blade and / or in a bearing surface or on a side facing the blade or away from the blade the storage area can be arranged.
  • a radial dimension or height of the or at least one first blade section, in particular made of the first material is at least 5%, in particular at least 10%, and / or at most 200%, in particular at most 75%, of a radial dimension or Height of the airfoil. Additionally or alternatively, in one embodiment, a radial dimension or height of the or at least one, in particular made of the first material, first blade section is at least 5%, in particular at least 10%, and / or at most 1000%, in particular at most 500%, one radial dimension or height of the second blade section arranged between this first blade section and the airfoil.
  • the one or both platforms are made integrally with the airfoil.
  • the turbomachine has a one-part or multi-part housing in which the guide vane is or is mounted in an adjustable manner, in particular in a rotatable or pivotable manner.
  • the adjustable guide vane in one embodiment is rotatably or pivotably mounted in a housing of the turbomachine, in particular a housing section of a turbine or compressor stage of the gas turbine, or is set up for this purpose, in particular by means of corresponding bearing surfaces, in particular circumferential bearing surfaces.
  • a circumferential bearing surface is rotationally symmetrical with respect to the radial direction and / or supports or supports the guide vane in a circumferential and / or axial direction perpendicular to the radial direction or is set up for this purpose.
  • the turbomachine has a one-part or multi-part adjusting device for, in particular mechanical, hydraulic and / or motorized, adjustment of the guide vane, which is coupled to it, in particular its interface, in particular mechanically, in particular positively and / or frictionally, or becomes.
  • Fig. 1 shows an adjustable guide vane of a turbomachine according to an embodiment of the present invention.
  • This has an airfoil 1 for deflecting a working fluid of the turbomachine as well as an upper or radially outer bearing area 2 and a lower or radially inner bearing area 4 for adjustable mounting of the guide vane in a (not shown) housing of the turbomachine, which radially ( vertically in Fig. 1 ) are arranged opposite sides of the airfoil 1.
  • the airfoil 1 as well as the platforms 12, 14 delimiting them and a second airfoil section 6, which connects radially and directly to the radially outer platform 12, are made integrally from a second material, in particular a high-temperature superalloy.
  • the radially inner or outer first blade section can also be produced from the second material or a third material different from the first and second material.
  • the radially inner first blade section 4 is or is joined to the radially inner platform 14 and the radially outer first blade section 5 to the second blade section 6 in a joint 7 by friction welding.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Die vorliegende Erfindung betrifft eine verstellbare Leitschaufel für eine Turbomaschine, insbesondere eine Gasturbine, eine Turbomaschine, insbesondere eine Gasturbine, mit wenigstens einer solchen verstellbaren Leitschaufel sowie ein Verfahren zum Herstellen einer solchen verstellbaren Leitschaufel.The present invention relates to an adjustable guide vane for a turbomachine, in particular a gas turbine, a turbomachine, in particular a gas turbine, with at least one such adjustable guide vane and a method for producing such an adjustable guide vane.

Aus betriebsinterner Praxis sind bereits Verdichterstufen von Gasturbinen mit verstellbaren Leitschaufeln bekannt.Compressor stages of gas turbines with adjustable guide blades are already known from in-house practice.

Dabei müssen Schaufelblätter solcher verstellbaren Leitschaufeln häufig primär anderen Anforderungen genügen als davon verschiedene Schaufelabschnitte, insbesondere Lagerflächen und/oder Schnittstellen, an denen die Leitschaufeln mit einer Verstellvorrichtung zum Verstellen der Leitschaufel gekoppelt sind bzw. werden: während erstere insbesondere mit einem Arbeitsfluid der Turbomaschine interagieren, insbesondere durch dieses beansprucht werden, sollen letztere beispielsweise bessere Lagereigenschaften aufweisen und/oder, insbesondere zur Herstellung der Schnittstelle, leichter bearbeitbar, insbesondere besser spanbar sein.The blades of such adjustable guide vanes must often primarily meet different requirements than different blade sections, in particular bearing surfaces and / or interfaces, at which the guide blades are or are coupled to an adjustment device for adjusting the guide blade: while the former interact, in particular, with a working fluid of the turbomachine, The latter are to be claimed in particular by this, for example the latter should have better storage properties and / or, in particular for the production of the interface, be easier to process, in particular be easier to machine.

Sollen verstellbare Leitschaufeln in Turbinenstufen eingesetzt werden, müssen die Leitschaufelblätter regelmäßig höheren Temperaturen standhalten als bei Verdichterstufen. Insbesondere solche hochwarmfesten Materialien weisen jedoch häufig schlechte(re) Lagereigenschaften auf und/oder sind, insbesondere zur Herstellung der Schnittstelle und/oder Lagerflächen, schwer(er) bearbeitbar, insbesondere schlecht(er) spanbar.If adjustable guide blades are to be used in turbine stages, the guide blade blades must regularly withstand higher temperatures than with compressor stages. However, such heat-resistant materials in particular often have poor (re) storage properties and / or are difficult to machine, in particular poorly machinable, in particular for producing the interface and / or storage surfaces.

