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EP2483019A2 - Turbine blade and method for the production thereof - Google Patents

Turbine blade and method for the production thereof

Info

Publication number
EP2483019A2
EP2483019A2 EP10754483A EP10754483A EP2483019A2 EP 2483019 A2 EP2483019 A2 EP 2483019A2 EP 10754483 A EP10754483 A EP 10754483A EP 10754483 A EP10754483 A EP 10754483A EP 2483019 A2 EP2483019 A2 EP 2483019A2
Authority
EP
European Patent Office
Prior art keywords
blade
turbine
turbine blade
wall
produced
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.)
Withdrawn
Application number
EP10754483A
Other languages
German (de)
French (fr)
Inventor
Jens Göhler
Frank Kernstock
Olaf Rehme
Martin Schäfer
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.)
Siemens AG
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Publication of EP2483019A2 publication Critical patent/EP2483019A2/en
Withdrawn legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F10/00—Additive manufacturing of workpieces or articles from metallic powder
    • B22F10/20—Direct sintering or melting
    • B22F10/28—Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y80/00—Products made by additive manufacturing
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P10/00—Technologies related to metal processing
    • Y02P10/25—Process efficiency

Definitions

  • Turbine blade and method for the production thereof The invention relates to. a. to a method having the features according to the preamble of patent claim 1.
  • the invention has for its object to provide a method for producing a turbine blade, which allows the production of particularly lightweight, yet stable turbine blades.
  • the turbine blade is produced by an additive manufacturing process.
  • a significant advantage of the method according to the invention is that it allows a great many degrees of freedom in the design of the turbine blade.
  • a turbine blade, the cavities and / or grating structures or the like with the inventive method in a very simple manner be produced, having - for example, can - in contrast to the initially described ⁇ metal casting process.
  • Such complicated blade designs can be with a metal casting process not, at least not readily realized.
  • a further significant advantage of the method according to the invention is that all features of the turbine blade, at least all of the essential features of the turbine blade, can be produced therewith by one and the same method, ie in other words simultaneously.
  • ⁇ play as the additive manufacturing process allows the realization of drainage slots heating openings and / or other holes or recesses in the turbine blade even during the blade production without the need for additional tools or other subsequent procedural ⁇ rensinhoe would be necessary.
  • the turbine blade can be produced in layers in a particularly simple and thus advantageous manner.
  • a first powder layer is melted locally by means of an energy beam to form a first blade layer; subsequently it, so in this first shovel ⁇ layer, layer by layer brought listed more powder coatings which are melted locally in each case to form further blade layers.
  • the turbine blade is formed by a plurality of stacked individual layers.
  • the liquid layers may be used, which are hardened locally by means of an energy beam so that the turbine blade is assembled in this manner of layers instead of powder layers.
  • the turbine blade is particularly preferably produced in a metal ⁇ metallic powder bed with an electron beam or laser beam.
  • the laser or electron beam serves to selectively melt the thin powder layers, which form the turbine blade after cooling.
  • CAD data are processed which describe the three-dimensional turbine blade by means of a volume model or a surface model.
  • CAD data are converted prior to or during the additive manufacturing process is preferably in ⁇ layer data, where each layer corresponds to a cross-section of the turbine blade with finite thickness.
  • the cross-sectional geometry of the turbine blade is preferably produced during the additive manufacturing process by a line-like exposure of the outer contours and a planar exposure of the cross sections to be filled.
  • the line-like exposure is realized in the case of a point-shaped characteristic of the energy beam, preferably by a corresponding beam movement.
  • a sur fa ⁇ chenetti exposure may be effected for example by a Aneinan ⁇ derreihung of line-like exposure operations.
  • Turbines for example steam or gas turbines, can have a multiplicity of turbine blades of various types.
  • turbines comprise in many cases shovel Leit ⁇ that are similar to the blades shaped and non-rotating or static for example, may have the shape of a support surface. Guiding blades serve primarily to specifically direct the flow of the flow medium within the turbine.
  • turbines may include compressor blades for a compressor section of the turbine. For this reason, it is considered advantageous when a rotor blade, a vane or a compressor blade for a Kom ⁇ pressorabêt of the turbine is made as part of the additive manufacturing process as a turbine blade.
  • At least one cavity is formed between blade walls of the turbine blade.
  • a cavity is preferably at least from ⁇ section-wise filled with a lattice structure.
  • a lattice structure is preferably three-dimensional and may include at ⁇ play filigree, open-cellular SD Jardingitterstruktu ⁇ ren.
  • the separate by a cavity blade walls, at least portion ⁇ be connected to one another by lattice structures in order to achieve through the grating structures a support of the blade walls with each other.
  • the suction-side blade wall of the turbine blade and the réellesei ⁇ term blade wall of the turbine blade are connected by a entspre ⁇ sponding grating structure at least in sections with each other to increase the stability of the turbine blade as a whole.
  • At least one drainage slot is produced in the turbine blade within the scope of the additive manufacturing method.
  • Such drainage slots are preferably to ver ⁇ turns, water which is condensed out of the current flowing through the turbine steam flow to dissipate from the near-wall flow of the flow medium.
  • the ent ⁇ stationary wall by the condensation drops can lead to erosion damage to the rotor blades of the turbine in subsequent turbine stages.
  • erosion damage can be reduced if - as proposed - drainage slits are provided, with which the size of the water droplets can be reduced. Thereby, the water droplets undergo a greater velocity and therefore a smaller Relativgeschwindig ⁇ ness to the rotational movement of the rotor blades, whereby the erosion damage is reduced by the water drops.
  • the drainage slots are located near the trailing edge of the turbine blade.
