EP1188500B1 - Apparatus and method for producing a turbine blade and turbine blade - Google Patents

Apparatus and method for producing a turbine blade and turbine blade

Info

Publication number
EP1188500B1
EP1188500B1 EP00120035A EP00120035A EP1188500B1 EP 1188500 B1 EP1188500 B1 EP 1188500B1 EP 00120035 A EP00120035 A EP 00120035A EP 00120035 A EP00120035 A EP 00120035A EP 1188500 B1 EP1188500 B1 EP 1188500B1
Authority
EP
European Patent Office
Prior art keywords
cores
blade
cavity
outer walls
wall
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.)
Expired - Lifetime
Application number
EP00120035A
Other languages
German (de)
French (fr)
Other versions
EP1188500A1 (en
Inventor
Peter Tiemann
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
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 DE50013334T priority Critical patent/DE50013334D1/en
Priority to EP00120035A priority patent/EP1188500B1/en
Priority to CNB018027393A priority patent/CN1213823C/en
Priority to JP2002526531A priority patent/JP4350372B2/en
Priority to US10/239,792 priority patent/US6805535B2/en
Priority to PCT/EP2001/010600 priority patent/WO2002022291A1/en
Publication of EP1188500A1 publication Critical patent/EP1188500A1/en
Application granted granted Critical
Publication of EP1188500B1 publication Critical patent/EP1188500B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/02—Sand moulds or like moulds for shaped castings
    • B22C9/04—Use of lost patterns
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C21/00—Flasks; Accessories therefor
    • B22C21/12—Accessories
    • B22C21/14—Accessories for reinforcing or securing moulding materials or cores, e.g. gaggers, chaplets, pins, bars
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49339—Hollow blade
    • Y10T29/49341—Hollow blade with cooling passage