Aus der WO2014099530A1 ist eine Verstellleitschaufel für einen Verdichter bekannt, bei der das Schaufelblatt aus einem weniger harten Material als ein Drehzapfen der Verstellleitschaufel besteht. Weitere Verstellleitschaufeln für einen Verdichter sind aus der DE4237031C1 und der US2015167490A1 bekannt. Eine Verstellleitschaufel für eine Verdichter- und für eine Turbinenstufe mit einem Plastik umfassenden Schaufelblatt ist aus der WO2015147964A2 bekannt.From the WO2014099530A1 is known a Verstellleitschaufel for a compressor, in which the airfoil is made of a less hard material than a pivot of the Verstellleitschaufel. Further adjustment guide vanes for a compressor are from the DE4237031C1 and the US2015167490A1 known. An adjustable guide vane for a compressor stage and for a turbine stage with an airfoil comprising plastic is from the WO2015147964A2 known.

Eine Aufgabe einer Ausführung der vorliegenden Erfindung ist es, eine Turbomaschine und/oder deren Herstellung zu verbessern.An object of an embodiment of the present invention is to improve a turbomachine and / or its manufacture.

Diese Aufgabe wird durch eine verstellbare Leitschaufel mit den Merkmalen des Anspruchs 1 bzw. ein Verfahren mit den Merkmalen des Anspruchs 9 gelöst. Anspruch 8 stellt eine Turbomaschine, insbesondere eine Gasturbine, mit wenigstens einer hier beschriebenen verstellbaren Leitschaufel unter Schutz, vorteilhafte Ausführungsformen der Erfindung sind Gegenstand der Unteransprüche.This object is achieved by an adjustable guide vane with the features of claim 1 and a method with the features of claim 9. Claim 8 provides protection for a turbomachine, in particular a gas turbine, with at least one adjustable guide vane described here; advantageous embodiments of the invention are the subject of the dependent claims.

Nach einer Ausführung der vorliegenden Erfindung weist eine verstellbare Leitschaufel für eine Turbomaschine, insbesondere eine Turbinen- oder Verdichterstufe einer Gasturbine, insbesondere wenigstens eine verstellbare Leitschaufel einer Turbomaschine, insbesondere einer Turbinen- oder Verdichterstufe einer Gasturbine, insbesondere eines Flugtriebwerks, ein Schaufelblatt zur, insbesondere durch Verstellung der Leitschaufel variablen, Umlenkung eines Arbeitsfluids der Turbomaschine, und wenigstens einen, insbesondere radialen und/oder von dem Schaufelblatt verschiedenen, insbesondere radial innen oder außen von dem Schaufelblatt angeordneten, Schaufelabschnitt, in einer Ausführung zwei, insbesondere radiale, Schaufelabschnitte, die auf einander radial gegenüberliegenden Seiten des Schaufelblatts angeordnet sind, auf, der bzw. die vorliegend ohne Beschränkung der Allgemeinheit als erste(r) Schaufelabschnitt(e) bezeichnet werden.According to one embodiment of the present invention, an adjustable guide vane for a turbomachine, in particular a turbine or compressor stage of a gas turbine, in particular at least one adjustable guide vane of a turbomachine, in particular a turbine or compressor stage of a gas turbine, in particular an aircraft engine, has an airfoil, in particular by Adjustment of the guide vane variable, deflection of a working fluid of the turbomachine, and at least one, in particular radial and / or different from the airfoil, in particular radially inside or outside of the airfoil, blade section, in one embodiment two, in particular radial, blade sections on each other radially opposite sides of the airfoil are arranged, which in the present case are referred to as the first airfoil section (s) without restricting generality.

Die Angabe "radial" bezieht sich vorliegend insbesondere auf eine Haupt- bzw. Rotationsachse der Turbomaschine bzw. bezeichnet eine zu einer Haupt- bzw. Rotationsachse der Turbomaschine senkrechte Richtung.In the present case, the term “radial” relates in particular to a main or rotational axis of the turbomachine or denotes a direction perpendicular to a main or rotational axis of the turbomachine.

In einer Ausführung weist das Schaufelblatt eine Vorder- und eine Hinterkante auf, die durch eine Saug- und eine Druckseite miteinander verbunden sind.In one embodiment, the airfoil has a front and a rear edge, which are connected to one another by a suction and a pressure side.

In einer Ausführung weist das Schaufelblatt eine oder zwei einander radial gegenüberliegende Stirnseite(n) auf, die in einer Weiterbildung das Schaufelblatt, insbesondere radial, begrenzt/begrenzen.In one embodiment, the airfoil has one or two radially opposite end face (s) which, in a further development, limits / delimits the airfoil, in particular radially.