  • the drainage slots are in the trailing edge of the next third of the pressure-side blade wall.
  • the drainage slots are located, for example, in the front third of the leading edge.
  • Arranging drainage slots particularly close to the trailing edge becomes possible if a grid structure is provided within the turbine blade, since in such a case a particularly thin blade wall thickness can be used.
  • a grid structure is provided within the turbine blade, since in such a case a particularly thin blade wall thickness can be used.
  • other characteristics of the turbine can be realized ⁇ scoop during the additive manufacturing process: For example, Behei ⁇ wetting openings for reduction of the water drops in the turbine and / or other holes in the blade wall made ⁇ the.
  • the heat transfer between the heating or cooling medium inside the blade is favored by the lattice structure and its large surface area.
  • drainage slots Heating with ⁇ openings, other holes or other openings are at least partially provided with grating structures through which a Support takes place.
  • the invention also relates to a turbine blade.
  • a turbine blade According to the invention in this respect is provided in that between the blade walls of the turbine blade is a cavity, which is at least partially filled with a Git ⁇ ter Design.
  • a significant advantage of the turbine blades according to the invention is the fact that it has a high stability with low weight.
  • the turbine blade is a vane, a rotor blade or a compressor blade.
  • the suction-side blade wall of the turbine blade and the pressure-side blade wall of the turbine show ⁇ fel are connected together by the lattice structure.
  • Such a connection can be a support of the blade walls reach each other and thus ensure a particularly high stability.
  • vane walls have openings or holes, these are preferably with a lattice structure - provided - partially ⁇ minimum.
  • the invention further relates to a turbine, especially a gas turbine or steam turbine, which is, out ⁇ equipped with at least one turbine blade, as described above.
  • the turbine blade within the turbine preferably forms a static guide vane, a rotating rotor blade or a compression vane.
  • Turbine blade according to the invention in a three-dimensional representation obliquely from the
  • FIG. 2 shows the turbine blade according to FIG. 1 in cross-section
  • FIG. 5 shows by way of example a hole in a blade wall of the turbine blade according to FIG. cut, with the hole completely with
  • FIG. 6 shows an example of a hole in a blade wall of the turbine blade of Figure 1 in cross-section ⁇ , wherein the hole in part with a
  • FIG. 7 shows an example of a hole in a blade wall of the turbine blade of Figure 1 in cross-section ⁇ , wherein the hole from below with a
  • FIG. 1 shows a turbine blade 10 which comprises a suction-side blade wall 20 and a pressure-side blade wall 30.
  • the suction-side blade wall 20 and the pressure-side blade wall 30 are ⁇ as at a front edge 50 joined together at a trailing edge 40th
  • the cavity 55 between the two blade walls 20 and 30 is provided with a three-dimensional lattice structure, which is identified by the reference numeral 60.
  • the turbine blade 10 illustrated in Figure 1 is made in the context of an additive manufacturing process, in which the suction-side blade wall 20, the pressure-side blade wall 30 and the lattice structure are formed simultaneously from the same Ma ⁇ TERIAL 60th
  • the turbine blade 10 is shown according to figure 1 in cross-section ⁇ .
  • the pressure-side blade wall 30 Tur ⁇ depicted of 10 according to Figures 1 and 2 in the plan view in further detail.
  • the blade ⁇ wall 30 has two slotted holes 100 and 110 has.
  • the slot-shaped holes can serve as drainage slots and / or heating openings, with which water is removed from the near-wall flow of the turbine flowing through the flow medium.
  • the arrangement of the slot-shaped holes 100 and 110 is selected such that they are as close as possible to the trailing edge 40, ie the leading edge 50 as far as possible. Particularly be ⁇ vorzugt the slot-shaped holes 100 and 110 are arranged within the trailing edge 40 facing half A of the pressure-side blade wall 30th
  • FIG. 4 shows by way of example the suction-side blade wall 20 of the turbine blade 10. It can be seen that a slot-shaped hole 120 which extends through the blade wall 20 is arranged in the region of the front edge 50. Specifics ⁇ DERS preferably, the slit-shaped hole 120 within which the leading edge 50 facing half B of the suction-side blade wall 20.
  • the grid structure 60 disposed within the turbine window 10 may be disposed outside of the slot-shaped hole 120 or alternatively extend into the slot-shaped hole 120.
  • FIG. 5 shows an embodiment in which the lattice structure 60 extends completely into a hole 200 of the blade wall 210 of the turbine blade 10. The hole 200 is thus bridged by the grid structure 60 and supported by this.
  • FIG. 6 shows by way of example an embodiment in which the grating structure 60 extends only partially into the hole 200.
  • approximately half the wall thickness d of the grating structural ⁇ tur 60 is detected; the other half of the wall thickness remains free of the grid structure 60.
  • FIG 7 an embodiment of a hole 200 is shown, which is not ver see ⁇ with a grating structure 60th
  • the grid structure 60 extends only to the lower edge 220 of the hole 200 and adjoins the hole 200 without protruding into the hole itself.
  • the lattice structure 60 is therefore located only within the turbine blade and not in the region of the hole 200.

Landscapes

  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention relates to, amongst other things, a method for producing a turbine blade (10). The aim of the invention is to produce a particularly light but also stable turbine blade, said turbine blade being produced according to a layering method. Said type of method allows lots of degrees of freedom during the configuration of the turbine blade. Cavities and/or mesh structures can be produced according to the same method. Said layering method also enables, for example, drainage slots, warming openings and/or other holes and/or recesses to be produced in the turbine blade during the production thereof. Holes can also be provided, totally or partially, with a mesh structure.

Description

Beschreibung description

Turbinenschaufel und Verfahren zu deren Herstellung Die Erfindung bezieht sich u. a. auf ein Verfahren mit den Merkmalen gemäß dem Oberbegriff des Patentanspruchs 1. Turbine blade and method for the production thereof The invention relates to. a. to a method having the features according to the preamble of patent claim 1.

