EP3280879A1 - Arrangement for a turbine - Google Patents

Arrangement for a turbine

Info

Publication number
EP3280879A1
EP3280879A1 EP16726577.6A EP16726577A EP3280879A1 EP 3280879 A1 EP3280879 A1 EP 3280879A1 EP 16726577 A EP16726577 A EP 16726577A EP 3280879 A1 EP3280879 A1 EP 3280879A1
Authority
EP
European Patent Office
Prior art keywords
arrangement
segments
support
recess
segment
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP16726577.6A
Other languages
German (de)
French (fr)
Other versions
EP3280879B1 (en
Inventor
Bernd Burbaum
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 Energy Global GmbH and Co KG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to PL16726577T priority Critical patent/PL3280879T3/en
Publication of EP3280879A1 publication Critical patent/EP3280879A1/en
Application granted granted Critical
Publication of EP3280879B1 publication Critical patent/EP3280879B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
    • 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
    • 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
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • 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
    • F01D5/284—Selection of ceramic materials
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • F05D2230/311—Layer deposition by torch or flame spraying
    • 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
    • F05D2230/50—Building or constructing in particular ways
    • F05D2230/51—Building or constructing in particular ways in a modular way, e.g. using several identical or complementary parts or features
    • 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
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6032—Metal matrix composites [MMC]
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/614—Fibres or filaments

Definitions

  • the invention relates to an arrangement for a flow ⁇ machine, in particular a turbine, such as a gas turbine, comprising a metallic support structure having at least one extending in a radial direction support strut, and a plurality of on the support structure
  • Segments that together define the peripheral contour of the assembly wherein the segments are provided with through holes through which extends the at least one support strut. Furthermore, the present invention relates to a method for producing such an arrangement.
  • Blade assembly with an airfoil, which consists of a plurality of superimposed in the radial direction, plate-shaped and made of a ceramic fiber composite material airfoil segments.
  • the individual airfoil segments each comprise mutually aligned passage openings through which support struts extend, for example in the form of metallic tie rods, which press the airfoil segments against each other, whereby a frictional connection is created between the airfoil segments, which holds them together.
  • a prob lem ⁇ such a blade structure consists DA rin that the blade segments to move transversely relative to the radial direction to each other in spite of the forces acting on this radial pressure forces in one direction.
  • interlocking projections and recesses may be provided on the upper and lower sides of the individual airfoil segments, which, however, is associated with very great expense in terms of production engineering.
  • Another disadvantage associated with the use of tie rods is that those passageways through which a tie rod extends can not normally be used as cooling channels, which would be desirable in principle.
  • the present invention provides an arrangement of the type mentioned, which is characterized in that at least one, for example, some support strut has at least one outwardly projecting, transversely to the radial direction extending projection in at least one of the segments at least a correspondingly shaped recess can engage or grip.
  • Support struts provided, as well as a plurality of
  • Recesses for example, some recesses into which the projections are designed to grip.
  • the present invention can provide a blade assembly of the type mentioned, which is characterized in that the at least one
  • Support strut outwardly projecting, extending transversely to the radial direction extending projections, which formed in corresponding to the blade segments
  • Recesses work. Thanks to such projections and recesses segments are connected directly to the at least one support strut without the use geson ⁇ derter fastener, creating a Relative movement of the respective segments in a direction transverse to the radial direction is effectively prevented.
  • the support structure on a plurality of support struts in particular three support struts, which of course a deviating number of support struts may be provided.
  • a very stable arrangement is achieved by providing a plurality of support struts.
  • the at least one support strut has a non-circular cross section, in particular a cross section, which follows the peripheral contour of the arrangement.
  • a non-circular cross section in particular a cross section, which follows the peripheral contour of the arrangement.
  • Such a choice of the cross section is also very beneficial to the stability of the arrangement.
  • the at least one support strut is hollow Indianabil ⁇ det.
  • a cooling fluid can be passed through the support strut during the intended use of the arrangement, so that the at least one support strut defines a cooling channel.
  • the support structure has a platform extending substantially parallel to the segments, from which the at least one support strut protrudes radially outwards, wherein the
  • Segments are stacked on the platform.
  • Platform connects to one another, the support struts with each other, if several support struts are provided.
  • the platform defines a defined underground on which the segments can be stacked.
  • such a platform can be provided with a blade root or eintei ⁇ lig can be formed with one which serves for fastening the arrangement to a turbine component.
  • a defined annular gap is formed between the at least one support strut and those passage openings of the segments through which it extends.
  • One such annular gap in the event that the segments thermally expand during the intended use of the arrangement, sufficient space available to avoid the formation of harmful thermal stresses.
  • the recesses each extend from an upper side of the respective segment. This has the consequence that the projections can be easily finished, as explained in more detail below.
  • the at least one recess or some or more recesses are formed in the form of chamfers, which extend, for example, along the circumference of a passage opening.
  • Plurality of the projections substantially form-fitting received in the corresponding recess or the recesses. In this way, a particularly good cohesion between the at least one support strut and the segments is achieved.
  • each segment is provided with at least one recess into which an associated projection engages or can engage.
  • each segment is connected to the at least one support strut.
  • the outer surfaces of the at least one segment or the segments are provided with a coating, in particular with a thermal barrier coating.
  • the arrangement is an arrangement for a turbine blade, in particular an airfoil, or an arrangement for a hot gas-impacted part for the turbine.
  • the arrangement may include an airfoil assembly for a
  • Turbine in particular a gas turbine, be.
  • the arrangement can furthermore be a ring segment arrangement for a turbine, in particular a gas turbine.
  • the arrangement may further be an arrangement for another part in the gas and / or vapor path of a turbine, for example a hot gas-impacted part of a gas turbine.
  • Support structure can be produced using a generative process. This may be, for example, an SLM (Selective Laser Melting) method, a flame spraying method, a high-speed flame spraying method or also a build-up welding method, to name just a few examples.
  • SLM Selective Laser Melting
  • the projections which engage in the recesses can be readily manufactured.
  • the realization of a positive connection between the projections and the recesses provides
  • the stacking of the segments is done using a robot. In this way, the entire
  • Manufacturing process of the arrangement can be performed with a high level of automation ⁇ s istsgrad.
  • the outer surfaces of the segments are provided with a coating, in particular with a thermal barrier coating, wherein the coating is advantageously provided subsequently.
  • Figure 3 is a schematic plan view of a Platt ⁇ form a support structure of the arrangement shown in Figure 1 and
  • Figures 4 to 7 are schematic sectional views, on the basis of which the production of the arrangement shown in Figure 1 using a method according to an embodiment of the present invention will be explained.
  • Figures 1 to 3 show an arrangement 1 according to a
  • the arrangement 1 is such for a turbine, in particular a gas turbine, wherein the arrangement 1 in principle both as Laufschaufei, as
  • the assembly 1 comprises as main components a metallic support structure with a platform 2 and three support struts 3, 4 and 5 extending in a radial direction R from the platform 2, and a plurality of segments 6 superimposed on the support structure and plate-shaped that together define the perimeter contour of the array.
  • the support structure which primarily serves to absorb and dissipate the forces acting on it during the intended use of the arrangement 1, is made of a metallic material, such as a nickel-based alloy, to name only one example.
  • the platform 2 comprises a generally convex suction side 7 and a substantially concave pressure side 8, and in principle other geometries are mög ⁇ Lich.
  • the platform 2 can be a prefabricated component that has been produced, for example, by means of casting and subsequent mechanical processing.
  • the platform 2 can also be produced using a generative manufacturing method, as in ⁇ example, by means of an SLM method, of course, other generative manufacturing methods are possible.
  • the support struts 3,4 and 5 are manufactured using a generative manufacturing process and firmly connected to the platform 2, as will be explained in more detail below. They extend from the platform 2 substantially parallel to each other, are hollow and have vorlie ⁇ ing each on a non-circular cross-section, which follows the circumferential contour of the arrangement in the present case. At the level of the upper edge of each segment 6, the support struts 3,4 and 5 are each circumferentially provided with outwardly projecting, extending transversely to the radial direction projections 9.
  • the segments 6 are each made of a ceramic fiber ⁇ composite.
  • a ceramic Faserver ⁇ composite material may, for example Al 2 O 3 2O 3 / Al 2 O 3, C / SiC,
  • the segments 6 comprise a suction side 10 and a pressure side 11, wherein the outer contours of adjacently arranged segments 6 are preferably aligned with one another, just as in the present case the outer contour of the platform 2 is aligned with the outer contour of the adjacently arranged segment 6.
  • the segments 6 are each ver ⁇ see with three through holes 12 through which the respective support struts 3,4 and 5 extend. Between the segments 6 and the support struts 3, 4 and 5, a defined annular gap can be left, which is interrupted only by the projections 9. Such an annular gap can during the intended use of
  • Arrangement 1 to be advantageous in that in the case of thermal expansion of the support struts 3,4 and 5 and / or the segments 6, an appropriate escape space is created, which reduces or prevents the occurrence of thermal stresses.
  • bevel-shaped recesses 13 are provided, which extend along the edge regions of the respective through holes 12. In these recesses 13 engage positively by the support struts 3,4 and 5 protruding projections 9, so that each segment 6 is fixedly connected to the support struts 3,4 and 5.
  • the platform 2 of the support structure is arranged on the ground. Then the platform 2 is a segment 6 so positio ⁇ ned that the outer contour of the segment 6 is aligned with the outer contour ⁇ of the platform 2. The positioning of the
  • Segmentes can be done using a robot, even if this is not shown here.
  • FIG. 4 shows, in this connection, schematically a nozzle arrangement 14, with which powdered metallic material is directed in the direction of the platform 2 and melted down using a laser. It should be clear that in principle any generative LMD process (laser metal deposition) can be used.
  • metallic cover layer can be arranged, which can be provided with cooling fluid outlet holes and manufactured, for example by means of build-up welding. Alternatively, a prefabricated cover layer can also be fixed to the metallic support structure by means of high-temperature soldering or the like. Furthermore, the arrangement 1 shown in Figure 1 can be provided with a coating, for example with a thermal barrier coating, if desired.
  • An essential advantage of the method according to the invention is that in the production of a hybrid arrangement 1, the individual segments 6 are firmly and securely connected to the support structure in all spatial directions, without requiring separate fastening means for this purpose.
  • each segment may be provided with a recess, it is sufficient for the
  • the gripping connection through the projections and the recesses in the center of the arrangement or in every third or fourth stacked segment of the arrangement may be sufficient to utilize the advantages according to the invention.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • Architecture (AREA)
  • Manufacturing & Machinery (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention relates to an arrangement (1) for a turbine comprising a metallic support structure having at least one radial support strut (3, 4, 5) and a multiplicity of plate-shaped, fiber-reinforced ceramic segments (6) which are arranged one on top of the other on the support structure and together define the circumferential contour, the segments (6) being provided with through-openings (12) through which the at least one support strut (3, 4, 5) extends, wherein the at least one support strut (3, 4, 5) has outwardly-extending projections (9) that extend perpendicular to the radial direction and engage in corresponding recesses (13) formed in the segments (6).