In einer Ausführung weist die Leitschaufel eine oder zwei einander radial gegenüberliegende Plattform(en) auf, die bzw. von denen eine oder beide in einer Weiterbildung (jeweils), insbesondere radial und/oder unmittelbar, an das Schaufelblatt anschließt/anschließen, dieses insbesondere begrenzt/begrenzen, und/oder mit einem Strömungskanal des Arbeitsfluids bzw. der Turbomaschine kommuniziert/kommunizieren bzw. hierzu eingerichtet ist/sind.In one embodiment, the guide vane has one or two radially opposite platform (s), one or both of which, in a further development (in each case), in particular radially and / or directly, connect / connect the vane blade, in particular delimiting it / limit, and / or communicates with a flow channel of the working fluid or the turbomachine or is / are set up for this purpose.

In einer Ausführung wird bzw. ist auf einer dem Schaufelblattradial gegenüberliegenden Seite der bzw. einer oder beider Stirnseite(n) und/oder der bzw. einer oder beider Plattform(en jeweils) ein, insbesondere unmittelbar und/oder radial an die Stirnseite bzw. Plattform anschließender, weiterer, insbesondere radialer, Schaufelabschnitt angeordnet, insbesondere integral mit dem Schaufelblatt hergestellt, der vorliegend ohne Beschränkung der Allgemeinheit als zweiter Schaufelabschnitt bezeichnet wird und in einer Weiterbildung eine Lagerfläche oder wenigstens einen Teil hiervon aufweisen, insbesondere zusammen mit einem ersten Schaufelabschnitt eine Lagerfläche bilden kann.In one embodiment, one, or in particular directly and / or radially, is or is located on a side opposite the airfoil radial of the or one or both end faces and / or the or one or both platforms. A further, in particular radial, blade section adjoining the platform is arranged, in particular produced integrally with the airfoil, which in the present case is referred to as a second blade section without restriction of generality and, in a further development, has a bearing surface or at least a part thereof, in particular together with a first blade section, a bearing surface can form.

In einer Ausführung ist wenigstens eine Plattform und/oder ein zweiter Schaufelabschnitt radial zwischen dem Schaufelblatt und einem ersten Schaufelblattabschnitt angeordnet.In one embodiment, at least one platform and / or a second airfoil section is arranged radially between the airfoil and a first airfoil section.

Nach einer Ausführung der vorliegenden Erfindung wird bzw. ist das Schaufelblatt der Leitschaufel, in einer Weiterbildung auch die bzw. eine oder beide Plattform(en) und/oder der bzw. einer oder beide zweite Schaufelabschnitt(e) der Leitschaufel, vollständig oder teilweise aus einem Material hergestellt, welches vorliegend ohne Beschränkung der Allgemeinheit als zweites Material bezeichnet wird.According to one embodiment of the present invention, the blade of the guide vane, in one development, the or one or both platform (s) and / or the or one or both second blade section (s) of the guide vane is completely or partially made made of a material which in the present case is referred to as a second material without restricting generality.

Der bzw. ein oder beide erste(r) Schaufelabschnitt(e) der Leitschaufel(n) wird/werden bzw. ist/sind nach einer Ausführung der vorliegenden Erfindung aus einem von diesem zweiten Material verschiedenen Material hergestellt, welches vorliegend ohne Beschränkung der Allgemeinheit als erstes Material bezeichnet wird.The or one or both first blade section (s) of the guide blade (s) is / are or are / are made according to an embodiment of the present invention from a material different from this second material, which in the present case is without limitation as generality first material is called.

Als erstes Material kann zum Beispiel ein Material verwendet werden, welches unter dem Markennamen INCONEL® 718 bekannt ist. Als zweites Material kann hingegen zum Beispiel ein Material verwendet werden, welches unter dem Markennamen MAR-M-247™ bekannt ist. Das erste Material kann eine Schmiedewerkstoff sein, wohingegen das zweite Material ein Gusswerkstoff sein kann.For example, a material that is known under the brand name INCONEL® 718 can be used as the first material. On the other hand, for example, a material which is known under the brand name MAR-M-247 ™ can be used as the second material. The first material can be a forged material, whereas the second material can be a cast material.

Dabei können in einer Ausführung die beiden ersten Schaufelabschnitte der Leitschaufel aus demselben, von dem zweiten Material verschiedenen, (ersten) Material hergestellt werden bzw. sein. In einer anderen Ausführung kann auch ein erster Schaufelabschnitt aus dem ersten Material und der andere erste Schaufelabschnitt aus dem zweiten Material oder einem von dem ersten und zweiten Material verschiedenen (dritten) Material hergestellt werden bzw. sein.In one embodiment, the two first vane sections of the guide vane can be produced from the same (first) material that is different from the second material. In another embodiment, a first blade section can also be produced from the first material and the other first blade section can be produced from the second material or a (third) material different from the first and second material.