Definitions

  • the present invention relates to a blade for a turbine, in particular a gas turbine, with two outer walls and at least one cavity arranged between the outer walls.
  • the invention further relates to an apparatus for producing such a blade with two outer walls and at least one arranged between the outer walls cavity for a turbine, with an outer shape and two cores for forming the outer walls and the at least one cavity.
  • the invention also relates to a method for producing such a blade having two outer walls and at least one cavity arranged between the outer walls for a turbine by means of a casting method, wherein an outer mold and two cores are provided for forming the outer walls and the at least one cavity.
  • Blades in particular blades for gas turbines, have to be cooled from the inside due to the high operating temperatures.
  • the blades have one or more cavities for this purpose. In the previously known blades, these cavities extend from one outer wall of the blade to the other outer wall. To form each cavity, a portion of a core is provided. The individual sections are connected to each other. The core is received in a suitable receptacle of an outer mold for the manufacture of the blade in a casting process. The length of the core can assume comparatively large values.
  • the wall thickness of the outer walls should be as low as possible. By a low wall thickness can achieve a significant improvement in cooling.
  • the minimum wall thickness required in any case must be greater than the wall thickness tolerance. Otherwise, there is a risk that the core will be displaced and / or deformed during casting so as to come into contact with the outer mold and the manufactured blade has a hole. In practice, therefore, a comparatively high wall thickness must be selected.
  • WO 99/59748 A1 discloses a mold for producing a metallic hollow body in which two cores are used, but with a complicated arrangement of the cavities.
  • Another object of the present invention is therefore to provide a simple and inexpensive device and a To provide low-cost method for producing a blade with low wall thicknesses.
  • this object is achieved in a blade according to claim 1.
  • each of the two cores has at least one section which extends from an associated outer wall to a central web of the blade to be produced extending approximately in the axial profile center, without being involved in the formation of the other outer wall.
  • the inventive method is characterized in that the two cores are supported against each other and pressed against the inside of the outer mold, that at least a portion of each core is supported such that the distance between the outside of the portion of the one core and the inside of the outer mold independently the distance between the outer side of the portion of the other core and the inside of the outer mold, so that wall thicknesses of the two outer walls are formed independently of each other at least in the region of the sections.
  • the basic idea of the invention is based on the fact that the production of the two outer walls of the blade takes place, at least in sections, independently of one another.
  • At least one cavity of the blade is divided by a central web into two channels.
  • the one channel extends from the first outer wall to the central web and the other channel from the central web to the second outer wall.
  • Two cores are provided.
  • a first core has one or more sections for forming the channels between the first outer wall and the central web.
  • the further channels are formed by sections of a second core, which is provided separately from the first core. Displacements and deformations of the first core, which is a modification of the Wall thickness of an outer wall, are not transferred to the second core.
  • the wall thicknesses of the two outer walls are therefore formed at least partially independent of each other.
  • the method according to the invention provides for supporting the sections of each core which serve to form the channels in such a way that a minimum wall thickness is ensured.
  • projections are advantageously used, which are supported on the inside of the outer mold.
  • the side of the sections associated with the central web can be subjected to comparatively coarse tolerances.
  • the manufacturing accuracy of relevant for the wall thickness of the outer walls outside of the cores can be substantially improved. All tolerances are shifted to the area of the center bar. Disadvantages for the cooling effect do not arise as a result, since the central web is not acted upon directly by the hot fluid flowing through the turbine. Further, the central web is cooled on both sides by the channels. The central web further provides the necessary strength for the blade at low wall thicknesses of the outer walls.
  • the cores are provided for support on the outer shape with projections. They are then advantageously supported during casting together and pressed against the inside of the outer mold.
  • the support can be effected by means of rigid, in particular wedge-shaped, or elastic spacers.
  • the projections serving for supporting on the outer mold taper advantageously from the cores. They can be formed in particular conical. This ensures that only point-shaped openings are formed in the outer walls through which only minimal coolant escapes. Despite the support on the inside of the outer mold, therefore, the desired high cooling efficiency is maintained.
  • the cores may be fixed at one or both ends in a receptacle of the outer shape in the longitudinal direction of the blade. Alignment in the longitudinal direction alone is sufficient if the transverse support is provided by the projections on the cores. This ensures the position of the cores during the manufacture of the wax tool and the casting.
  • the outer walls are connected to form a plurality of cavities via a plurality of ribs. This results in targeted cooling of individual areas of the blade with increased strength.
  • a cavity at an inlet edge and / or a trailing edge of the blade is free from the central web.
  • the reason for this is that an increased cooling effect is required in the area of the leading edge. At the junction of the central web, the cooling effect would be impaired. This applies mutatis mutandis to the trailing edge.
  • the wall thickness of the central web is greater than the wall thickness of the outer walls.
  • the required strength of the blade is then ensured by the central web and optionally the ribs.
  • the wall thickness of the outer walls can be reduced accordingly.
  • FIG. 1 shows a schematic longitudinal section through a gas turbine 10 with a housing 11 and a rotor 12.
  • Guide vanes 13 and rotor blades 12 are attached to the housing 11.
  • the turbine 10 is flowed through in the direction of arrow 15 by a hot medium, in particular a gas. Due to this flow, the rotor 12 is set in rotation about an axis 16 with respect to the housing 11.
  • the blades 13, 14 must be cooled from the inside due to the high prevailing temperature.
  • FIG. 2 shows a cross section through a blade 14 of the turbine 10.
  • the vanes 13 are constructed substantially similar.
  • the blade 14 has two outer walls 17, 18, which are connected by three ribs 19, 20, 21.
  • the ribs 19, 20, 21 are approximately perpendicular to the outer walls 17, 18.
  • the outer walls 17, 18 at its two ends in an entrance edge 22 and a trailing edge 23 on. The flow of the blade 14 in the direction of the arrow 15 takes place from the inlet edge 22 to the outlet edge 23.
  • the space between the outer walls 17, 18 into a plurality of cavities 24, 25, 26, 27 is divided.
  • the lying in the middle of the blade 14 cavities 26, 27 are divided by a central web 28 in two channels 26a, 26b, 27a, 27b.
  • the channels 26a, 27a are in this case arranged between the first outer wall 17 and the central web 28.
  • the further channels 26b, 27b are located between the central web 28 and the second outer wall 18.
  • the cavities 24, 25 in the region of the leading edge 22 and the trailing edge 23 are free of the central web 28.
  • the wall thickness D of the central web 28 is greater than the wall thickness d of the outer walls.
  • the central web 28 extends from the front rib 19 via the middle rib 20 to the rear rib 21. It is arranged approximately in the axial profile center of the blade 14.
  • the central bridge 28 puts together with the ribs 19, 20, 21 ready for operation strength of the blade 14 ready.
  • the outer walls 17, 18 can therefore be made thin.
  • Figure 3 shows a cross section through an inventive device 29 for producing a blade 13, 14. It is an outer mold 30 with two mold parts 31, 32 provided, which can be according to the arrow 33 away from each other and moved towards each other. Between the two mold parts 31, 32 two separately formed cores 34, 35 are used.
  • the first core 34 has three sections 36a, 37a, 38a.
  • the sections 36a, 37a serve to form the channels 26a, 27a.
  • the portion 38 a forms the cavity 24 in the region of the leading edge 22.
  • the second core 35 is substantially similar to sections 36b, 37b, 38b. Again, two sections 36b, 37b are provided for forming the channels 26b, 27b. The cavity 25 in the region of the outlet edge 23 is formed by the portion 38b. The individual sections 36ab, 37ab, 38ab of the cores 34, 35 are connected to each other.
  • the portions 36 ab, 37 ab for forming the channels 26 a, 26 b, 27 a, 27 b have projections 39 for support on an inner side 40 of the outer mold 30.
  • the projections 39 taper and are conical. They provide the minimum distance between the inner side 40 of the outer mold and an associated outer side 46a, 47a, 46b, 47b of the sections 36a, 36b, 37a, 37b. This distance corresponds essentially to the wall thickness d of the outer walls 17, 18.
  • the wall thickness D of the central web 28 is determined by the distance between the sections 36a, 37a and the sections 36b, 37b.
  • outer sides 46a, 47a, 46b, 47b of the sections 36a, 37a, 36b, 37b and the outer sides 48a, 48b of the sections 38a, 38b need to be highly accurate to be edited.
  • the further surfaces of the cores 34, 35 can have comparatively high tolerances since they are not important for determining the wall thickness d of the outer walls 17, 18.
  • FIGs 4 and 5 show the mounting of the cores 34, 35 in the device 29.
  • Each of the cores 34, 35 has at both ends projections 41, 42 for attachment in a recording 43 shown in phantom of the device 29 according to the invention.
  • the two cores 34, 35 are supported by spacers 44, 45 to each other.
  • the projections 39 are thereby pressed against the inner side 40 of the outer mold 30.
  • the use of rigid spacers 44 and in Figure 5 the use of elastic, in particular spring-trained spacers 45 is shown.
  • the minimum wall thickness d of the outer walls 17, 18 is ensured by the fact that the cores 34, 35 are supported with the projections 39 on the inner side 40. Due to the tapering of the projections 39, only a point-shaped opening is formed in the outer walls 17, 18 of the finished blade 13, 14. Movement of the cores 34, 35 toward one another is prevented by the spacers 44, 45. It is thus ensured that the desired wall thickness d of the outer walls 17, 18 is reliably maintained. The previously occurring tolerances of the wall thickness d can be substantially reduced. The wall thickness d can therefore be reduced structurally from the outset with respect to the known blades 13, 14 and devices 29.
  • Another advantage is that the wall thicknesses d of the outer walls 17, 18 no longer depend on each other. A displacement or deformation of the core 34 does not lead to a change in the wall thickness d of the outer wall 18. Also, a displacement or deformation of the core 35 does not lead to a change in the wall thickness d of the outer wall 17th
  • FIG. 6 schematically shows a plan view of FIG. 5.
  • the individual sections 36a, 36b, 37a, 37b, 38a, 38b of the cores 34, 35 are rigidly connected to each other as shown.
  • the cores 34, 35 are supported on the elastic spacers 45 to each other and are pressed against the inner side 40. If a plurality of spacers 45 distributed over the entire length of the cores 34, 35 are used, shifts and deformations during casting can be significantly reduced.
  • the desired cores 34, 35 are first preformed in a suitable mold, not shown, and then fired. They are then inserted into the provided outer mold 30. The projections 39 of the sections 36a, 36b, 37a, 37b of the two cores 34, 35 are brought into abutment against the inner side 40 of the outer mold 30. For this purpose, either rigid or elastic spacers 44, 45 are introduced between the two cores 34, 35. Thereafter, the two cores 34, 35 are fixed in the receptacles 43.
  • a suitable material such as wax is poured. After solidification of the wax, the outer shape is removed and the wax body provided with a protective layer.
  • This protective layer may, like the cores 34, 35, consist of a ceramic material.
  • the waxed tool provided with the protective layer is fired again. Subsequently, the pourable material for the blade 13, 14 is introduced into the intermediate space between the protective layer and the cores 34, 35. After solidification of this material, the protective layer and the cores 34, 35 are removed in a suitable manner, for example, rinsed with an acid or alkali.
  • the manufacturing and assembly tolerances in the production and fixing of the cores 34, 35, the wax tool and the protective layer which are present in the known methods and devices can be substantially reduced.
  • the wall thickness of the outer walls 17, 18 of the blade 13, 14 can therefore be significantly reduced. This results in an improved cooling effect.
  • the required strength of the blade 13, 14 is ensured by the central web 28.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)
  • Casting Devices For Molds (AREA)