Description

Anordnung für eine Turbine Arrangement of a turbine
Die Erfindung betrifft eine Anordnung für eine Strömungs¬ maschine, insbesondere eine Turbine, wie eine Gasturbine, umfassend eine metallische Stützstruktur, die zumindest eine sich in einer radialen Richtung erstreckende Stützstrebe aufweist, und eine Vielzahl von an der Stützstruktur The invention relates to an arrangement for a flow ¬ machine, in particular a turbine, such as a gas turbine, comprising a metallic support structure having at least one extending in a radial direction support strut, and a plurality of on the support structure
übereinander angeordneten, plattenförmig ausgebildeten und aus einem keramischen Faserverbundwerkstoff herstellten arranged one above the other, formed plate-shaped and made of a ceramic fiber composite material
Segmenten, die gemeinsam die Umfangskontur der Anordnung definieren, wobei die Segmente mit Durchgangsöffnungen versehen sind, durch die sich die zumindest eine Stützstrebe erstreckt. Ferner betrifft die vorliegende Erfindung ein Verfahren zum Herstellen einer solchen Anordnung. Segments that together define the peripheral contour of the assembly, wherein the segments are provided with through holes through which extends the at least one support strut. Furthermore, the present invention relates to a method for producing such an arrangement.
Anordnungen der eingangs genannten Art sind im Stand der Technik in unterschiedlichsten Ausgestaltungen bekannt. So offenbart beispielsweise die US 2006/00120871 AI eine Arrangements of the type mentioned are known in the prior art in a variety of configurations. For example, US 2006/00120871 A1 discloses a
Schaufelanordnung mit einem Schaufelblatt, das aus einer Vielzahl von in radialer Richtung übereinander angeordneten, plattenförmig ausgebildeten und aus einem keramischen Faserverbundwerkstoff hergestellten Schaufelblattsegmenten besteht. Die einzelnen Schaufelblattsegmente umfassen jeweils miteinander fluchtende Durchgangsöffnungen, durch die sich Stützstreben erstrecken, beispielsweise in Form von metallischen Zugankern, welche die Schaufelblattsegmente gegeneinan¬ der drücken, wodurch zwischen den Schaufelblattsegmenten ein Kraftschluss erzeugt wird, der diese zusammenhält. Ein Prob¬ lem eines derartigen Schaufelaufbaus besteht allerdings da- rin, dass sich die Schaufelblattsegmente trotz der auf diese einwirkenden radialen Druckkräfte in einer Richtung quer zur radialen Richtung relativ zueinander verschieben können. Entsprechend kann es erforderlich sein, ergänzende Mittel vorzu¬ sehen, um derartige Relativbewegungen zu verhindern. So kön- nen beispielsweise an den Ober- und Unterseiten der einzelnen Schaufelblattsegmente ineinander greifende Vorsprünge und Aussparungen vorgesehen werden, was fertigungstechnisch allerdings mit einem sehr großen Aufwand verbunden ist. In diesem Zusammenhang sei beispielhaft auf die US 2006/0120874 AI verwiesen. Ein weiterer Nachteil, der mit der Verwendung von Zugankern einhergeht, besteht darin, dass diejenigen Durchgangsöffnungen, durch die sich ein Zuganker erstreckt, normalerweise nicht als Kühlkanäle verwendet werden können, was grundsätzlich wünschenswert wäre. Blade assembly with an airfoil, which consists of a plurality of superimposed in the radial direction, plate-shaped and made of a ceramic fiber composite material airfoil segments. The individual airfoil segments each comprise mutually aligned passage openings through which support struts extend, for example in the form of metallic tie rods, which press the airfoil segments against each other, whereby a frictional connection is created between the airfoil segments, which holds them together. However, a prob lem ¬ such a blade structure consists DA rin that the blade segments to move transversely relative to the radial direction to each other in spite of the forces acting on this radial pressure forces in one direction. Accordingly, it may be necessary vorzu complementary means see ¬ to prevent such relative movements. Thus, for example, interlocking projections and recesses may be provided on the upper and lower sides of the individual airfoil segments, which, however, is associated with very great expense in terms of production engineering. In In this context, reference is made by way of example to US 2006/0120874 AI. Another disadvantage associated with the use of tie rods is that those passageways through which a tie rod extends can not normally be used as cooling channels, which would be desirable in principle.
Ausgehend von diesem Stand der Technik ist es eine Aufgabe der vorliegenden Erfindung, eine Anordnung der eingangs genannten Art mit alternativem Aufbau zu schaffen. Based on this prior art, it is an object of the present invention to provide an arrangement of the type mentioned above with an alternative structure.
Zur Lösung dieser Aufgabe schafft die vorliegende Erfindung eine Anordnung der eingangs genannten Art, die dadurch gekennzeichnet ist, dass zumindest eine, beispielsweise einige, Stützstrebe mindestens einen auswärts vorstehenden, sich quer zur radialen Richtung erstreckenden Vorsprung aufweist, der in an mindestens einem der Segmente mindestens eine korrespondierend ausgebildete Aussparung greift oder greifen kann. To achieve this object, the present invention provides an arrangement of the type mentioned, which is characterized in that at least one, for example, some support strut has at least one outwardly projecting, transversely to the radial direction extending projection in at least one of the segments at least a correspondingly shaped recess can engage or grip.
Vorzugsweise sind entsprechend sowohl eine Mehrzahl von Preferably, both a plurality of
Vorsprüngen, beispielsweise einige Vorsprünge, an den Projections, for example, some projections to the
Stützstreben vorgesehen, als auch eine Mehrzahl von Support struts provided, as well as a plurality of
Aussparungen, beispielsweise einige Aussparungen, in die die Vorsprünge zu greifen ausgebildet sind. Recesses, for example, some recesses into which the projections are designed to grip.
Zur Lösung dieser Aufgabe kann die vorliegende Erfindung eine Schaufelanordnung der eingangs genannten Art schaffen, die dadurch gekennzeichnet ist, dass die zumindest eine To achieve this object, the present invention can provide a blade assembly of the type mentioned, which is characterized in that the at least one
Stützstrebe auswärts vorstehende, sich quer zur radialen Richtung erstreckende Vorsprünge aufweist, die in an den Schaufelblattsegmenten korrespondierend ausgebildete Support strut outwardly projecting, extending transversely to the radial direction extending projections, which formed in corresponding to the blade segments