Hierdurch können in einer Ausführung das Schaufelblatt einerseits und der bzw. die erste(n) Schaufelabschnitt(e) andererseits vorteilhaft an unterschiedliche Anforderungen angepasst werden bzw. sein. Zusätzlich oder alternativ kann hierdurch in einer Ausführung die Fertigung der Leitschaufel verbessert werden.In this way, in one embodiment, the airfoil on the one hand and the first or the other blade section (s) on the other hand can advantageously be adapted to different requirements. Additionally or alternatively, the manufacture of the guide vane can be improved in one embodiment.

In einer Ausführung weist das zweite Material hochwarmfestes Metall und/oder eine Superlegierung auf, es kann insbesondere vollständig oder teilweise hieraus bestehen. Das zweite kann insbesondere hochwarmfest für Einsatztemperaturen von wenigstens 500°C, insbesondere wenigstens 800°C, ausgelegt bzw. geeignet sein.In one embodiment, the second material has high-temperature-resistant metal and / or a superalloy; in particular, it can consist entirely or partially of it. The second can in particular be designed or suitable for use at high temperatures for use at temperatures of at least 500 ° C., in particular at least 800 ° C.

Hierdurch kann in einer Ausführung das Schaufelblatt vorteilhaft mit einem Arbeitsfluid der Turbomaschine interagieren, insbesondere einer, insbesondere thermischen, Beanspruchung durch dieses standhalten bzw. hierfür ausgelegt werden bzw. sein, in einer Ausführung insbesondere in einer Turbinenstufe.As a result, in one embodiment, the airfoil can interact advantageously with a working fluid of the turbomachine, in particular withstand, or be designed for, thermal stress, in particular, in one embodiment, particularly in a turbine stage.

In einer Ausführung weist das erste Material, in einer Weiterbildung auch das dritte Material, Metall und/oder keine Superlegierung auf und/oder ist nicht hochwarmfest, insbesondere nicht für Einsatztemperaturen von wenigstens 1000°C, insbesondere wenigstens 800°C, ausgelegt bzw. geeignet.In one embodiment, the first material, in a further development also the third material, has metal and / or no superalloy and / or is not heat-resistant, in particular not designed or suitable for use temperatures of at least 1000 ° C., in particular at least 800 ° C. .

Hierdurch kann in einer Ausführung ein aus dem ersten bzw. dritten Material hergestellter erster Schaufelabschnitt insbesondere vorteilhafte Bearbeitungs- und/oder Lagereigenschaften aufweisen.As a result, in one embodiment, a first blade section made from the first or third material can have particularly advantageous machining and / or storage properties.

In einer Ausführung beträgt eine Streck- oder 0,2-%-Dehngrenze (Re bzw. Rp,0,2 [N/mm2]) des zweiten Materials wenigstens das 1,1 fache, insbesondere wenigstens das 1,5fache, einer Streck- und/oder 0,2-%-Dehngrenze des ersten Materials, in einer Weiterbildung auch des dritten Materials. Zusätzlich oder alternativ beträgt in einer Ausführung eine Dichte (ρ[kg/m3]) des zweiten Materials wenigstens das 1,1 fache, insbesondere wenigstens das 1,5fache, einer Dichte des ersten Materials, in einer Weiterbildung auch des dritten Materials.In one embodiment, a yield or 0.2% proof stress (R e or R p, 0.2 [N / mm 2 ]) of the second material is at least 1.1 times, in particular at least 1.5 times, a yield and / or 0.2% proof stress of the first material, in a further development also of the third material. Additionally or alternatively, in one embodiment a density (ρ [kg / m 3 ]) of the second material is at least 1.1 times, in particular at least 1.5 times, a density of the first material, in a further development also of the third material.

Hierdurch können in einer Ausführung das Schaufelblatt einerseits und der bzw. die erste(n) Schaufelabschnitt(e) andererseits vorteilhaft an unterschiedliche Anforderungen angepasst werden bzw. sein. Insbesondere kann durch ein leichteres erstes (bzw. drittes) Material ein G(esamtg)ewicht der Leitschaufel reduziert werden.In this way, in one embodiment, the airfoil on the one hand and the first or the other blade section (s) on the other hand can advantageously be adapted to different requirements. In particular, a lighter (or third) material can reduce a weight of the guide vane.

In einer Ausführung wird bzw. ist der bzw. wenigstens ein, insbesondere aus dem ersten Material hergestellte(r), erste(r) Schaufelabschnitt spanend bearbeitet und/oder weist ein oder mehrere Gewinde auf.In one embodiment, the or at least one, in particular made of the first material, first blade section is machined and / or has one or more threads.