Ein derartiges Verfahren ist beispielsweise aus der deutschen Patentschrift DE 10 2006 030 365 B3 bekannt. Bei diesem vor- bekannten Verfahren wird eine Turbinenschaufel durch ein Me¬ tallgussverfahren hergestellt. Such a method is known for example from the German patent DE 10 2006 030 365 B3. In this pre-known process, a turbine blade is produced by a ¬ Me tallgussverfahren.

Der Erfindung liegt die Aufgabe zugrunde, ein Verfahren zum Herstellen einer Turbinenschaufel anzugeben, das die Herstel- lung besonders leichter, aber dennoch stabiler Turbinenschaufeln ermöglicht. The invention has for its object to provide a method for producing a turbine blade, which allows the production of particularly lightweight, yet stable turbine blades.

Diese Aufgabe wird erfindungsgemäß durch ein Verfahren mit den Merkmalen gemäß Patentanspruch 1 gelöst. Vorteilhafte Ausgestaltungen des erfindungsgemäßen Verfahrens sind in Unteransprüchen angegeben. This object is achieved by a method having the features according to claim 1. Advantageous embodiments of the method according to the invention are specified in subclaims.

Danach ist erfindungsgemäß vorgesehen, dass die Turbinenschaufel durch ein additives Herstellungsverfahren herge- stellt wird. Thereafter, it is provided according to the invention that the turbine blade is produced by an additive manufacturing process.

Ein wesentlicher Vorteil des erfindungsgemäßen Verfahrens besteht darin, dass dieses sehr viele Freiheitsgrade bei der Gestaltung der Turbinenschaufel ermöglicht. Beispielsweise kann - im Unterschied zu dem eingangs beschriebenen Metall¬ gussverfahren - mit dem erfindungsgemäßen Verfahren in sehr einfacher Weise eine Turbinenschaufel hergestellt werden, die Hohlräume und/oder Gitterstrukturen oder dergleichen aufweist. Derart komplizierte Schaufelgestaltungen lassen sich mit einem Metallgussverfahren nicht, zumindest nicht ohne weiteres, realisieren. A significant advantage of the method according to the invention is that it allows a great many degrees of freedom in the design of the turbine blade. A turbine blade, the cavities and / or grating structures or the like with the inventive method in a very simple manner be produced, having - for example, can - in contrast to the initially described ¬ metal casting process. Such complicated blade designs can be with a metal casting process not, at least not readily realized.

Ein weiterer wesentlicher Vorteil des erfindungsgemäßen Ver- fahrens ist darin zu sehen, dass mit diesem alle Merkmale der Turbinenschaufel, zumindest alle wesentlichen Merkmale der Turbinenschaufel, mit ein und demselben Verfahren, also mit anderen Worten gleichzeitig, hergestellt werden können. Bei¬ spielsweise erlaubt das additive Herstellungsverfahren die Realisierung von Entwässerungsschlitzen, Beheizungsöffnungen und/oder sonstigen Löchern bzw. Ausnehmungen in der Turbinenschaufel bereits während der Schaufelherstellung, ohne dass hierzu weitere Werkzeuge oder weitere anschließende Verfah¬ rensschritte nötig wären. A further significant advantage of the method according to the invention is that all features of the turbine blade, at least all of the essential features of the turbine blade, can be produced therewith by one and the same method, ie in other words simultaneously. In ¬ play as the additive manufacturing process allows the realization of drainage slots heating openings and / or other holes or recesses in the turbine blade even during the blade production without the need for additional tools or other subsequent procedural ¬ rensschritte would be necessary.

Additive Herstellungsverfahren sind für sich aus anderen Technikgebieten bereits bekannt. Nur beispielhaft sei diesbe¬ züglich auf die Druckschrift "Wohlers Report 2008" (Terry T. Wohlers, Wohlers Associates Inc., Fort Collins, CO, USA, ISBN 0-9754429-4-5) verwiesen. Dieser Druckschrift lassen sich Beispiele entnehmen, wie additive Herstellungsverfahren im Einzelnen ausgeführt werden können. Additive manufacturing processes are already known per se from other fields of technology. For example only was diesbe ¬ züglich refer to the publication "Wohlers Report 2008" (0-9754429-4-5 Terry T. Wohlers, Wohlers Associates Inc., Fort Collins, CO, USA, ISBN). This document shows examples of how additive manufacturing processes can be carried out in detail.

Besonders einfach und damit vorteilhaft lässt sich die Turbi- nenschaufel schichtweise herstellen. Vorzugsweise wird eine erste Pulverschicht mittels eines Energiestrahles lokal unter Bildung einer ersten Schaufelschicht geschmolzen; anschließend werden darauf, also auf diese erste Schaufel¬ schicht, Schicht für Schicht weitere Pulverschichten aufge- bracht, die jeweils unter Bildung weiterer Schaufelschichten lokal geschmolzen werden. In dieser Weise wird die Turbinenschaufel durch eine Vielzahl aufeinander gesetzter Einzelschichten gebildet. Alternativ können anstelle von Pulverschichten auch Flüssigkeitsschichten verwendet werden, die lokal mittels eines Energiestrahles ausgehärtet werden, so dass die Turbinen¬ schaufel in dieser Weise aus Schichten zusammengesetzt wird. The turbine blade can be produced in layers in a particularly simple and thus advantageous manner. Preferably, a first powder layer is melted locally by means of an energy beam to form a first blade layer; subsequently it, so in this first shovel ¬ layer, layer by layer brought listed more powder coatings which are melted locally in each case to form further blade layers. In this way, the turbine blade is formed by a plurality of stacked individual layers. Alternatively, the liquid layers may be used, which are hardened locally by means of an energy beam so that the turbine blade is assembled in this manner of layers instead of powder layers.