Aussparungen greifen. Dank derartiger Vorsprünge und Aussparungen werden Segmente mit der zumindest einen Stützstrebe ohne den Einsatz geson¬ derter Befestigungsmittel direkt verbunden, wodurch eine Relativbewegung der entsprechenden Segmente in einer Richtung quer zur radialen Richtung effektiv verhindert wird. Recesses work. Thanks to such projections and recesses segments are connected directly to the at least one support strut without the use geson ¬ derter fastener, creating a Relative movement of the respective segments in a direction transverse to the radial direction is effectively prevented.
Gemäß einer Ausgestaltung der vorliegenden Erfindung weist die Stützstruktur mehrere Stützstreben auf, insbesondere drei Stützstreben, wobei natürlich auch eine hiervon abweichende Anzahl von Stützstreben vorgesehen sein kann. Insgesamt wird durch das Vorsehen mehrerer Stützstreben eine sehr stabile Anordnung erzielt. According to one embodiment of the present invention, the support structure on a plurality of support struts, in particular three support struts, which of course a deviating number of support struts may be provided. Overall, a very stable arrangement is achieved by providing a plurality of support struts.
Bevorzugt weist die zumindest eine Stützstrebe einen unrunden Querschnitt auf, insbesondere einen Querschnitt, welcher der Umfangskontur der Anordnung folgt. Eine derartige Wahl des Querschnittes ist der Stabilität der Anordnung ebenfalls sehr zuträglich. Preferably, the at least one support strut has a non-circular cross section, in particular a cross section, which follows the peripheral contour of the arrangement. Such a choice of the cross section is also very beneficial to the stability of the arrangement.
Vorteilhaft ist die zumindest eine Stützstrebe hohl ausgebil¬ det. In diesem Fall kann während der bestimmungsgemäßen Verwendung der Anordnung durch die Stützstrebe ein Kühlfluid geleitet werden, so dass die zumindest eine Stützstrebe einen Kühlkanal definiert. Advantageously, the at least one support strut is hollow ausgebil ¬ det. In this case, a cooling fluid can be passed through the support strut during the intended use of the arrangement, so that the at least one support strut defines a cooling channel.
Gemäß einer Ausgestaltung der vorliegenden Erfindung weist die Stützstruktur eine sich im Wesentlichen parallel zu den Segmenten erstreckende Plattform auf, von der die zumindest eine Stützstrebe radial auswärts hervorsteht, wobei die According to one embodiment of the present invention, the support structure has a platform extending substantially parallel to the segments, from which the at least one support strut protrudes radially outwards, wherein the
Segmente auf der Plattform gestapelt sind. Eine solche Segments are stacked on the platform. Such
Plattform verbindet zum einen die Stützstreben miteinander, wenn mehrere Stützstreben vorgesehen sind. Zum anderen defi- niert die Plattform einen definierten Untergrund, auf den die Segmente gestapelt werden können. Darüber hinaus kann eine solche Plattform mit einem Schaufelfuß versehen oder eintei¬ lig mit einem solchen ausgebildet werden, der zur Befestigung der Anordnung an einer Turbinenkomponente dient. Platform connects to one another, the support struts with each other, if several support struts are provided. On the other hand, the platform defines a defined underground on which the segments can be stacked. In addition, such a platform can be provided with a blade root or eintei ¬ lig can be formed with one which serves for fastening the arrangement to a turbine component.
Bevorzugt ist zwischen der zumindest einen Stützstrebe und denjenigen Durchgangsöffnungen der Segmente, durch die sich diese erstreckt, ein definierter Ringspalt ausgebildet. Ein solcher Ringspalt stellt für den Fall, dass sich die Segmente während der bestimmungsgemäßen Verwendung der Anordnung thermisch ausdehnen, ausreichend Raum zur Verfügung, um die Entstehung schädlicher thermischer Spannungen zu vermeiden. Preferably, a defined annular gap is formed between the at least one support strut and those passage openings of the segments through which it extends. One such annular gap, in the event that the segments thermally expand during the intended use of the arrangement, sufficient space available to avoid the formation of harmful thermal stresses.
Gemäß einer Ausgestaltung der vorliegenden Erfindung erstrecken sich die Aussparungen jeweils ausgehend von einer Oberseite des jeweiligen Segments. Dies hat zur Folge, dass sich die Vorsprünge einfach fertigen lassen, wie es nachfolgend noch näher erläutert ist. According to one embodiment of the present invention, the recesses each extend from an upper side of the respective segment. This has the consequence that the projections can be easily finished, as explained in more detail below.
Bevorzugt sind die mindestens eine Aussparung oder einige oder mehrere Aussparungen in Form von Fasen ausgebildet, die sich beispielsweise entlang des Umfangs einer Durch- gangsöffnung erstrecken. Preferably, the at least one recess or some or more recesses are formed in the form of chamfers, which extend, for example, along the circumference of a passage opening.
Vorteilhaft ist der mindestens eine Vorsprung oder die Advantageously, the at least one projection or the
Mehrzahl der Vorsprünge im Wesentlichen formschlüssig in der entsprechenden Aussparung bzw. den Aussparungen aufgenommen. Auf diese Weise wird ein besonders guter Zusammenhalt zwischen der zumindest einen Stützstrebe und den Segmenten erzielt . Plurality of the projections substantially form-fitting received in the corresponding recess or the recesses. In this way, a particularly good cohesion between the at least one support strut and the segments is achieved.
Bevorzugt ist jedes Segment mit zumindest einer Aussparung versehen, in die ein zugeordneter Vorsprung greift oder greifen kann. Mit anderen Worten ist bei dieser Ausgestaltung jedes Segment mit der zumindest einen Stützstrebe verbunden. Preferably, each segment is provided with at least one recess into which an associated projection engages or can engage. In other words, in this embodiment, each segment is connected to the at least one support strut.
Gemäß einer Variante der vorliegenden Erfindung sind die Au- ßenflächen des mindestens einen Segments bzw. der Segmente mit einer Beschichtung versehen, insbesondere mit einer Wärmebarrierebeschichtung . According to a variant of the present invention, the outer surfaces of the at least one segment or the segments are provided with a coating, in particular with a thermal barrier coating.