Hierdurch kann in einer Ausführung insbesondere eine vorteilhafte Lagerfläche und/oder Schnittstelle, an der die Leitschaufel mit einer Verstellvorrichtung zum Verstellen der Leitschaufel gekoppelt ist bzw. wird, geschaffen, insbesondere Normteile wie Muttern oder dergleichen zum Koppeln verwendet werden.As a result, in one embodiment, in particular, an advantageous bearing surface and / or interface at which the guide vane is or is coupled to an adjusting device for adjusting the guide vane can be created, in particular standard parts such as nuts or the like can be used for coupling.

In einer Ausführung wird bzw. ist der bzw. wenigstens ein, insbesondere aus dem ersten Material hergestellte(r), erste(r) Schaufelabschnitt, insbesondere stoffschlüssig, gefügt, insbesondere mit dem Schaufelblatt, insbesondere einer Stirnseite des Schaufelblattes, einer, insbesondere an das Schaufelblatt anschließenden, Plattform der Leitschaufel oder einem, insbesondere an Stirnseite oder Plattform anschließenden, zweiten Schaufelabschnitt, und/oder durch bzw. mittels Schweißen, insbesondere Reib- bzw. Rotationsschweißen.In one embodiment, the or at least one, in particular manufactured from the first material, first blade section, in particular cohesively, is joined, in particular with the airfoil, in particular an end face of the airfoil, one, in particular to the Adjoining the airfoil, platform of the guide vane or a second vane section, in particular adjoining the end face or platform, and / or by or by means of welding, in particular friction or rotational welding.

Gleichermaßen können auch andere Fügeverfahren vorteilhaft sein bzw. verwendet werden. So kann ein, insbesondere aus dem ersten Material hergestellter, erster Schaufelabschnitte in einer Ausführung auch durch ein anderes Schweißverfahren, Löten, Kleben, Pressen, Schrumpfen oder dergleichen gefügt sein bzw. werden, insbesondere mit einer Stirnseite des Schaufelblattes, einer, insbesondere an das Schaufelblatt anschließenden, Plattform der Leitschaufel oder einem, insbesondere an Stirnseite oder Plattform anschließenden, zweiten Schaufelabschnitt. Gleichermaßen kann ein, insbesondere aus dem ersten Material hergestellter, erster Schaufelabschnitte auch mit der Stirnseite bzw. Plattform bzw. dem zweiten Schaufelabschnitt form- und/oder reibschlüssig verbunden, insbesondere verschraubt, und/oder durch entsprechenden Materialwechsel mittels eines generativen Verfahrens gemeinsam mit dem Schaufelblatt, der Plattform oder dem zweiten Schaufelabschnitt hergestellt werden bzw. sein.Similarly, other joining methods can also be advantageous or used. In one embodiment, a first blade section, in particular made of the first material, can also be joined by another welding method, soldering, gluing, pressing, shrinking or the like, in particular with an end face of the blade, one, in particular on the blade adjoining platform of the guide vane or a second vane section, in particular adjoining the end face or platform. Likewise, a first blade section, in particular made of the first material, can also be connected to the end face or platform or the second blade section in a form-fitting and / or frictional manner, in particular screwed, and / or by appropriate material change by means of a generative process together with the blade leaf , the platform or the second blade section are produced.

Hierdurch können in einer Ausführung Schaufelblatt und erste(r) Schaufelabschnitt(e) vorteilhaft, insbesondere einfach, steif, prozesssicher und/oder zuverlässig, verbunden werden bzw. sein.As a result, in one embodiment, the airfoil and the first airfoil section (s) can be or be connected advantageously, in particular in a simple, rigid, process-reliable and / or reliable manner.

In einer Ausführung weist der bzw. wenigstens ein, insbesondere aus dem ersten Material hergestellte(r), erste(r) Schaufelabschnitt ein radiales Ende der Leitschaufel und/oder eine, insbesondere Umfangs-, Lagerfläche der Leitschaufel und/oder eine Schnittstelle der Leitschaufel zum, insbesondere zerstörungsfrei lösbaren und/oder form- und/oder reibschlüssigen, Koppeln einer Verstellvorrichtung zum Verstellen der Leitschaufel oder wenigstens einen Teil hiervon auf.In one embodiment, the or at least one, in particular made of the first material, first blade section has a radial end of the guide blade and / or an, in particular peripheral, bearing surface of the guide blade and / or an interface of the guide blade , in particular non-destructively detachable and / or positive and / or frictional engagement, coupling an adjusting device for adjusting the guide vane or at least a part thereof.

Hierdurch kann in einer Ausführung wenigstens ein radiales Ende und/oder eine Lagerfläche und/oder Schnittstelle der Leitschaufel vorteilhaft ausgebildet, insbesondere bearbeitet werden bzw. sein.As a result, in one embodiment, at least one radial end and / or one bearing surface and / or interface of the guide vane can advantageously be designed, in particular machined or be.