Besonders bevorzugt wird die Turbinenschaufel in einem metal¬ lischen Pulverbett mit einem Laserstrahl oder Elektronenstrahl hergestellt. Der Laser- oder Elektronenstrahl dient dabei zum selektiven Aufschmelzen der dünnen Pulverschichten, die nach dem Abkühlen die Turbinenschaufel bilden. The turbine blade is particularly preferably produced in a metal ¬ metallic powder bed with an electron beam or laser beam. The laser or electron beam serves to selectively melt the thin powder layers, which form the turbine blade after cooling.

Zur Ansteuerung des Energiestrahls werden vorzugsweise CAD- Daten verarbeitet, die die dreidimensionale Turbinenschaufel durch ein Volumenmodell oder ein Oberflächenmodell beschrei- ben. Zur Verarbeitung werden die CAD-Daten vor oder während des additiven Herstellungsprozesses vorzugsweise in Schicht¬ daten überführt, wobei jede Schicht einem Querschnitt der Turbinenschaufel mit finiter Schichtdicke entspricht. Die Querschnittsgeometrie der Turbinenschaufel wird während des additiven Herstellungsverfahrens vorzugsweise durch eine linienartige Belichtung der äußeren Konturen und einer flächenartigen Belichtung der zu füllenden Querschnitte hergestellt. Die linienartige Belichtung wird im Falle einer punktförmigen Charakteristik des Energiestrahls vorzugsweise durch eine entsprechende Strahlbewegung realisiert. Eine flä¬ chenartige Belichtung kann beispielsweise durch eine Aneinan¬ derreihung von linienartigen Belichtungsvorgängen erfolgen. Turbinen, beispielsweise Dampf- oder Gasturbinen, können einer Vielzahl unterschiedlich gearteter Turbinenschaufeln aufweisen. Neben rotierenden Laufschaufeln umfassen Turbinen in vielen Fällen auch nichtrotierende bzw. statische Leit¬ schaufeln, die ähnlich wie die Laufschaufeln geformt sind und beispielsweise die Form einer Tragfläche aufweisen können. Leitschaufeln dienen primär dazu, die Strömung des Strömungsmediums innerhalb der Turbine gezielt auszurichten. Darüber hinaus können Turbinen Kompressorschaufeln für einen Kompres- sorabschnitt der Turbine umfassen. Aus diesem Grunde wird es als vorteilhaft angesehen, wenn im Rahmen des additiven Herstellungsverfahrens als Turbinenschaufel eine Laufschaufei , eine Leitschaufel oder eine Kompressorschaufel für einen Kom¬ pressorabschnitt der Turbine hergestellt wird. To control the energy beam, preferably CAD data are processed which describe the three-dimensional turbine blade by means of a volume model or a surface model. For processing the CAD data are converted prior to or during the additive manufacturing process is preferably in ¬ layer data, where each layer corresponds to a cross-section of the turbine blade with finite thickness. The cross-sectional geometry of the turbine blade is preferably produced during the additive manufacturing process by a line-like exposure of the outer contours and a planar exposure of the cross sections to be filled. The line-like exposure is realized in the case of a point-shaped characteristic of the energy beam, preferably by a corresponding beam movement. A sur fa ¬ chenartige exposure may be effected for example by a Aneinan ¬ derreihung of line-like exposure operations. Turbines, for example steam or gas turbines, can have a multiplicity of turbine blades of various types. In addition to rotating blades turbines comprise in many cases shovel Leit ¬ that are similar to the blades shaped and non-rotating or static for example, may have the shape of a support surface. Guiding blades serve primarily to specifically direct the flow of the flow medium within the turbine. In addition, turbines may include compressor blades for a compressor section of the turbine. For this reason, it is considered advantageous when a rotor blade, a vane or a compressor blade for a Kom ¬ pressorabschnitt of the turbine is made as part of the additive manufacturing process as a turbine blade.

Um das Gewicht der Turbinenschaufel zu reduzieren, wird es als vorteilhaft angesehen, wenn zwischen Schaufelwänden der Turbinenschaufel zumindest ein Hohlraum gebildet wird. Um dennoch eine hohe Stabilität der Turbinenschaufel zu gewähr- leisten, wird ein solcher Hohlraum vorzugsweise zumindest ab¬ schnittsweise mit einer Gitterstruktur gefüllt. Eine solche Gitterstruktur ist vorzugsweise dreidimensional und kann bei¬ spielsweise filigrane, offen-zelluläre SD-Raumgitterstruktu¬ ren umfassen. In order to reduce the weight of the turbine blade, it is considered advantageous if at least one cavity is formed between blade walls of the turbine blade. In order to nevertheless provide a high stability of the turbine blade to warranty, such a cavity is preferably at least from ¬ section-wise filled with a lattice structure. Such a lattice structure is preferably three-dimensional and may include at ¬ play filigree, open-cellular SD Raumgitterstruktu ¬ ren.

Als besonders vorteilhaft wird es angesehen, wenn die durch einen Hohlraum getrennten Schaufelwände zumindest abschnitts¬ weise durch Gitterstrukturen miteinander verbunden werden, um durch die Gitterstrukturen eine Abstützung der Schaufelwände untereinander zu erreichen. Beispielsweise werden die saug- seitige Schaufelwand der Turbinenschaufel und die drucksei¬ tige Schaufelwand der Turbinenschaufel durch eine entspre¬ chende Gitterstruktur zumindest abschnittsweise miteinander verbunden, um die Stabilität der Turbinenschaufel insgesamt zu erhöhen. Especially advantageous is considered when the separate by a cavity blade walls, at least portion ¬, be connected to one another by lattice structures in order to achieve through the grating structures a support of the blade walls with each other. For example, the suction-side blade wall of the turbine blade and the drucksei ¬ term blade wall of the turbine blade are connected by a entspre ¬ sponding grating structure at least in sections with each other to increase the stability of the turbine blade as a whole.