Gemäß einer Ausgestaltung ist die Anordnung eine Anordnung für eine Turbinenschaufel, insbesondere ein Schaufelblatt, oder eine Anordnung für ein heißgasbeaufSchlagtes Teil für die Turbine. Die Anordnung kann eine Schaufelblattanordnung für eine According to one embodiment, the arrangement is an arrangement for a turbine blade, in particular an airfoil, or an arrangement for a hot gas-impacted part for the turbine. The arrangement may include an airfoil assembly for a
Turbine, insbesondere eine Gasturbine, sein. Turbine, in particular a gas turbine, be.
Die Anordnung kann weiterhin eine Ringsegment-Anordnung für eine Turbine, insbesondere eine Gasturbine, sein. The arrangement can furthermore be a ring segment arrangement for a turbine, in particular a gas turbine.
Die Anordnung kann weiterhin eine Anordnung für ein anderes Teil im Gas- und/oder Dampfpfad eine Turbine, beispielsweise ein heißgasbeaufSchlagtes Teil einer Gasturbine, sein. The arrangement may further be an arrangement for another part in the gas and / or vapor path of a turbine, for example a hot gas-impacted part of a gas turbine.
Zur Lösung der eingangs genannten Aufgabe schafft die vorlie¬ gende Erfindung ferner ein Verfahren zur Herstellung einer erfindungsgemäßen Anordnung, wobei das Verfahren dadurch gekennzeichnet ist, dass zumindest die Stützstreben der To achieve the aforementioned object of the products contained ¬ constricting invention further provides a method for producing an arrangement according to the invention, the method is characterized in that at least the support braces of
Stützstruktur unter Verwendung eines generativen Verfahrens hergestellt werden. Hierbei kann es sich beispielsweise um ein SLM-Verfahren ( Selective Laser Melting) , ein Flammspritzverfahren, ein Hochgeschwindigkeits-Flammspritzverfahren oder auch ein Auftragsschweißverfahren handeln, um nur einige Bei- spiele zu nennen. Support structure can be produced using a generative process. This may be, for example, an SLM (Selective Laser Melting) method, a flame spraying method, a high-speed flame spraying method or also a build-up welding method, to name just a few examples.
Vorteilhaft wechseln ein Stapeln der Segmente und eine schrittweise Herstellung der zumindest einen Stützstrebe einander derart ab, dass nach einem Anordnung eines mit einer Aussparung versehenen Segments ein Teilbereich der zumindest einen Stützstrebe einschließlich eines in die Aussparung greifenden Vorsprungs generiert wird. Auf diese Weise lassen sich die in die Aussparungen greifenden Vorsprünge ohne weiteres fertigen. Auch die Realisierung eines Formschlusses zwischen den Vorsprüngen und den Aussparungen stellt Advantageously, stacking of the segments and stepwise production of the at least one support strut alternate with one another in such a way that, after an arrangement of a segment provided with a recess, a subregion of the at least one support strut including a projection engaging in the recess is generated. In this way, the projections which engage in the recesses can be readily manufactured. Also, the realization of a positive connection between the projections and the recesses provides
keinerlei Probleme dar. no problems.
Bevorzugt erfolgt das Stapeln der Segmente unter Verwendung eines Roboters. Auf diese Weise kann der gesamte Preferably, the stacking of the segments is done using a robot. In this way, the entire
Herstellungsprozess der Anordnung mit hohem Automati¬ sierungsgrad durchgeführt werden. Vorteilhaft werden die Außenflächen der Segmente mit einer Beschichtung versehen, insbesondere mit einer Wärmebarriere- beschichtung, wobei die Beschichtung vorteilhaft nachträglich vorgesehen wird. Manufacturing process of the arrangement can be performed with a high level of automation ¬ sierungsgrad. Advantageously, the outer surfaces of the segments are provided with a coating, in particular with a thermal barrier coating, wherein the coating is advantageously provided subsequently.
Weitere Merkmale und Vorteile der vorliegenden Erfindung werden anhand der nachfolgenden Beschreibung einer Anordnung gemäß einer Ausführungsform der vorliegenden Erfindung unter Bezugnahme auf die beiliegende Zeichnung deutlich. Darin ist/sind: eine schematische perspektivische Ansicht einer Anordnung gemäß einer Ausführungsform der vorliegenden Erfindung; eine schematische Draufsicht eines Further features and advantages of the present invention will become apparent from the following description of an arrangement according to an embodiment of the present invention with reference to the accompanying drawings. Therein: a schematic perspective view of an arrangement according to an embodiment of the present invention; a schematic plan view of a
Segmentes der in Figur 1 gezeigten  Segmentes shown in Figure 1
Anordnung; Figur 3 eine schematische Draufsicht einer Platt¬ form einer Stützstruktur der in Figur 1 gezeigten Anordnung und Arrangement; Figure 3 is a schematic plan view of a Platt ¬ form a support structure of the arrangement shown in Figure 1 and
Figuren 4 bis 7 schematische Schnittansichten, anhand derer die Herstellung der in Figur 1 gezeigten Anordnung unter Einsatz eines Verfahrens gemäß einer Ausführungsform der vorliegenden Erfindung erläutert wird . Figures 4 to 7 are schematic sectional views, on the basis of which the production of the arrangement shown in Figure 1 using a method according to an embodiment of the present invention will be explained.
Die Figuren 1 bis 3 zeigen eine Anordnung 1 gemäß einer Figures 1 to 3 show an arrangement 1 according to a
Ausführungsform der vorliegenden Erfindung bzw. Komponenten derselben. Bei der Anordnung 1 handelt es sich um eine solche für eine Turbine, insbesondere eine Gasturbine, wobei die Anordnung 1 grundsätzlich sowohl als Laufschaufei , als Embodiment of the present invention or components thereof. In the arrangement 1 is such for a turbine, in particular a gas turbine, wherein the arrangement 1 in principle both as Laufschaufei, as
Leitschaufel und/oder als ein Ringsegment oder ein anderes Teil im Gas- oder Dampfpfad einer Turbine ausgebildet sein kann, auch wenn dies vorliegend nicht näher dargestellt ist. Die Anordnung 1 umfasst als Hauptkomponenten eine metallische Stützstruktur mit einer Plattform 2 und drei Stützstreben 3,4 und 5, die sich ausgehend von der Plattform 2 in einer radialen Richtung R erstrecken, und eine Vielzahl von an der Stützstruktur übereinander angeordneten und plattenförmig ausgebildeten Segmenten 6, die gemeinsam die Umfangskontur der Anordnung definieren. Guide vane and / or may be formed as a ring segment or other part in the gas or vapor path of a turbine, although this is not shown in detail here. The assembly 1 comprises as main components a metallic support structure with a platform 2 and three support struts 3, 4 and 5 extending in a radial direction R from the platform 2, and a plurality of segments 6 superimposed on the support structure and plate-shaped that together define the perimeter contour of the array.