Description

Die vorliegende Erfindung betrifft eine Schaufel für eine Turbine, insbesondere eine Gasturbine, mit zwei Außenwänden und mindestens einem zwischen den Außenwänden angeordneten Hohlraum.The present invention relates to a blade for a turbine, in particular a gas turbine, with two outer walls and at least one cavity arranged between the outer walls.

Die Erfindung betrifft weiterhin eine Vorrichtung zur Herstellung einer derartigen Schaufel mit zwei Außenwänden und mindestens einem zwischen den Außenwänden angeordneten Hohlraum für eine Turbine, mit einer Außenform und zwei Kernen zur Ausbildung der Außenwände und des mindestens eines Hohlraums.The invention further relates to an apparatus for producing such a blade with two outer walls and at least one arranged between the outer walls cavity for a turbine, with an outer shape and two cores for forming the outer walls and the at least one cavity.

Die Erfindung betrifft ebenso ein Verfahren zur Herstellung einer derartigen Schaufel mit zwei Außenwänden und mindestens einem zwischen den Außenwänden angeordneten Hohlraum für eine Turbine mittels eines Gussverfahrens, wobei eine Außenform und zwei Kerne zur Ausbildung der Außenwände und des mindestens eines Hohlraums bereitgestellt werden.The invention also relates to a method for producing such a blade having two outer walls and at least one cavity arranged between the outer walls for a turbine by means of a casting method, wherein an outer mold and two cores are provided for forming the outer walls and the at least one cavity.

Schaufeln, insbesondere Schaufeln für Gasturbinen, müssen aufgrund der hohen Betriebstemperaturen von innen gekühlt werden. Die Schaufeln weisen zu diesem Zweck einen oder mehrere Hohlräume auf. Bei den bisher bekannten Schaufeln erstrecken sich diese Hohlräume von der einen Außenwand der Schaufel bis zur anderen Außenwand. Zur Ausbildung jedes Hohlraums ist ein Abschnitt eines Kerns vorgesehen. Die einzelnen Abschnitte sind miteinander verbunden. Der Kern wird in einer geeigneten Aufnahme einer Außenform zur Herstellung der Schaufel in einem Gußverfahren aufgenommen. Die Länge des Kerns kann hierbei vergleichsweise große Werte annehmen.Blades, in particular blades for gas turbines, have to be cooled from the inside due to the high operating temperatures. The blades have one or more cavities for this purpose. In the previously known blades, these cavities extend from one outer wall of the blade to the other outer wall. To form each cavity, a portion of a core is provided. The individual sections are connected to each other. The core is received in a suitable receptacle of an outer mold for the manufacture of the blade in a casting process. The length of the core can assume comparatively large values.

Bei von innen gekühlten Schaufeln soll die Wandstärke der Außenwände möglichst gering gewählt werden. Durch eine geringe Wandstärke läßt sich eine wesentliche Verbesserung der Kühlung erreichen. Die minimal vorgesehene Wandstärke muß in jedem Fall größer sein als die Wandstärkentoleranz. Ansonsten besteht die Gefahr, dass der Kern während des Gießens verschoben und/oder derart verformt wird, dass er in Kontakt mit der Außenform kommt und die hergestellte Schaufel ein Loch aufweist. In der Praxis muß daher eine vergleichsweise hohe Wandstärke gewählt werden.For internally cooled blades, the wall thickness of the outer walls should be as low as possible. By a low wall thickness can achieve a significant improvement in cooling. The minimum wall thickness required in any case must be greater than the wall thickness tolerance. Otherwise, there is a risk that the core will be displaced and / or deformed during casting so as to come into contact with the outer mold and the manufactured blade has a hole. In practice, therefore, a comparatively high wall thickness must be selected.