Durch das beschriebene Abstützen der Schaufelwände mit Git¬ terstrukturen lässt sich darüber hinaus erreichen, dass die Schaufelwände dünner, also mit geringerer Profilwandstärke, hergestellt werden können, als dies bei hohlen Turbinenschau¬ feln der Fall wäre. The described supporting the blade walls with Git ¬ terstrukturen can be achieved beyond that the blade walls thinner, so with a lower profile wall thickness, can be produced than would be the case with hollow turbine shop ¬ feln.

Darüber hinaus wird es als vorteilhaft angesehen, wenn im Rahmen des additiven Herstellungsverfahrens in der Turbinenschaufel zumindest ein Entwässerungsschlitz hergestellt wird. Derartige Entwässerungsschlitze werden vorzugsweise dazu ver¬ wendet, Wasser, das aus dem durch die Turbine fließenden Dampfstrom auskondensiert ist, aus der wandnahen Strömung des Strömungsmediums abzuführen. Die durch die Kondensation ent¬ stehenden Wandtropfen können zu Erosionsschäden an den Laufschaufeln der Turbine in nachfolgenden Turbinenstufen führen. Eine solche Erosionsschädigung lässt sich jedoch reduzieren, wenn - wie vorgeschlagen - Entwässerungsschlitze vorgesehen werden, mit denen sich die Größe der Wassertropfen verkleinern lässt. Dadurch erfahren die Wassertropfen eine größere Geschwindigkeit und somit eine kleinere Relativgeschwindig¬ keit zur Rotationsbewegung der Laufschaufeln, wodurch die Erosionsschädigung durch die Wassertropfen reduziert wird. In addition, it is considered advantageous if at least one drainage slot is produced in the turbine blade within the scope of the additive manufacturing method. Such drainage slots are preferably to ver ¬ turns, water which is condensed out of the current flowing through the turbine steam flow to dissipate from the near-wall flow of the flow medium. The ent ¬ stationary wall by the condensation drops can lead to erosion damage to the rotor blades of the turbine in subsequent turbine stages. However, such erosion damage can be reduced if - as proposed - drainage slits are provided, with which the size of the water droplets can be reduced. Thereby, the water droplets undergo a greater velocity and therefore a smaller Relativgeschwindig ¬ ness to the rotational movement of the rotor blades, whereby the erosion damage is reduced by the water drops.

Besonders bevorzugt werden die Entwässerungsschlitze nahe der Hinterkante der Turbinenschaufel angeordnet. Beispielsweise befinden sich die Entwässerungsschlitze in dem der Hinterkante nächsten Drittel der druckseitigen Schaufelwand. Auf der saugseitigen Schaufelwand befinden sich die Entwässerungsschlitze beispielsweise im vorderen Drittel nach der Eintrittskante . Most preferably, the drainage slots are located near the trailing edge of the turbine blade. For example, the drainage slots are in the trailing edge of the next third of the pressure-side blade wall. On the suction-side blade wall, the drainage slots are located, for example, in the front third of the leading edge.

Ein Anordnen von Entwässerungsschlitzen besonders nahe an der Hinterkante wird möglich, wenn eine Gitterstruktur innerhalb der Turbinenschaufel vorgesehen wird, da in einem solchen Falle eine besonders dünne Schaufelwanddicke eingesetzt wer¬ den kann. Alternativ und/oder zusätzlich können während des additiven Herstellungsverfahrens auch weitere Merkmale der Turbinen¬ schaufel realisiert werden: So können beispielsweise Behei¬ zungsöffnungen zur Reduktion der Wassertropfen in der Turbine und/oder sonstige Löcher in der Schaufelwand hergestellt wer¬ den. Außerdem wird der Wärmeübergang zwischen dem Heiz- oder Kühlmedium im Inneren der Schaufel durch die Gitterstruktur und deren großer Oberfläche begünstigt. Um zu vermeiden, dass Entwässerungsschlitze oder Beheizungs¬ öffnungen die Stabilität der Turbinenschaufel beeinträchti¬ gen, beispielsweise Sollbruchstellen bilden, wird es als vorteilhaft angesehen, wenn Entwässerungsschlitze, Beheizungs¬ öffnungen, sonstige Löcher oder sonstige Öffnungen zumindest teilweise mit Gitterstrukturen versehen werden, durch die eine Abstützung erfolgt. Arranging drainage slots particularly close to the trailing edge becomes possible if a grid structure is provided within the turbine blade, since in such a case a particularly thin blade wall thickness can be used. Alternatively and / or additionally, other characteristics of the turbine can be realized ¬ scoop during the additive manufacturing process: For example, Behei ¬ wetting openings for reduction of the water drops in the turbine and / or other holes in the blade wall made ¬ the. In addition, the heat transfer between the heating or cooling medium inside the blade is favored by the lattice structure and its large surface area. In order to avoid that drainage slots or Heating with ¬ openings the stability of the turbine blade impair ¬ gene, for example, predetermined breaking points form, it is considered advantageous if drainage slots Heating with ¬ openings, other holes or other openings are at least partially provided with grating structures through which a Support takes place.

Die Erfindung bezieht sich darüber hinaus auf eine Turbinenschaufel. Erfindungsgemäß ist diesbezüglich vorgesehen, dass zwischen Schaufelwänden der Turbinenschaufel ein Hohlraum vorhanden ist, der zumindest abschnittsweise mit einer Git¬ terstruktur gefüllt ist. The invention also relates to a turbine blade. According to the invention in this respect is provided in that between the blade walls of the turbine blade is a cavity, which is at least partially filled with a Git ¬ terstruktur.

Ein wesentlicher Vorteil der erfindungsgemäßen Turbinenschau- fei ist darin zu sehen, dass diese eine hohe Stabilität bei geringem Gewicht aufweist. A significant advantage of the turbine blades according to the invention is the fact that it has a high stability with low weight.

Vorzugsweise handelt es sich bei der Turbinenschaufel um eine Leitschaufel, eine Laufschaufei oder eine Kompressorschaufel. Preferably, the turbine blade is a vane, a rotor blade or a compressor blade.