In einer Ausführung schließt der bzw. wenigstens ein, insbesondere aus dem ersten Material hergestellte(r), erste(r) Schaufelabschnitt, insbesondere unmittelbar und/oder radial, an eine das Schaufelblatt begrenzende Stirnseite oder Plattform oder einen zweiten Schaufelabschnitt an, der auf einer dem Schaufelblatt gegenüberliegenden Seite der Stirnseite oder Plattform angeordnet ist.In one embodiment, the or at least one, in particular made from the first material, first blade section, in particular directly and / or radially, adjoins an end face or platform delimiting the airfoil or a second blade section which is on a the airfoil opposite side of the end face or platform is arranged.

Indem ein, insbesondere aus dem ersten Material hergestellter, erster Schaufelabschnitt an die Stirnseite oder Plattform anschließt, kann in einer Ausführung möglichst viel Gewicht und/oder teureres zweites Material gespart werden. Indem umgekehrt ein, insbesondere aus dem ersten Material hergestellter, erster Schaufelabschnitt (erst) an den zweiten Schaufelabschnitt anschließt, kann in einer Ausführung eine Fügestelle vorteilhaft von dem Schaufelblatt beabstandet und/oder in einer Lagerfläche oder auf einer dem Schaufelblatt zugewandten oder vom Schaufelblatt abgewandten Seite der Lagerfläche angeordnet werden.By connecting a first blade section, in particular made of the first material, to the end face or platform, as much weight and / or more expensive second material as possible can be saved in one embodiment. Conversely, since a first blade section, in particular made of the first material, adjoins the second blade section, in one embodiment a joint can advantageously be spaced apart from the blade and / or in a bearing surface or on a side facing the blade or away from the blade the storage area can be arranged.

In einer Ausführung beträgt eine radiale Abmessung bzw. Höhe des bzw. wenigstens eines, insbesondere aus dem ersten Material hergestellten, ersten Schaufelabschnitts wenigstens 5%, insbesondere wenigstens 10%, und/oder höchstens 200%, insbesondere höchstens 75%, einer radialen Abmessung bzw. Höhe des Schaufelblattes. Zusätzlich oder alternativ beträgt in einer Ausführung eine radiale Abmessung bzw. Höhe des bzw. wenigstens eines, insbesondere aus dem ersten Material hergestellten, ersten Schaufelabschnitts wenigstens 5%, insbesondere wenigstens 10%, und/oder höchstens 1000%, insbesondere höchstens 500%, einer radialen Abmessung bzw. Höhe des zwischen diesem ersten Schaufelabschnitt und dem Schaufelblatt angeordneten zweiten Schaufelabschnitts.In one embodiment, a radial dimension or height of the or at least one first blade section, in particular made of the first material, is at least 5%, in particular at least 10%, and / or at most 200%, in particular at most 75%, of a radial dimension or Height of the airfoil. Additionally or alternatively, in one embodiment, a radial dimension or height of the or at least one, in particular made of the first material, first blade section is at least 5%, in particular at least 10%, and / or at most 1000%, in particular at most 500%, one radial dimension or height of the second blade section arranged between this first blade section and the airfoil.

In einer Ausführung wird/werden bzw. ist/sind die bzw. eine oder beide Plattform(en) integral mit dem Schaufelblatt, hergestellt.In one embodiment, the one or both platforms are made integrally with the airfoil.

In einer Ausführung weist die Turbomaschine ein ein- oder mehrteiliges Gehäuse auf, in dem die Leitschaufel verstellbar, insbesondere verdreh- bzw. schwenkbar, gelagert ist bzw. wird. Entsprechend ist die verstellbare Leitschaufel in einer Ausführung verdreh- bzw. schwenkbar in einem Gehäuse der Turbomaschine, insbesondere einem Gehäuseabschnitt einer Turbinen- oder Verdichterstufe der Gasturbine, gelagert bzw. hierzu eingerichtet, insbesondere mittels entsprechender Lagerflächen, insbesondere Umfangs-Lagerflächen. Eine Umfangs-Lagerfläche ist in einer Ausführung zur radialen Richtung rotationssymmetrisch und/oder stützt bzw. lagert die Leitschaufel in einer zur radialen Richtung senkrechten Umfangs- und/oder Axialrichtung bzw. ist hierzu eingerichtet.In one embodiment, the turbomachine has a one-part or multi-part housing in which the guide vane is or is mounted in an adjustable manner, in particular in a rotatable or pivotable manner. Accordingly, the adjustable guide vane in one embodiment is rotatably or pivotably mounted in a housing of the turbomachine, in particular a housing section of a turbine or compressor stage of the gas turbine, or is set up for this purpose, in particular by means of corresponding bearing surfaces, in particular circumferential bearing surfaces. In one embodiment, a circumferential bearing surface is rotationally symmetrical with respect to the radial direction and / or supports or supports the guide vane in a circumferential and / or axial direction perpendicular to the radial direction or is set up for this purpose.