Ein weiterer Nachteil der bekannten Verfahren ist, dass eine Verlagerung des Kerns während des Gießens Auswirkungen auf beide Außenwände der Schaufel hat. Grund hierfür ist, dass sich der Kern von der einen Außenwand bis zur anderen Außenwand erstreckt. Daher muß bei diesen bekannten Verfahren der Kern hochgenau gefertigt werden. Bei der Fertigung des Kerns auftretende Toleranzen müssen ebenfalls berücksichtigt werden.Another disadvantage of the known methods is that a displacement of the core during casting has an effect on both outer walls of the blade. The reason for this is that the core extends from one outer wall to the other outer wall. Therefore, in these known methods, the core must be manufactured with high precision. Tolerances occurring during the production of the core must also be taken into account.

Zur Verbesserung der Kühlung sind Schaufeln mit Hohlwänden bekannt. Eine derartige Schaufel sowie ein Verfahren und eine Vorrichtung zu ihrer Herstellung sind aus der auf dieselbe Anmelderin zurückgehenden WO 99/59748 bekannt. Diese Druckschrift schlägt eine Vielzahl von Kernen vor, die über Verbindungselemente miteinander und der Außenform verbunden werden. Es handelt sich um eine komplizierte und kostenintensive Herstellung.To improve cooling, hollow-walled blades are known. Such a blade as well as a method and a device for its production are known from WO 99/59748, which originates from the same Applicant. This document proposes a plurality of cores which are connected to one another via fasteners and the outer mold. It is a complicated and costly production.

Die WO 99/59748 A1 offenbart eine Gussform zur Herstellung eines metallischen Hohlkörpers, bei dem zwei Kerne verwendet werden, wobei jedoch eine komplizierte Anordnung der Hohlräume gegeben ist.WO 99/59748 A1 discloses a mold for producing a metallic hollow body in which two cores are used, but with a complicated arrangement of the cavities.

Es ist daher Aufgabe der Erfindung, eine Schaufel für eine Turbine bereitzustellen, die Außenwände mit einer wesentlich geringeren Wandstärke aufweist.It is therefore an object of the invention to provide a blade for a turbine having outer walls with a much smaller wall thickness.

Eine weitere Aufgabe der vorliegenden Erfindung ist es daher, eine einfache und kostengünstige Vorrichtung sowie ein kostengünstiges Verfahren zur Herstellung einer Schaufel mit geringen Wandstärken bereitzustellen.Another object of the present invention is therefore to provide a simple and inexpensive device and a To provide low-cost method for producing a blade with low wall thicknesses.

Erfindungsgemäß wird diese Aufgabe bei einer Schaufel gemäß Anspruch 1 gelöst.According to the invention, this object is achieved in a blade according to claim 1.

Die erfindungsgemäße Vorrichtung sieht vor, dass jeder der beiden Kerne mindestens einen Abschnitt aufweist, der sich von einer zugeordneten Außenwand bis zu einem etwa in der axialen Profilmitte verlaufenden Mittelsteg der herzustellenden Schaufel erstreckt, ohne an der Ausbildung der anderen Außenwand beteiligt zu sein.The device according to the invention provides that each of the two cores has at least one section which extends from an associated outer wall to a central web of the blade to be produced extending approximately in the axial profile center, without being involved in the formation of the other outer wall.

Das erfindungsgemäße Verfahren ist dadurch gekennzeichnet, dass die beiden Kerne aneinander abgestützt und gegen die Innenseite der Außenform gedrückt werden, dass mindestens ein Abschnitt jedes Kerns derart abgestützt wird, dass der Abstand zwischen der Außenseite des Abschnitts des einen Kerns und der Innenseite der Außenform unabhängig von dem Abstand zwischen der Außenseite des Abschnitts des anderen Kerns und der Innenseite der Außenform ist, so dass Wandstärken der beiden Außenwände zumindest im Bereich der Abschnitte unabhängig voneinander ausgebildet werden.The inventive method is characterized in that the two cores are supported against each other and pressed against the inside of the outer mold, that at least a portion of each core is supported such that the distance between the outside of the portion of the one core and the inside of the outer mold independently the distance between the outer side of the portion of the other core and the inside of the outer mold, so that wall thicknesses of the two outer walls are formed independently of each other at least in the region of the sections.

Der Grundgedanke der Erfindung basiert darauf, dass die Herstellung der beiden Außenwände der Schaufel zumindest abschnittsweise unabhängig voneinander erfolgt. Mindestens ein Hohlraum der Schaufel wird durch einen Mittelsteg in zwei Kanäle aufgeteilt. Der eine Kanal erstreckt sich von der ersten Außenwand bis zum Mittelsteg und der andere Kanal vom Mittelsteg bis zur zweiten Außenwand. Es werden zwei Kerne bereitgestellt. Ein erster Kern weist einen oder mehrere Abschnitte zur Ausbildung der Kanäle zwischen der ersten Außenwand und dem Mittelsteg auf. Die weiteren Kanäle werden durch Abschnitte eines zweiten Kerns ausgebildet, der getrennt von dem ersten Kern vorgesehen ist. Verschiebungen und Verformungen des ersten Kerns, die eine Änderung der Wandstärke der einen Außenwand bewirken, werden nicht auf den zweiten Kern übertragen. Die Wandstärken der beiden Außenwände werden daher zumindest bereichsweise unabhängig voneinander ausgebildet.The basic idea of the invention is based on the fact that the production of the two outer walls of the blade takes place, at least in sections, independently of one another. At least one cavity of the blade is divided by a central web into two channels. The one channel extends from the first outer wall to the central web and the other channel from the central web to the second outer wall. Two cores are provided. A first core has one or more sections for forming the channels between the first outer wall and the central web. The further channels are formed by sections of a second core, which is provided separately from the first core. Displacements and deformations of the first core, which is a modification of the Wall thickness of an outer wall, are not transferred to the second core. The wall thicknesses of the two outer walls are therefore formed at least partially independent of each other.