Um eine besonders hohe Stabilität der Turbinenschaufel zu ge¬ währleisten, sind die saugseitige Schaufelwand der Turbinen¬ schaufel und die druckseitige Schaufelwand der Turbinenschau¬ fel durch die Gitterstruktur miteinander verbunden. Durch eine solche Verbindung lässt sich ein Abstützen der Schaufelwände untereinander erreichen und somit eine besonders hohe Stabilität gewährleisten. To achieve a particularly high stability of the turbine blade to ge ¬ währleisten, the suction-side blade wall of the turbine blade and the pressure-side blade wall of the turbine show ¬ fel are connected together by the lattice structure. By Such a connection can be a support of the blade walls reach each other and thus ensure a particularly high stability.

Falls in den Schaufelwänden Öffnungen oder Löcher vorhanden sind, sind diese vorzugsweise mit einer Gitterstruktur - zu¬ mindest teilweise - versehen. If present in the vane walls have openings or holes, these are preferably with a lattice structure - provided - partially ¬ minimum.

Die Erfindung bezieht sich darüber hinaus auf eine Turbine, insbesondere Gasturbine oder Dampfturbine, die mit zumindest einer Turbinenschaufel, wie sie oben beschrieben ist, ausge¬ stattet ist. Vorzugsweise bildet die Turbinenschaufel inner¬ halb der Turbine eine statische Leitschaufel, eine rotierende Laufschaufei oder eine Kompressionsschaufel. The invention further relates to a turbine, especially a gas turbine or steam turbine, which is, out ¬ equipped with at least one turbine blade, as described above. The turbine blade within the turbine preferably forms a static guide vane, a rotating rotor blade or a compression vane.

Die Erfindung wird nachfolgend anhand von Ausführungsbeispie¬ len näher erläutert; dabei zeigen beispielhaft The invention will be explained in more detail with reference to Ausführungsbeispie ¬ len; thereby show by way of example

Figur 1 Ausführungsbeispiel für eine Figure 1 embodiment for a

erfindungsgemäße Turbinenschaufel in einer dreidimensionalen Darstellung schräg von der Turbine blade according to the invention in a three-dimensional representation obliquely from the

Seite, Page,

Figur 2 die Turbinenschaufel gemäß Figur 1 im Quer- schnitt, FIG. 2 shows the turbine blade according to FIG. 1 in cross-section,

Figur 3 die druckseitige Schaufelwand der Turbinen¬ schaufel gemäß Figur 1 in der Draufsicht, 3, the pressure-side blade wall of the turbine blade of Figure 1 in plan view,

Figur 4 die saugseitige Schaufelwand der Turbinen¬ schaufel gemäß Figur 1 in der Draufsicht, 4, the suction-side blade wall of the turbine blade of Figure 1 in plan view,

Figur 5 beispielhaft ein Loch in einer Schaufelwand der Turbinenschaufel gemäß Figur 1 im Quer- schnitt, wobei das Loch vollständig mit FIG. 5 shows by way of example a hole in a blade wall of the turbine blade according to FIG. cut, with the hole completely with

einer Gitterstruktur gefüllt  filled a grid structure

Figur 6 beispielhaft ein Loch in einer Schaufelwand der Turbinenschaufel gemäß Figur 1 im Quer¬ schnitt, wobei das Loch teilweise mit einer6 shows an example of a hole in a blade wall of the turbine blade of Figure 1 in cross-section ¬, wherein the hole in part with a

Gitterstruktur gefüllt ist, und Lattice structure is filled, and

Figur 7 beispielhaft ein Loch in einer Schaufelwand der Turbinenschaufel gemäß Figur 1 im Quer¬ schnitt, wobei das Loch von unten mit einer7 shows an example of a hole in a blade wall of the turbine blade of Figure 1 in cross-section ¬, wherein the hole from below with a

Gitterstruktur abgestützt Lattice structure supported

Der Übersicht halber werden in den Figuren für identische oder vergleichbare Komponenten stets dieselben Bezugszeichen verwendet . For the sake of clarity, the same reference numerals are always used in the figures for identical or comparable components.

In der Figur 1 erkennt man eine Turbinenschaufel 10, die eine saugseitige Schaufelwand 20 sowie eine druckseitige Schaufel- wand 30 umfasst. Die saugseitige Schaufelwand 20 und die druckseitige Schaufelwand 30 sind an einer Hinterkante 40 so¬ wie an einer Vorderkante 50 miteinander verbunden. FIG. 1 shows a turbine blade 10 which comprises a suction-side blade wall 20 and a pressure-side blade wall 30. The suction-side blade wall 20 and the pressure-side blade wall 30 are ¬ as at a front edge 50 joined together at a trailing edge 40th

In der Figur 1 lässt sich darüber hinaus erkennen, dass der Hohlraum 55 zwischen den beiden Schaufelwänden 20 und 30 mit einer dreidimensionalen Gitterstruktur versehen ist, die mit dem Bezugszeichen 60 gekennzeichnet ist. In addition, it can be seen in FIG. 1 that the cavity 55 between the two blade walls 20 and 30 is provided with a three-dimensional lattice structure, which is identified by the reference numeral 60.