Die Stützstruktur, die in erster Linie dazu dient, während des bestimmungsgemäßen Einsatzes der Anordnung 1 die auf diese einwirkenden Kräfte aufzunehmen und abzuleiten, ist aus einem metallischen Werkstoff hergestellt, wie beispielsweise aus einer Nickel-Basis-Legierung, um nur ein Beispiel zu nennen. Die Plattform 2 weist eine im Wesentlichen konvex gewölbte Saugseite 7 und eine im Wesentlichen konkav gewölbte Druckseite 8 auf, wobei grundsätzlich andere Geometrien mög¬ lich sind. Bei der Plattform 2 kann es sich um ein vorgefertigtes Bauteil handeln, das beispielsweise mittels Gießen und anschließender mechanischer Bearbeitung hergestellt wurde. Alternativ kann die Plattform 2 auch unter Einsatz eines generativen Fertigungsverfahrens hergestellt sein, wie bei¬ spielsweise mittels eines SLM-Verfahrens , wobei natürlich auch andere generative Fertigungsverfahren möglich sind. Die Stützstreben 3,4 und 5 sind unter Einsatz eines generativen Fertigungsverfahrens hergestellt und fest mit der Plattform 2 verbunden, wie es nachfolgend noch näher erläutert ist. Sie erstrecken sich ausgehend von der Plattform 2 im Wesentlichen parallel zueinander, sind hohl ausgebildet und weisen vorlie¬ gend jeweils einen unrunden Querschnitt auf, der vorliegend der Umfangskontur der Anordnung folgt. Auf Höhe der Oberkante jedes Segmentes 6 sind die Stützstreben 3,4 und 5 jeweils umfänglich mit auswärts vorstehenden, sich quer zur radialen Richtung erstreckenden Vorsprüngen 9 versehen. Die Segmente 6 sind jeweils aus einem keramischen Faser¬ verbundwerkstoff hergestellt. Als keramischer Faserver¬ bundwerkstoff kann beispielsweise AI2O3 2O3/AI2O3, C/SiC, The support structure, which primarily serves to absorb and dissipate the forces acting on it during the intended use of the arrangement 1, is made of a metallic material, such as a nickel-based alloy, to name only one example. The platform 2 comprises a generally convex suction side 7 and a substantially concave pressure side 8, and in principle other geometries are mög ¬ Lich. The platform 2 can be a prefabricated component that has been produced, for example, by means of casting and subsequent mechanical processing. Alternatively, the platform 2 can also be produced using a generative manufacturing method, as in ¬ example, by means of an SLM method, of course, other generative manufacturing methods are possible. The support struts 3,4 and 5 are manufactured using a generative manufacturing process and firmly connected to the platform 2, as will be explained in more detail below. They extend from the platform 2 substantially parallel to each other, are hollow and have vorlie ¬ ing each on a non-circular cross-section, which follows the circumferential contour of the arrangement in the present case. At the level of the upper edge of each segment 6, the support struts 3,4 and 5 are each circumferentially provided with outwardly projecting, extending transversely to the radial direction projections 9. The segments 6 are each made of a ceramic fiber ¬ composite. As a ceramic Faserver ¬ composite material may, for example Al 2 O 3 2O 3 / Al 2 O 3, C / SiC,
SiC/SiC oder dergleichen verwendet werden, um nur einige Bei- spiele zu nennen. Analog zu der Plattform 2 umfassen die Segmente 6 eine Saugseite 10 und eine Druckseite 11, wobei die Außenkonturen benachbart angeordneter Segmente 6 bevorzugt miteinander fluchtend ausgebildet sind, ebenso wie vorliegend die Außenkontur der Plattform 2 mit der Außenkontur des benachbart angeordneten Segmentes 6 fluchten. Die Segmente 6 sind jeweils mit drei Durchgangsöffnungen 12 ver¬ sehen, durch die sich die jeweiligen Stützstreben 3,4 und 5 erstrecken. Zwischen den Segmenten 6 und den Stützstreben 3,4 und 5 kann ein definierter Ringspalt belassen sein, der nur von den Vorsprüngen 9 unterbrochen wird. Ein solcher Ringspalt kann während des bestimmungsgemäßen Einsatzes der SiC / SiC or the like, only a few examples to call games. Analogous to the platform 2, the segments 6 comprise a suction side 10 and a pressure side 11, wherein the outer contours of adjacently arranged segments 6 are preferably aligned with one another, just as in the present case the outer contour of the platform 2 is aligned with the outer contour of the adjacently arranged segment 6. The segments 6 are each ver ¬ see with three through holes 12 through which the respective support struts 3,4 and 5 extend. Between the segments 6 and the support struts 3, 4 and 5, a defined annular gap can be left, which is interrupted only by the projections 9. Such an annular gap can during the intended use of
Anordnung 1 dahingehend von Vorteil sein, dass im Fall thermischer Ausdehnungen der Stützstreben 3,4 und 5 und/oder der Segmente 6 ein angemessener Ausweichraum geschaffen wird, der das Auftreten thermischer Spannungen reduziert oder verhindert. Ausgehend von der Oberseite jedes Segmentes 6 sind umlaufende, fasenförmig ausgebildete Aussparungen 13 vorgesehen, die sich entlang der Randbereiche der jeweiligen Durchgangsöffnungen 12 erstrecken. In diese Aussparungen 13 greifen formschlüssig die von den Stützstreben 3,4 und 5 vorstehenden Vorsprünge 9 ein, so dass jedes Segment 6 fest mit den Stützstreben 3,4 und 5 verbunden ist. Zur Herstellung der in Figur 1 dargestellten Anordnung 1 wird in einem ersten Schritt, wie es in Figur 4 schematisch dargestellt ist, die Plattform 2 der Stützstruktur am Untergrund angeordnet. Daraufhin wird der Plattform 2 ein Segment 6 derart positio¬ niert, dass die Außenkontur des Segmentes 6 mit der Außen¬ kontur der Plattform 2 fluchtet. Die Positionierung des Arrangement 1 to be advantageous in that in the case of thermal expansion of the support struts 3,4 and 5 and / or the segments 6, an appropriate escape space is created, which reduces or prevents the occurrence of thermal stresses. Starting from the upper side of each segment 6 circumferential, bevel-shaped recesses 13 are provided, which extend along the edge regions of the respective through holes 12. In these recesses 13 engage positively by the support struts 3,4 and 5 protruding projections 9, so that each segment 6 is fixedly connected to the support struts 3,4 and 5. In order to produce the arrangement 1 shown in FIG. 1, in a first step, as shown schematically in FIG. 4, the platform 2 of the support structure is arranged on the ground. Then the platform 2 is a segment 6 so positio ¬ ned that the outer contour of the segment 6 is aligned with the outer contour ¬ of the platform 2. The positioning of the