Das erfindungsgemäße Verfahren sieht vor, die zur Ausbildung der Kanäle dienenden Abschnitte jedes Kerns derart abzustützen, dass eine minimale Wandstärke gewährleistet wird. Hierfür werden vorteilhaft Vorsprünge verwendet, die sich an der Innenseite der Außenform abstützen.The method according to the invention provides for supporting the sections of each core which serve to form the channels in such a way that a minimum wall thickness is ensured. For this purpose, projections are advantageously used, which are supported on the inside of the outer mold.

Bei der Herstellung der Kerne ist nur noch die der Innenseite der Außenform zugewandte Außenseite der Abschnitte kritisch für die Wandstärke der Außenwände. Insbesondere die dem Mittelsteg zugeordnete Seite der Abschnitte kann mit vergleichsweise groben Toleranzen beaufschlagt werden. Hierdurch kann die Fertigungsgenauigkeit der für die Wandstärke der Außenwände maßgebliche Außenseite der Kerne wesentlich verbessert werden. Sämtliche Toleranzen werden in den Bereich des Mittelstegs verlagert. Nachteile für die Kühlwirkung entstehen hierdurch nicht, da der Mittelsteg nicht direkt mit dem heißen, die Turbine durchströmenden Fluid beaufschlagt wird. Weiter wird der Mittelsteg auf beiden Seiten durch die Kanäle gekühlt. Der Mittelsteg stellt weiter bei geringen Wandstärken der Außenwände die erforderliche Festigkeit für die Schaufel bereit.In the manufacture of the cores, only the outer side of the sections facing the inside of the outer shape is critical for the wall thickness of the outer walls. In particular, the side of the sections associated with the central web can be subjected to comparatively coarse tolerances. As a result, the manufacturing accuracy of relevant for the wall thickness of the outer walls outside of the cores can be substantially improved. All tolerances are shifted to the area of the center bar. Disadvantages for the cooling effect do not arise as a result, since the central web is not acted upon directly by the hot fluid flowing through the turbine. Further, the central web is cooled on both sides by the channels. The central web further provides the necessary strength for the blade at low wall thicknesses of the outer walls.

Vorteilhafte Ausgestaltungen und Weiterbildungen der Erfindung gehen aus den abhängigen Ansprüchen hervor.Advantageous embodiments and further developments of the invention will become apparent from the dependent claims.

Nach einer vorteilhaften Weiterbildung der Erfindung sind die Kerne zur Abstützung an der Außenform mit Vorsprüngen versehen. Sie werden dann vorteilhaft während des Gießens aneinander abgestützt und gegen die Innenseite der Außenform gedrückt. Die Abstützung kann mittels starrer, insbesondere keilförmiger, oder elastischer Abstandshalter erfolgen.According to an advantageous embodiment of the invention, the cores are provided for support on the outer shape with projections. They are then advantageously supported during casting together and pressed against the inside of the outer mold. The support can be effected by means of rigid, in particular wedge-shaped, or elastic spacers.

Bei diesem Vorgehen wird eine minimale Wandstärke für die Außenwände zuverlässig eingehalten. Verschiebungen der Kerne nach innen werden durch die Abstützung aneinander vermieden. Für die Herstellung der Kerne bedeutet dies, dass lediglich die der Innenseite der Außenform zugewandte Außenseite hochgenau hergestellt werden muß. Durch die Abstützung der beiden Kerne aneinander ist die Maßhaltigkeit der weiteren Außenseiten von nur untergeordneter Bedeutung. Weiter wird durch die Abstützung der Kerne aneinander eine höhere Steifigkeit als bei den bekannten Vorrichtungen und Verfahren erreicht. Verschiebungen oder Verformungen der Kerne während des Gießens werden daher verringert. Die Toleranzspanne für die Wandstärke der Außenwände kann daher deutlich reduziert werden, so dass insgesamt dünnere Außenwände vorgesehen werden können.In this procedure, a minimum wall thickness for the outer walls is reliably maintained. Shifts of the cores inward are avoided by the support to each other. For the production of the cores, this means that only the outside facing the inside of the outer shape must be made with high precision. By supporting the two cores together, the dimensional accuracy of the other outer sides of only minor importance. Further, by supporting the cores together, a higher rigidity is achieved than in the known devices and methods. Shifts or deformations of the cores during casting are therefore reduced. The tolerance margin for the wall thickness of the outer walls can therefore be significantly reduced, so that overall thinner outer walls can be provided.

Die zur Abstützung an der Außenform dienenden Vorsprünge verjüngen sich vorteilhaft ausgehend von den Kernen. Sie können insbesondere konisch ausgebildet werden. Hierdurch wird sichergestellt, dass nur punktförmige Öffnungen in den Außenwänden entstehen, durch die nur minimal Kühlmittel austritt. Trotz der Abstützung an der Innenseite der Außenform bleibt daher die gewünschte hohe Kühleffizienz erhalten.The projections serving for supporting on the outer mold taper advantageously from the cores. They can be formed in particular conical. This ensures that only point-shaped openings are formed in the outer walls through which only minimal coolant escapes. Despite the support on the inside of the outer mold, therefore, the desired high cooling efficiency is maintained.