Die in der Figur 1 dargestellte Turbinenschaufel 10 wird im Rahmen eines additiven Herstellungsverfahrens hergestellt, bei dem die saugseitige Schaufelwand 20, die druckseitige Schaufelwand 30 sowie die Gitterstruktur 60 aus demselben Ma¬ terial gleichzeitig hergestellt werden. In Figur 2 ist die Turbinenschaufel 10 gemäß Figur 1 im Quer¬ schnitt dargestellt. Man erkennt die Schaufelwände 20 und 30, die Hinterkante 40, die Vorderkante 50 sowie die Gitterstruk¬ tur 60. The turbine blade 10 illustrated in Figure 1 is made in the context of an additive manufacturing process, in which the suction-side blade wall 20, the pressure-side blade wall 30 and the lattice structure are formed simultaneously from the same Ma ¬ TERIAL 60th In Figure 2, the turbine blade 10 is shown according to figure 1 in cross-section ¬. One recognizes the blade walls 20 and 30, the trailing edge 40, the leading edge 50 as well as the grating structural ¬ tur 60th

In der Figur 3 ist die druckseitige Schaufelwand 30 der Tur¬ binenschaufel 10 gemäß den Figuren 1 und 2 in der Draufsicht näher im Detail dargestellt. Man erkennt, dass die Schaufel¬ wand 30 zwei schlitzförmige Löcher 100 und 110 aufweist. Die schlitzförmigen Löcher können als Entwässerungsschlitze und/oder Heizungsöffnungen dienen, mit denen Wasser aus der wandnahen Strömung des die Turbine durchströmenden Strömungsmediums abgeführt wird. Wie sich in der Figur 3 gut erkennen lässt, ist die Anordnung der schlitzförmigen Löcher 100 und 110 derart gewählt, dass sich diese möglichst dicht an der Hinterkante 40, also der Vorderkante 50 möglichst abgewandt, befinden. Besonders be¬ vorzugt sind die schlitzförmigen Löcher 100 und 110 innerhalb der der Hinterkante 40 zugewandten Hälfte A der druckseitigen Schaufelwand 30 angeordnet. In the figure 3, the pressure-side blade wall 30 Tur ¬ binenschaufel shown of 10 according to Figures 1 and 2 in the plan view in further detail. It can be seen that the blade ¬ wall 30 has two slotted holes 100 and 110 has. The slot-shaped holes can serve as drainage slots and / or heating openings, with which water is removed from the near-wall flow of the turbine flowing through the flow medium. As can be clearly seen in FIG. 3, the arrangement of the slot-shaped holes 100 and 110 is selected such that they are as close as possible to the trailing edge 40, ie the leading edge 50 as far as possible. Particularly be ¬ vorzugt the slot-shaped holes 100 and 110 are arranged within the trailing edge 40 facing half A of the pressure-side blade wall 30th

Die Figur 4 zeigt beispielhaft die saugseitige Schaufelwand 20 der Turbinenschaufel 10. Man erkennt, dass im Bereich der Vorderkante 50 ein schlitzförmiges Loch 120 angeordnet ist, das sich durch die Schaufelwand 20 hindurch erstreckt. Beson¬ ders bevorzugt ist das schlitzförmige Loch 120 innerhalb der der Vorderkante 50 zugewandten Hälfte B der saugseitigen Schaufelwand 20 angeordnet. Die innerhalb der Turbinenschau- fei 10 angeordnete Gitterstruktur 60 kann außerhalb des schlitzförmigen Lochs 120 angeordnet sein oder sich alternativ in das schlitzförmige Loch 120 hinein erstrecken. In der Figur 5 ist ein Ausführungsbeispiel gezeigt, bei dem sich die Gitterstruktur 60 vollständig in ein Loch 200 der Schaufelwand 210 der Turbinenschaufel 10 hineinerstreckt. Das Loch 200 wird somit durch die Gitterstruktur 60 überbrückt und durch diese abgestützt. FIG. 4 shows by way of example the suction-side blade wall 20 of the turbine blade 10. It can be seen that a slot-shaped hole 120 which extends through the blade wall 20 is arranged in the region of the front edge 50. Specifics ¬ DERS preferably, the slit-shaped hole 120 within which the leading edge 50 facing half B of the suction-side blade wall 20. The grid structure 60 disposed within the turbine window 10 may be disposed outside of the slot-shaped hole 120 or alternatively extend into the slot-shaped hole 120. FIG. 5 shows an embodiment in which the lattice structure 60 extends completely into a hole 200 of the blade wall 210 of the turbine blade 10. The hole 200 is thus bridged by the grid structure 60 and supported by this.

In der Figur 6 ist beispielhaft eine Ausführungsform gezeigt, bei der sich die Gitterstruktur 60 nur teilweise in das Loch 200 hineinerstreckt. Bei dem Ausführungsbeispiel gemäß Figur 6 wird circa die Hälfte der Wandstärke d von der Gitterstruk¬ tur 60 erfasst; die andere Hälfte der Wandstärke bleibt von der Gitterstruktur 60 frei. FIG. 6 shows by way of example an embodiment in which the grating structure 60 extends only partially into the hole 200. In the embodiment according to figure 6 approximately half the wall thickness d of the grating structural ¬ tur 60 is detected; the other half of the wall thickness remains free of the grid structure 60.

In der Figur 7 ist ein Ausführungsbeispiel für ein Loch 200 gezeigt, das überhaupt nicht mit einer Gitterstruktur 60 ver¬ sehen ist. Die Gitterstruktur 60 erstreckt sich nur bis an den unteren Rand 220 des Lochs 200 heran bzw. grenzt an das Loch 200 an, ohne dabei in das Loch selbst hineinzuragen. Die Gitterstruktur 60 befindet sich also nur innerhalb der Turbi- nenschaufel und nicht im Bereich des Lochs 200. In the figure 7 an embodiment of a hole 200 is shown, which is not ver see ¬ with a grating structure 60th The grid structure 60 extends only to the lower edge 220 of the hole 200 and adjoins the hole 200 without protruding into the hole itself. The lattice structure 60 is therefore located only within the turbine blade and not in the region of the hole 200.