Segmentes kann dabei unter Einsatz eines Roboters erfolgen, auch wenn dies vorliegend nicht dargestellt ist. Segmentes can be done using a robot, even if this is not shown here.
In einem weiteren Schritt werden entlang des Umfangs der jeweiligen Durchgangsöffnungen 12 auf der Plattform 2 unter Einsatz eines generativen Fertigungsverfahrens Teilbereiche der Stützstreben 3,4 und 5 bis zur Oberkante des Segmentes 6 schichtweise generiert, wobei auch die Aussparungen 13 unter Erzeugung der Vorsprünge 9 mit metallischem Material gefüllt werden, wie es in Figur 5 gezeigt ist. Figur 4 zeigt in diesem Zusammenhang schematisch eine Düsenanordnung 14, mit der pulvertörmiges metallisches Material in Richtung der Plattform 2 gerichtet und unter Einsatz eines Lasers aufge- schmolzen wird. Es sollte klar sein, dass grundsätzlich jedes generative LMD-Verfahren (Laser-Metal-Deposition) eingesetzt werden kann. In a further step, partial regions of the support struts 3, 4 and 5 up to the upper edge of the segment 6 are generated in layers along the circumference of the respective through openings 12 on the platform 2 using a generative manufacturing process, the recesses 13 also being metallic with the projections 9 being produced Material filled be as shown in Figure 5. FIG. 4 shows, in this connection, schematically a nozzle arrangement 14, with which powdered metallic material is directed in the direction of the platform 2 and melted down using a laser. It should be clear that in principle any generative LMD process (laser metal deposition) can be used.
In einem sich anschließenden Schritt wird, wie es in Figur 6 dargestellt ist, ein weiteres Segment 6 auf dem bereits an der Plattform 2 befestigten Segment 6 positioniert, woraufhin erneut Teilbereiche der Stützstreben 3,4 und 5 schichtweise generiert werden, siehe Figur 7. Die zuvor beschriebenen Schritte werden wiederholt, bis die in Figur 1 dargestellte Anordnung 1 fertiggestellt ist. Mit anderen Worten wechseln sich ein Stapeln der Segmente 6 und eine schrittweise In a subsequent step, as shown in Figure 6, another segment 6 positioned on the already attached to the platform 2 segment 6, whereupon again portions of the support struts 3,4 and 5 are generated in layers, see Figure 7. Die The above-described steps are repeated until the arrangement 1 shown in FIG. 1 is completed. In other words, stacking of the segments 6 and one stepwise alternate
Herstellung der Stützstreben 3,4 und 5 ab, wobei nach einem Anordnen eines mit einer Aussparung 13 versehenen Segments 6 jeweils ein Teilbereich der Stützstreben 3,4 und 5 Production of the support struts 3,4 and 5, wherein after arranging a provided with a recess 13 segment 6 each have a portion of the support struts 3,4 and 5
einschließlich eines in die Aussparung 13 greifenden including a cross in the recess 13
Vorsprungs 9 generiert wird. Projection 9 is generated.
Nach Fertigstellung der in Figur 1 dargestellten Anordnung 1 kann zur Ausbildung einer Schaufelspitze eine oberste After completion of the arrangement 1 shown in Figure 1 can form a blade tip a top
metallische Decklage angeordnet werden, die mit Kühl- fluidauslassbohrungen versehen und beispielsweise mittels Auftragsschweißen hergestellt sein kann. Alternativ kann eine vorgefertigte Decklage aber auch mittels Hochtemperaturlöten oder dergleichen an der metallischen Stützstruktur fixiert werden. Ferner kann die in Figur 1 dargestellte Anordnung 1 mit einer Beschichtung versehen werden, beispielsweise mit einer Wärmebarrierebeschichtung, wenn dies gewünscht ist. metallic cover layer can be arranged, which can be provided with cooling fluid outlet holes and manufactured, for example by means of build-up welding. Alternatively, a prefabricated cover layer can also be fixed to the metallic support structure by means of high-temperature soldering or the like. Furthermore, the arrangement 1 shown in Figure 1 can be provided with a coating, for example with a thermal barrier coating, if desired.
Ein wesentlicher Vorteil des erfindungsgemäßen Verfahrens be- steht darin, dass bei der Herstellung einer Hybrid-Anordnung 1 die einzelnen Segmente 6 in allen Raumrichtungen fest und sicher mit der Stützstruktur verbunden werden, ohne dass es hierzu gesonderter Befestigungsmittel bedarf. Obwohl in den Darstellungen der Figuren jedes Segment mit einer Aussparung versehen sein kann, reicht es für den An essential advantage of the method according to the invention is that in the production of a hybrid arrangement 1, the individual segments 6 are firmly and securely connected to the support structure in all spatial directions, without requiring separate fastening means for this purpose. Although in the representations of the figures, each segment may be provided with a recess, it is sufficient for the
Erfindungsgedanken aus, wenn dies nur für mindestens eines oder einige der Segmente, beispielsweise zwei, drei oder vier Segmente der Fall ist. Dementsprechend muss gemäß der Inventive concept, if this is the case for at least one or some of the segments, for example two, three or four segments. Accordingly, according to the
vorliegenden Erfindung auch nur mindestens eine entsprechende Stützstrebe bzw. die genannte Mehrzahl einen entsprechenden Vorsprung aufweisen. present invention, only at least one corresponding support strut or said plurality have a corresponding projection.
Beispielsweise kann die GreifVerbindung durch die Vorsprünge und die Aussparungen in der Mitte der Anordnung oder in jedem dritten oder vierten gestapelten Segment der Anordnung ausreichend sein, um die erfindungsgemäßen Vorteile zu nutzen. For example, the gripping connection through the projections and the recesses in the center of the arrangement or in every third or fourth stacked segment of the arrangement may be sufficient to utilize the advantages according to the invention.
Obwohl die Erfindung im Detail durch das bevorzugte Ausführungsbeispiel näher illustriert und beschrieben wurde, so ist die Erfindung nicht durch die offenbarten Beispiele einge- schränkt und andere Variationen können vom Fachmann hieraus abgeleitet werden, ohne den Schutzumfang der Erfindung zu verlassen . Although the invention has been further illustrated and described in detail by the preferred embodiment, the invention is not limited by the disclosed examples, and other variations can be derived therefrom by those skilled in the art without departing from the scope of the invention.