Die Kerne können an einem oder beiden Enden in einer Aufnahme der Außenform in Längsrichtung der Schaufel fixiert sein. Eine Fixierung allein in Längsrichtung ist ausreichend, wenn die Abstützung in Querrichtung durch die Vorsprünge an den Kernen erfolgt. Hierdurch wird die Lage der Kerne während der Herstellung des Wachswerkzeugs und des Gießens sichergestellt.The cores may be fixed at one or both ends in a receptacle of the outer shape in the longitudinal direction of the blade. Alignment in the longitudinal direction alone is sufficient if the transverse support is provided by the projections on the cores. This ensures the position of the cores during the manufacture of the wax tool and the casting.

Vorteilhaft sind die Außenwände zur Bildung mehrerer Hohlräume über mehrere Rippen miteinander verbunden. Hierdurch ergibt sich eine gezielte Kühlung einzelner Bereiche der Schaufel bei erhöhter Festigkeit.Advantageously, the outer walls are connected to form a plurality of cavities via a plurality of ribs. This results in targeted cooling of individual areas of the blade with increased strength.

Gemäß einer vorteilhaften Weiterbildung ist ein Hohlraum an einer Eintrittskante und/oder einer Austrittskante der Schaufel frei von dem Mittelsteg. Grund hierfür ist, dass im Bereich der Eintrittskante eine erhöhte Kühlwirkung erforderlich ist. Im Einmündungsbereich des Mittelstegs wäre die Kühlwirkung beeinträchtigt. Dies gilt sinngemäß auch für die Austrittskante.According to an advantageous development, a cavity at an inlet edge and / or a trailing edge of the blade is free from the central web. The reason for this is that an increased cooling effect is required in the area of the leading edge. At the junction of the central web, the cooling effect would be impaired. This applies mutatis mutandis to the trailing edge.

In vorteilhafter Ausgestaltung ist die Wandstärke des Mittelstegs größer als die Wandstärke der Außenwände. Die erforderliche Festigkeit der Schaufel wird dann von dem Mittelsteg und gegebenenfalls den Rippen gewährleistet. Die Wandstärke der Außenwände kann entsprechend verringert werden.In an advantageous embodiment, the wall thickness of the central web is greater than the wall thickness of the outer walls. The required strength of the blade is then ensured by the central web and optionally the ribs. The wall thickness of the outer walls can be reduced accordingly.

Nachstehend wird die Erfindung anhand eines Ausführungsbeispiels näher beschrieben, das in schematischer Weise in der Zeichnung dargestellt ist. Dabei zeigt:

Figur 1
einen schematischen Längsschnitt durch eine Gasturbine;
Figur 2
einen Querschnitt durch eine Laufschaufel der Turbine;
Figur 3
einen Querschnitt durch die erfindungsgemäß vorgesehene Vorrichtung zur Herstellung der Schaufel;
Figur 4
eine schematische Seitenansicht der Lagerung der Kerne in der erfindungsgemäßen Vorrichtung;
Figur 5
eine Ansicht ähnlich Figur 4 in weiterer Ausgestaltung; und
Figur 6
eine Draufsicht auf Figur 5.
The invention will be described in more detail below with reference to an exemplary embodiment, which is shown schematically in the drawing. Showing:
FIG. 1
a schematic longitudinal section through a gas turbine;
FIG. 2
a cross section through a blade of the turbine;
FIG. 3
a cross section through the inventively provided device for producing the blade;
FIG. 4
a schematic side view of the storage of the cores in the device according to the invention;
FIG. 5
a view similar to Figure 4 in a further embodiment; and
FIG. 6
a plan view of Figure 5.

Figur 1 zeigt einen schematischen Längsschnitt durch eine Gasturbine 10 mit einem Gehäuse 11 und einem Rotor 12. Am Gehäuse 11 sind Leitschaufeln 13 und am Rotor 12 Laufschaufeln 14 angebracht. Die Turbine 10 wird in Pfeilrichtung 15 von einem heißen Medium, insbesondere einem Gas durchströmt. Aufgrund dieser Strömung wird der Rotor 12 in Drehung um eine Achse 16 gegenüber dem Gehäuse 11 versetzt. Die Schaufeln 13, 14 müssen aufgrund der hohen herrschenden Temperatur von innen gekühlt werden.FIG. 1 shows a schematic longitudinal section through a gas turbine 10 with a housing 11 and a rotor 12. Guide vanes 13 and rotor blades 12 are attached to the housing 11. The turbine 10 is flowed through in the direction of arrow 15 by a hot medium, in particular a gas. Due to this flow, the rotor 12 is set in rotation about an axis 16 with respect to the housing 11. The blades 13, 14 must be cooled from the inside due to the high prevailing temperature.

Figur 2 zeigt einen Querschnitt durch eine Laufschaufel 14 der Turbine 10. Die Leitschaufeln 13 sind im wesentlichen ähnlich aufgebaut. Die Laufschaufel 14 weist zwei Außenwände 17, 18 auf, die über drei Rippen 19, 20, 21 verbunden sind. Die Rippen 19, 20, 21 stehen etwa senkrecht zu den Außenwänden 17, 18. Die Außenwände 17, 18 gehen an ihren beiden Enden in eine Eintrittskante 22 beziehungsweise eine Austrittskante 23 über. Die Anströmung der Schaufel 14 gemäß Pfeilrichtung 15 erfolgt von der Eintrittskante 22 zur Austrittskante 23.Figure 2 shows a cross section through a blade 14 of the turbine 10. The vanes 13 are constructed substantially similar. The blade 14 has two outer walls 17, 18, which are connected by three ribs 19, 20, 21. The ribs 19, 20, 21 are approximately perpendicular to the outer walls 17, 18. The outer walls 17, 18 at its two ends in an entrance edge 22 and a trailing edge 23 on. The flow of the blade 14 in the direction of the arrow 15 takes place from the inlet edge 22 to the outlet edge 23.