Claims

Patentansprüche claims 1. Verfahren zum Herstellen einer Turbinenschaufel (10), d a d u r c h g e k e n n z e i c h n e t , dass 1. A method for producing a turbine blade (10), characterized in that die Turbinenschaufel durch ein additives Herstellungsverfah¬ ren hergestellt wird. the turbine blade is produced by an additive Herstellungsverfah ¬ ren. 2. Verfahren nach Anspruch 1, 2. The method according to claim 1, d a d u r c h g e k e n n z e i c h n e t , dass d a d u r c h e c e n c i n e s that die Turbinenschaufel schichtweise hergestellt wird, the turbine blade is produced in layers, indem eine erste Pulverschicht mittels eines Energiestrah¬ les lokal unter Bildung einer ersten Schaufelschicht ge¬ schmolzen wird und by locally melting a first powder layer by means of an energy beam, thereby forming a first blade layer , and indem darauf Schicht für Schicht weitere Pulverschichten aufgebracht und jeweils lokal geschmolzen und anschließend unter Bildung weiterer Schaufelschichten abgekühlt werden.  by applying thereto further powder layers layer by layer and in each case locally melted and then cooled to form further blade layers. 3. Verfahren nach einem der voranstehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t , dass 3. Method according to one of the preceding claims, characterized in that die Turbinenschaufel durch selektives Laserschmelzen herge¬ stellt wird. is the turbine blade Herge ¬ represents by selective laser melting. 4. Verfahren nach einem der voranstehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t , dass 4. Method according to one of the preceding claims, characterized in that als Turbinenschaufel eine Laufschaufei , eine statische Leit¬ schaufel oder eine Kompressorschaufel für einen Kompressorab¬ schnitt einer Turbine hergestellt wird. as a turbine blade having a rotor blade, a static routing ¬ blade or a compressor blade for a Kompressorab ¬ section of a turbine is made. 5. Verfahren nach einem der voranstehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t , dass 5. Method according to one of the preceding claims, characterized in that zwischen einer druckseitigen Schaufelwand (30) und einer saugseitigen Schaufelwand (20) ein Hohlraum (55) gebildet wird, der zumindest abschnittsweise mit einer Gitterstruktur (60) gefüllt wird. between a pressure-side blade wall (30) and a suction-side blade wall (20), a cavity (55) is formed, which is at least partially filled with a grid structure (60). 6. Verfahren nach Anspruch 5, 6. The method according to claim 5, d a d u r c h g e k e n n z e i c h n e t , dass d a d u r c h e c e n c i n e s that die Gitterstruktur topologisch optimiert ist und beispiels- weise eine lokal unterschiedliche Strukturierung und/oder lo¬ kal unterschiedliche Stabdurchmesser aufweist. the lattice structure is topologically optimized and, for example, has locally different structuring and / or lo ¬ cal different bar diameters. 7. Verfahren nach Anspruch 5 oder 6, 7. The method according to claim 5 or 6, d a d u r c h g e k e n n z e i c h n e t , dass d a d u r c h e c e n c i n e s that die saugseitige Schaufelwand und die druckseitige Schaufel¬ wand durch die Gitterstruktur miteinander verbunden werden. the suction-side blade wall and the pressure-side blade ¬ wall are interconnected by the grid structure. 8. Verfahren nach einem der voranstehenden Ansprüche, d a d u r c h g e k e n n z e i c h n e t , dass 8. The method according to any one of the preceding claims, d a d u r c h e c e n e c e s in that e in der Turbinenschaufel durch das additive Herstellungsver¬ fahren zumindest ein Loch (200), beispielsweise in Form eines Entwässerungsschlitzes oder einer Beheizungsöffnung, in mindestens einer Schaufelwand hergestellt wird. in the turbine blade by the additive Herstellungsver ¬ drive at least one hole (200), for example in the form of a dewatering slit or a heating opening is produced in at least one blade wall. 9. Verfahren nach Anspruch 8, 9. The method according to claim 8, d a d u r c h g e k e n n z e i c h n e t , dass d a d u r c h e c e n c i n e s that das Loch zumindest teilweise mit einer Gitterstruktur verse¬ hen wird. the hole is at least partially with a grating structure shipping ¬ hen. 10. Turbinenschaufel (10), 10. turbine blade (10), d a d u r c h g e k e n n z e i c h n e t , dass d a d u r c h e c e n c i n e s that zwischen den Schaufelwänden der Turbinenschaufel ein Hohlraum (55) vorhanden ist, der zumindest abschnittsweise mit einer Gitterstruktur (60) gefüllt ist. between the blade walls of the turbine blade a cavity (55) is present, which is at least partially filled with a grid structure (60). 11. Turbinenschaufel nach Anspruch 10, 11. turbine blade according to claim 10, d a d u r c h g e k e n n z e i c h n e t , dass d a d u r c h e c e n c i n e s that die Turbinenschaufel eine Laufschaufei , eine statische Leitschaufel oder eine Kompressorschaufel ist und die saugseitige Schaufelwand der Turbinenschaufel und die druckseitige Schaufelwand der Turbinenschaufel durch die Gitterstruktur miteinander verbunden sind. the turbine blade is a rotor blade, a static vane or a compressor blade and the suction-side blade wall of the turbine blade and the pressure-side blade wall of the turbine blade are interconnected by the grid structure. 12. Turbine, insbesondere Gasturbine oder Dampfturbine, mit zumindest einer Turbinenschaufel nach einem der voranstehenden Ansprüche 10 oder 11. 12. Turbine, in particular gas turbine or steam turbine, with at least one turbine blade according to one of the preceding claims 10 or 11. 13. Turbine nach Anspruch 12, 13. Turbine according to claim 12, d a d u r c h g e k e n n z e i c h n e t , dass d a d u r c h e c e n c i n e s that die Turbinenschaufel eine Laufschaufei , eine statische Leit¬ schaufel oder eine Kompressorschaufel der Turbine bildet. the turbine blade is a rotor blade, a static routing ¬ blade or a compressor blade of the turbine.
EP10754483A 2009-09-28 2010-09-14 Turbine blade and method for the production thereof Withdrawn EP2483019A2 (en)

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