Claims

Patentansprüche claims
1. Anordnung (1) für eine Turbine, 1. arrangement (1) for a turbine,
umfassend eine metallische Stützstruktur,  comprising a metallic support structure,
die zumindest eine sich in einer radialen Richtung erstreckende Stützstrebe (3, 4, 5) aufweist, und  the at least one extending in a radial direction supporting strut (3, 4, 5), and
eine Vielzahl von an der Stützstruktur übereinander angeordneten,  a plurality of superimposed on the support structure,
plattenförmig ausgebildeten und  plate-shaped and
aus einem keramischen Faserverbundwerkstoff hergestellten made of a ceramic fiber composite material
Segmenten ( 6) , Segments (6),
die gemeinsam zumindest einen Teil einer Umfangskontur der Anordnung definieren,  which together define at least part of a circumferential contour of the assembly,
wobei die Segmente (6) mit Durchgangsöffnungen (12)  the segments (6) having passage openings (12)
versehen sind,  are provided
durch die sich die zumindest eine Stützstrebe (3, 4, 5) erstreckt,  through which the at least one support strut (3, 4, 5) extends,
dadurch gekennzeichnet, dass  characterized in that
die zumindest eine Stützstrebe (3, 4, 5) mindestens einen auswärts vorstehenden,  the at least one support strut (3, 4, 5) at least one outwardly projecting,
sich quer zur radialen Richtung erstreckenden Vorsprung (9) aufweist,  has transversely to the radial direction extending projection (9),
der in an mindestens einem der Segmente (6) mindestens eine korrespondierend ausgebildete Aussparung (13) greift.  which engages in at least one of the segments (6) at least one correspondingly formed recess (13).
2. Anordnung (1) nach Anspruch 1, 2. Arrangement (1) according to claim 1,
dadurch gekennzeichnet, dass  characterized in that
die Stützstruktur mehrere Stützstreben (3, 4, 5) aufweist, insbesondere drei Stützstreben ( 3 , 4, 5).  the support structure has a plurality of support struts (3, 4, 5), in particular three support struts (3, 4, 5).
3. Anordnung (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass 3. Arrangement (1) according to one of the preceding claims, characterized in that
die zumindest eine Stützstrebe (3, 4,5) einen unrunden Querschnitt aufweist,  the at least one support strut (3, 4, 5) has a non-circular cross section,
insbesondere einen Querschnitt,  in particular a cross section,
welcher der Umfangskontur der Anordnung folgt. which follows the peripheral contour of the assembly.
4. Anordnung (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass 4. Arrangement (1) according to one of the preceding claims, characterized in that
die zumindest eine Stützstrebe (3, 4, 5) hohl ausgebildet ist .  the at least one support strut (3, 4, 5) is hollow.
5. Anordnung (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass 5. Arrangement (1) according to one of the preceding claims, characterized in that
die Stützstruktur eine sich im Wesentlichen parallel zu den Segmenten (6) erstreckende Plattform (2) aufweist,  the support structure has a platform (2) extending essentially parallel to the segments (6),
von der die zumindest eine Stützstrebe (3, 4, 5) radial auswärts vorsteht,  of which the at least one support strut (3, 4, 5) protrudes radially outward,
wobei die Segmente (6) auf der Plattform (2) gestapelt sind .  wherein the segments (6) are stacked on the platform (2).
6. Anordnung (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass 6. Arrangement (1) according to one of the preceding claims, characterized in that
zwischen der zumindest einen Stützstrebe (3, 4, 5) und den¬ jenigen Durchgangsöffnungen (12) der Segmente (6), between the at least one support strut (3, 4, 5) and the ¬ jenigen passage openings (12) of the segments (6),
durch die sich diese erstreckt,  through which this extends,
ein definierter Ringspalt ausgebildet ist.  a defined annular gap is formed.
7. Anordnung (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass 7. Arrangement (1) according to one of the preceding claims, characterized in that
sich die mindestens eine Aussparung (13) ausgehend von einer Oberseite des jeweiligen Segments (6) erstreckt.  the at least one recess (13) extends from an upper side of the respective segment (6).
8. Anordnung (1) nach Anspruch 7, 8. Arrangement (1) according to claim 7,
dadurch gekennzeichnet, dass  characterized in that
die mindestens eine Aussparung (13) in Form von Fasen ausgebildet ist.  the at least one recess (13) is designed in the form of chamfers.
9. Anordnung (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass 9. Arrangement (1) according to one of the preceding claims, characterized in that
der mindestens eine Vorsprung (9) im Wesentlichen  the at least one projection (9) substantially
formschlüssig in der entsprechenden Aussparung (13) aufgenommen oder aufnehmbar ist. positively received in the corresponding recess (13) or is receivable.
10. Anordnung (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass 10. Arrangement (1) according to one of the preceding claims, characterized in that
jedes Segment mit zumindest einer Aussparung (13) versehen ist,  each segment is provided with at least one recess (13),
in die ein zugeordneter Vorsprung (12) greift.  into which an associated projection (12) engages.
11. Anordnung (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass 11. Arrangement (1) according to one of the preceding claims, characterized in that
die Außenflächen des mindestens einen Segments (6) mit einer Beschichtung versehen sind,  the outer surfaces of the at least one segment (6) are provided with a coating,
insbesondere mit einer Wärmebarrierebeschichtung .  in particular with a thermal barrier coating.
12. Anordnung (1) nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, dass 12. Arrangement (1) according to one of the preceding claims, characterized in that
die Anordnung (1) eine Anordnung für eine Turbinenschaufel, insbesondere ein Schaufelblatt, oder eine Anordnung für ein heißgasbeaufSchlagtes Teil, beispielsweise ein Ringsegment, für die Turbine ist.  the arrangement (1) is an arrangement for a turbine blade, in particular an airfoil, or an arrangement for a hot gas-impacted part, for example a ring segment, for which turbine is.
13. Verfahren zur Herstellung einer Anordnung (1) nach einem der vorhergehenden Ansprüche, 13. A method for producing an arrangement (1) according to one of the preceding claims,
dadurch gekennzeichnet, dass  characterized in that
zumindest die Stützstreben (3, 4, 5) der Stützstruktur un- ter Verwendung eines generativen Verfahrens hergestellt werden .  at least the support struts (3, 4, 5) of the support structure are made using a generative process.
14. Verfahren nach Anspruch 13, 14. The method according to claim 13,
dadurch gekennzeichnet, dass  characterized in that
ein Stapeln der Segmente (6) und eine schrittweise  a stacking of the segments (6) and one stepwise
Herstellung der zumindest einen Stützstrebe (3, 4, 5) einander derart abwechseln,  Production of the at least one support strut (3, 4, 5) alternating each other such
dass nach einem Anordnen eines mit einer Aussparung (13) versehenen Segments (6) ein Teilbereich der zumindest einen Stützstrebe (3, 4, 5) einschließlich eines in die  that after arranging a segment (6) provided with a recess (13), a partial region of the at least one support strut (3, 4, 5) including one in the
Aussparung (13) greifenden Vorsprungs (12) generiert wird. Recess (13) cross-projection (12) is generated.
15. Verfahren nach Anspruch 13 oder 14, dadurch gekennzeichnet, dass 15. The method according to claim 13 or 14, characterized in that
das Stapeln der Segmente (6) unter Verwendung Roboters erfolgt.  the stacking of the segments (6) is done using robot.
EP16726577.6A 2015-07-02 2016-06-02 Arrangement for a turbine Active EP3280879B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL16726577T PL3280879T3 (en) 2015-07-02 2016-06-02 Arrangement for a turbine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102015212419.3A DE102015212419A1 (en) 2015-07-02 2015-07-02 Blade assembly for a gas turbine
PCT/EP2016/062508 WO2017001139A1 (en) 2015-07-02 2016-06-02 Arrangement for a turbine