Durch die Rippen 19, 20, 21 wird der Zwischenraum zwischen den Außenwänden 17, 18 in mehrere Hohlräume 24, 25, 26, 27 unterteilt. Die in der Mitte der Laufschaufel 14 liegenden Hohlräume 26, 27 sind durch einen Mittelsteg 28 in je zwei Kanäle 26a, 26b, 27a, 27b aufgeteilt. Die Kanäle 26a, 27a sind hierbei zwischen der ersten Außenwand 17 und dem Mittelsteg 28 angeordnet. Die weiteren Kanäle 26b, 27b befinden sich zwischen dem Mittelsteg 28 und der zweiten Außenwand 18. Die Hohlräume 24, 25 im Bereich der Eintrittskante 22 und der Austrittskante 23 sind frei von dem Mittelsteg 28.By the ribs 19, 20, 21, the space between the outer walls 17, 18 into a plurality of cavities 24, 25, 26, 27 is divided. The lying in the middle of the blade 14 cavities 26, 27 are divided by a central web 28 in two channels 26a, 26b, 27a, 27b. The channels 26a, 27a are in this case arranged between the first outer wall 17 and the central web 28. The further channels 26b, 27b are located between the central web 28 and the second outer wall 18. The cavities 24, 25 in the region of the leading edge 22 and the trailing edge 23 are free of the central web 28.

Die Wandstärke D des Mittelstegs 28 ist größer als die Wandstärke d der Außenwände. Der Mittelsteg 28 verläuft von der vorderen Rippe 19 über die mittlere Rippe 20 bis zur hinteren Rippe 21. Er ist etwa in der axialen Profilmitte der Laufschaufel 14 angeordnet. Der Mittelsteg 28 stellt zusammen mit den Rippen 19, 20, 21 die für den Betrieb erforderliche Festigkeit der Laufschaufel 14 bereit. Die Außenwände 17, 18 können daher dünn ausgebildet werden.The wall thickness D of the central web 28 is greater than the wall thickness d of the outer walls. The central web 28 extends from the front rib 19 via the middle rib 20 to the rear rib 21. It is arranged approximately in the axial profile center of the blade 14. The central bridge 28 puts together with the ribs 19, 20, 21 ready for operation strength of the blade 14 ready. The outer walls 17, 18 can therefore be made thin.

Figur 3 zeigt einen Querschnitt durch eine erfindungsgemäße Vorrichtung 29 zur Herstellung einer Schaufel 13, 14. Es ist eine Außenform 30 mit zwei Formteilen 31, 32 vorgesehen, die gemäß Pfeilrichtung 33 voneinander entfernt und aufeinander zu bewegt werden können. Zwischen die beiden Formteile 31, 32 sind zwei getrennt voneinander ausgebildete Kerne 34, 35 eingesetzt. Der erste Kern 34 weist drei Abschnitte 36a, 37a, 38a auf. Die Abschnitte 36a, 37a dienen zur Ausbildung der Kanäle 26a, 27a. Der Abschnitt 38a bildet den Hohlraum 24 im Bereich der Eintrittskante 22.Figure 3 shows a cross section through an inventive device 29 for producing a blade 13, 14. It is an outer mold 30 with two mold parts 31, 32 provided, which can be according to the arrow 33 away from each other and moved towards each other. Between the two mold parts 31, 32 two separately formed cores 34, 35 are used. The first core 34 has three sections 36a, 37a, 38a. The sections 36a, 37a serve to form the channels 26a, 27a. The portion 38 a forms the cavity 24 in the region of the leading edge 22.

Der zweite Kern 35 ist im wesentlichen ähnlich mit Abschnitten 36b, 37b, 38b ausgebildet. Auch hier sind zwei Abschnitte 36b, 37b zum Ausbilden der Kanäle 26b, 27b vorgesehen. Der Hohlraum 25 im Bereich der Austrittskante 23 wird durch den Abschnitt 38b gebildet. Die einzelnen Abschnitte 36ab, 37ab, 38ab der Kerne 34, 35 sind miteinander verbunden.The second core 35 is substantially similar to sections 36b, 37b, 38b. Again, two sections 36b, 37b are provided for forming the channels 26b, 27b. The cavity 25 in the region of the outlet edge 23 is formed by the portion 38b. The individual sections 36ab, 37ab, 38ab of the cores 34, 35 are connected to each other.

Die Abschnitte 36ab, 37ab zur Bildung der Kanäle 26a, 26b, 27a, 27b weisen Vorsprünge 39 zur Abstützung an einer Innenseite 40 der Außenform 30 auf. Die Vorsprünge 39 verjüngen sich und sind konisch ausgebildet. Sie stellen den Minimalabstand zwischen der Innenseite 40 der Außenform und einer jeweils zugeordneten Außenseite 46a, 47a, 46b, 47b der Abschnitte 36a, 36b, 37a, 37b bereit. Dieser Abstand entspricht im wesentlichen der Wandstärke d der Außenwände 17, 18. Die Wandstärke D des Mittelstegs 28 wird durch den Abstand zwischen den Abschnitten 36a, 37a und den Abschnitten 36b, 37b festgelegt.The portions 36 ab, 37 ab for forming the channels 26 a, 26 b, 27 a, 27 b have projections 39 for support on an inner side 40 of the outer mold 30. The projections 39 taper and are conical. They provide the minimum distance between the inner side 40 of the outer mold and an associated outer side 46a, 47a, 46b, 47b of the sections 36a, 36b, 37a, 37b. This distance corresponds essentially to the wall thickness d of the outer walls 17, 18. The wall thickness D of the central web 28 is determined by the distance between the sections 36a, 37a and the sections 36b, 37b.