In einer Ausführung weist die Turbomaschine eine ein- oder mehrteilige Verstellvorrichtung zum, insbesondere mechanischen, hydraulischen und/oder motorisch, Verstellen der Leitschaufel auf, die damit, insbesondere deren Schnittstelle, insbesondere mechanisch, insbesondere form- und/oder reibschlüssig, gekoppelt ist bzw. wird.In one embodiment, the turbomachine has a one-part or multi-part adjusting device for, in particular mechanical, hydraulic and / or motorized, adjustment of the guide vane, which is coupled to it, in particular its interface, in particular mechanically, in particular positively and / or frictionally, or becomes.

Weitere vorteilhafte Weiterbildungen der vorliegenden Erfindung ergeben sich aus den Unteransprüchen und der nachfolgenden Beschreibung bevorzugter Ausführungen. Hierzu zeigt, teilweise schematisiert, die einzige:

Fig. 1
eine verstellbare Leitschaufel einer Turbomaschine nach einer Ausführung der vorliegenden Erfindung.
Further advantageous developments of the present invention result from the subclaims and the following description of preferred embodiments. The only one shows, partly schematically:
Fig. 1
an adjustable guide vane of a turbomachine according to an embodiment of the present invention.

Fig. 1 zeigt eine verstellbare Leitschaufel einer Turbomaschine nach einer Ausführung der vorliegenden Erfindung. Fig. 1 shows an adjustable guide vane of a turbomachine according to an embodiment of the present invention.

Diese weist ein Schaufelblatt 1 zur Umlenkung eines Arbeitsfluids der Turbomaschine sowie einen oberen bzw. radial äußeren Lagerbereich 2 und einen unteren bzw. radial inneren Lagerbereich 4 zur verstellbaren Lagerung der Leitschaufel in einem (nicht dargestellten) Gehäuse der Turbomaschine auf, die auf einander radial (vertikal in Fig. 1) gegenüberliegenden Seiten des Schaufelblatts 1 angeordnet sind.This has an airfoil 1 for deflecting a working fluid of the turbomachine as well as an upper or radially outer bearing area 2 and a lower or radially inner bearing area 4 for adjustable mounting of the guide vane in a (not shown) housing of the turbomachine, which radially ( vertically in Fig. 1 ) are arranged opposite sides of the airfoil 1.

Das Schaufelblatt 1 sowie diese begrenzende Plattformen 12, 14 und ein zweiter Schaufelabschnitt 6, der radial und unmittelbar an die radial äußeren Plattform 12 anschließt, sind integral aus einem zweiten Material hergestellt, insbesondere einer hochwarmfesten Superlegierung.The airfoil 1 as well as the platforms 12, 14 delimiting them and a second airfoil section 6, which connects radially and directly to the radially outer platform 12, are made integrally from a second material, in particular a high-temperature superalloy.

Ein radial innerer erster Schaufelabschnitt in Form des radial inneren Lagerbereichs 4 sowie ein radial äußerer erster Schaufelabschnitt 5, der zusammen mit dem zweiten Schaufelabschnitt 6 die Umfangs-Lagerfläche des radial äußeren Lagerbereichs 2 bildet sowie eine hieran anschließende Schnittstelle zur Koppelung mit einer Verstellvorrichtung 3 zum Verstellen der Leitschaufel und ein radial äußeres Ende der Leitschaufel mit einem Gewinde aufweist, auf das eine Mutter 8 zur Befestigung der Verstellvorrichtung 3 aufgeschraubt ist bzw. wird, sind bzw. werden jeweils aus einem von dem zweiten Material verschiedenen ersten Material hergestellt, insbesondere einem Material, welches gegenüber der hochwarmfesten Superlegierung eine bessere Spanbarkeit und/oder ein geringeres spezifisches Gewicht aufweist. In einer Abwandlung kann auch der radial innere oder äußerer erster Schaufelabschnitt aus dem zweiten Material oder einem von dem ersten und zweiten Material verschiedenen dritten Material hergestellt werden bzw. sein.A radially inner first blade section in the form of the radially inner bearing area 4 and a radially outer first blade section 5, which together with the second blade section 6 forms the circumferential bearing surface of the radially outer bearing area 2 and an adjoining interface for coupling to an adjusting device 3 for adjustment the guide vane and a radially outer end of the guide vane with a thread onto which a nut 8 for fastening the adjusting device 3 is screwed, are or are each made of a first material different from the second material, in particular a material, which has better machinability and / or a lower specific weight than the high-temperature superalloy. In a modification, the radially inner or outer first blade section can also be produced from the second material or a third material different from the first and second material.

Der radial innere erste Schaufelabschnitt 4 wird bzw. ist mit der radial inneren Plattform 14 und der radial äußere erste Schaufelabschnitt 5 mit dem zweiten Schaufelabschnitt 6 in einer Fügestelle 7 durch Reibschweißen stoffschlüssig gefügt.The radially inner first blade section 4 is or is joined to the radially inner platform 14 and the radially outer first blade section 5 to the second blade section 6 in a joint 7 by friction welding.