Publications (2)

Publication Number Publication Date
EP3280879A1 true EP3280879A1 (en) 2018-02-14
EP3280879B1 EP3280879B1 (en) 2021-07-28

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US (1) US10851654B2 (en)
EP (1) EP3280879B1 (en)
JP (1) JP6695363B2 (en)
KR (1) KR102033653B1 (en)
CN (1) CN107709705B (en)
DE (1) DE102015212419A1 (en)
PL (1) PL3280879T3 (en)
WO (1) WO2017001139A1 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102018213421A1 (en) * 2018-08-09 2020-02-13 Siemens Aktiengesellschaft CMC turbine component in StackWrap construction with cooling system
DE102018213417A1 (en) * 2018-08-09 2020-02-13 Siemens Aktiengesellschaft CMC turbine component

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1476921U (en)
US3301526A (en) * 1964-12-22 1967-01-31 United Aircraft Corp Stacked-wafer turbine vane or blade
GB1075910A (en) * 1966-04-04 1967-07-19 Rolls Royce Improvements in or relating to blades for mounting in fluid flow ducts
JPS54102412A (en) 1978-01-31 1979-08-11 Denriyoku Chuo Kenkyusho Gas turbine vane
JPS58172406A (en) 1982-04-05 1983-10-11 Hitachi Ltd Laminated blade for gas turbine
US5820337A (en) 1995-01-03 1998-10-13 General Electric Company Double wall turbine parts
US7247003B2 (en) 2004-12-02 2007-07-24 Siemens Power Generation, Inc. Stacked lamellate assembly
US7198458B2 (en) 2004-12-02 2007-04-03 Siemens Power Generation, Inc. Fail safe cooling system for turbine vanes
US7255535B2 (en) * 2004-12-02 2007-08-14 Albrecht Harry A Cooling systems for stacked laminate CMC vane
US7247002B2 (en) * 2004-12-02 2007-07-24 Siemens Power Generation, Inc. Lamellate CMC structure with interlock to metallic support structure
US7153096B2 (en) 2004-12-02 2006-12-26 Siemens Power Generation, Inc. Stacked laminate CMC turbine vane
DE102006049216A1 (en) * 2006-10-18 2008-04-24 Mtu Aero Engines Gmbh High-pressure turbine rotor and method for producing a high-pressure turbine rotor
US9663404B2 (en) 2012-01-03 2017-05-30 General Electric Company Method of forming a ceramic matrix composite and a ceramic matrix component
EP3224457A1 (en) * 2014-11-24 2017-10-04 Siemens Aktiengesellschaft Hybrid ceramic matrix composite materials

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JP2018524510A (en) 2018-08-30
KR20180021188A (en) 2018-02-28
PL3280879T3 (en) 2021-12-27
CN107709705B (en) 2019-12-24
US10851654B2 (en) 2020-12-01
JP6695363B2 (en) 2020-05-20
US20180156038A1 (en) 2018-06-07
EP3280879B1 (en) 2021-07-28
DE102015212419A1 (en) 2017-01-05
CN107709705A (en) 2018-02-16
WO2017001139A1 (en) 2017-01-05
KR102033653B1 (en) 2019-10-18

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