Obwohl in der vorhergehenden Beschreibung exemplarische Ausführungen erläutert wurden, sei daraufhingewiesen, dass eine Vielzahl von Abwandlungen möglich ist. Außerdem sei darauf hingewiesen, dass es sich bei den exemplarischen Ausführungen lediglich um Beispiele handelt, die den Schutzbereich, die Anwendungen und den Aufbau in keiner Weise einschränken sollen. Vielmehr wird dem Fachmann durch die vorausgehende Beschreibung ein Leitfaden für die Umsetzung von mindestens einer exemplarischen Ausführung gegeben, wobei diverse Änderungen, insbesondere in Hinblick auf die Funktion und Anordnung der beschriebenen Bestandteile, vorgenommen werden können, ohne den Schutzbereich zu verlassen, wie er sich aus den Ansprüchen und diesen äquivalenten Merkmalskombinationen ergibt.Although exemplary embodiments have been explained in the preceding description, it should be noted that a large number of modifications are possible. In addition, it should be pointed out that the exemplary embodiments are only examples which are not intended to restrict the scope of protection, the applications and the structure in any way. Rather, the person skilled in the art is given a guideline for the implementation of at least one exemplary embodiment by the preceding description, with various changes, in particular with regard to the function and arrangement of the described components, can be made without leaving the scope of protection resulting from the claims and these equivalent combinations of features.

BezugszeichenlisteReference list

11
SchaufelblattAirfoil
22nd
radial äußerer Lagerbereichradially outer storage area
33rd
VerstellvorrichtungAdjustment device
44th
radial innerer Lagerbereichradially inner storage area
55
radial äußerer erster Schaufelabschnittradially outer first blade section
66
zweiter Schaufelabschnittsecond blade section
77
FügestelleJoint
88th
Muttermother

Claims (9)

  1. Adjustable guide vane for a turbomachine, in particular a turbine or compressor stage of a gas turbine, which vane comprises an airfoil (1) for deflecting a working fluid of the turbomachine, which airfoil is at least partly produced from a second material, and at least one first vane portion (4, 5) which is produced from a first material that is different from the second material, characterized in that at least one of the following three conditions i. to iii. is met:
    i.- the second material comprises high-temperature metal and/or a superalloy and the first material does not comprise high-temperature metal and/or a superalloy,
    ii.- a yield stress or 0.2% proof stress of the second material is at least 1.1 times, in particular at least 1.5 times, a yield stress or 0.2% proof stress of the first material and the at least one first vane portion (4, 5) is joined by welding, soldering, pressing or shrinking,
    iii.- a thickness of the second material is at least 1.1 times, in particular at least 1.5 times, a thickness of the first material.
  2. Adjustable guide vane according to the preceding claim, characterized in that it has two first vane portions (4, 5) which are arranged on radially opposite sides of the airfoil (1), at least one of said first vane portions (4, 5) being produced from the first material that is different from the second material.
  3. Adjustable guide vane according to either of the preceding claims, characterized in that at least one first vane portion (4, 5), which is in particular produced from the first material, is machined and/or has at least one thread.
  4. Adjustable guide vane according to any of the preceding claims, characterized in that at least one first vane portion (4, 5), which is in particular produced from the first material, is, in particular integrally, joined.
  5. Adjustable guide vane according to any of the preceding claims, characterized in that at least one first vane portion (4, 5), which is in particular produced from the first material, has a radial end and/or at least part of a bearing surface (2) and/or an interface for coupling an adjusting device (3) for adjusting the guide vane.
  6. Adjustable guide vane according to any of the preceding claims, characterized in that at least one first vane portion (4, 5), which is in particular produced from the first material, adjoins an end face or platform (12, 14) which delimits the airfoil (1) or a second vane portion (6) which is arranged on a side of the end face or platform (12, 14) that is radially opposite the airfoil (1).
  7. Adjustable guide vane according to claim 6, characterized in that the platform (12, 14) and/or the second vane portion (6) is at least partly produced from the second material, in particular is produced integrally with the airfoil (1).
  8. Turbomachine, in particular a gas turbine, comprising a housing, at least one adjustable guide vane, in particular a turbine or compressor stage, according to any of the preceding claims, which guide vane is adjustably mounted in the housing, and an adjusting device (3) coupled thereto for adjusting said guide vane.
  9. Method for producing an adjustable guide vane according to any of the preceding claims, comprising the steps of:
    producing the airfoil (1) from the second material;
    producing at least one first vane portion (4, 5) from the first material and connecting the airfoil (1) to the at least one first vane portion (4, 5), in particular by pressing, shrinking, soldering or welding, in particular friction welding.
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US15/450,143 US20170268378A1 (en) 2016-03-16 2017-03-06 Adjustable guide vane for turbomachine

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EP3219921A1 (en) 2017-09-20
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