Für die Herstellung müssen lediglich die Außenseiten 46a, 47a, 46b, 47b der Abschnitte 36a, 37a, 36b, 37b sowie die Außenseiten 48a, 48b der Abschnitte 38a, 38b hochgenau bearbeitet werden. Die weiteren Oberflächen der Kerne 34, 35 können vergleichsweise hohe Toleranzen aufweisen, da sie für die Festlegung der Wandstärke d der Außenwände 17, 18 nicht von Bedeutung sind.For the production, only the outer sides 46a, 47a, 46b, 47b of the sections 36a, 37a, 36b, 37b and the outer sides 48a, 48b of the sections 38a, 38b need to be highly accurate to be edited. The further surfaces of the cores 34, 35 can have comparatively high tolerances since they are not important for determining the wall thickness d of the outer walls 17, 18.

Die Figuren 4 und 5 zeigen die Lagerung der Kerne 34, 35 in der Vorrichtung 29. Jeder der Kerne 34, 35 weist an beiden Enden Vorsprünge 41, 42 zur Befestigung in einer in Strichlinien dargestellten Aufnahme 43 der erfindungsgemäßen Vorrichtung 29 auf. Die beiden Kerne 34, 35 werden über Abstandshalter 44, 45 aneinander abgestützt. Die Vorsprünge 39 werden hierdurch gegen die Innenseite 40 der Außenform 30 gedrückt. In Figur 4 ist die Verwendung starrer Abstandshalter 44 und in Figur 5 die Verwendung elastischer, insbesondere federnd ausgebildeter Abstandshalter 45 dargestellt.Figures 4 and 5 show the mounting of the cores 34, 35 in the device 29. Each of the cores 34, 35 has at both ends projections 41, 42 for attachment in a recording 43 shown in phantom of the device 29 according to the invention. The two cores 34, 35 are supported by spacers 44, 45 to each other. The projections 39 are thereby pressed against the inner side 40 of the outer mold 30. In Figure 4, the use of rigid spacers 44 and in Figure 5, the use of elastic, in particular spring-trained spacers 45 is shown.

Bei der erfindungsgemäßen Vorrichtung wird somit die minimale Wandstärke d der Außenwände 17, 18 dadurch sichergestellt, dass die Kerne 34, 35 sich mit den Vorsprüngen 39 an der Innenseite 40 abstützen. Aufgrund der Verjüngung der Vorsprünge 39 entsteht nur eine punktförmige Öffnung in den Außenwänden 17, 18 der fertiggestellten Schaufel 13, 14. Ein Verschieben der Kerne 34, 35 aufeinander zu wird durch die Abstandshalter 44, 45 verhindert. Es ist somit sichergestellt, dass die gewünschte Wandstärke d der Außenwände 17, 18 zuverlässig eingehalten wird. Die bisher auftretenden Toleranzen der Wandstärke d können wesentlich verringert werden. Die Wandstärke d kann daher von vornherein konstruktiv bereits gegenüber den bekannten Schaufeln 13, 14 und Vorrichtungen 29 verringert werden.In the device according to the invention thus the minimum wall thickness d of the outer walls 17, 18 is ensured by the fact that the cores 34, 35 are supported with the projections 39 on the inner side 40. Due to the tapering of the projections 39, only a point-shaped opening is formed in the outer walls 17, 18 of the finished blade 13, 14. Movement of the cores 34, 35 toward one another is prevented by the spacers 44, 45. It is thus ensured that the desired wall thickness d of the outer walls 17, 18 is reliably maintained. The previously occurring tolerances of the wall thickness d can be substantially reduced. The wall thickness d can therefore be reduced structurally from the outset with respect to the known blades 13, 14 and devices 29.

Ein weiterer Vorteil ist, dass die Wandstärken d der Außenwände 17, 18 nicht mehr voneinander abhängen. Eine Verschiebung oder Verformung des Kerns 34 führt nicht zu einer Änderung der Wandstärke d der Außenwand 18. Auch eine Verschiebung oder Verformung des Kerns 35 führt nicht zu einer Änderung der Wandstärke d der Außenwand 17.Another advantage is that the wall thicknesses d of the outer walls 17, 18 no longer depend on each other. A displacement or deformation of the core 34 does not lead to a change in the wall thickness d of the outer wall 18. Also, a displacement or deformation of the core 35 does not lead to a change in the wall thickness d of the outer wall 17th

Figur 6 zeigt schematisch eine Draufsicht auf Figur 5. Die einzelnen Abschnitte 36a, 36b, 37a, 37b, 38a, 38b der Kerne 34, 35 sind wie dargestellt starr miteinander verbunden. Die Kerne 34, 35 sind über die elastischen Abstandshalter 45 aneinander abgestützt und werden gegen die Innenseite 40 gedrückt. Falls mehrere Abstandshalter 45 verteilt über die gesamte Länge der Kerne 34, 35 eingesetzt werden, können Verschiebungen und Verformungen während des Gießens wesentlich reduziert werden.FIG. 6 schematically shows a plan view of FIG. 5. The individual sections 36a, 36b, 37a, 37b, 38a, 38b of the cores 34, 35 are rigidly connected to each other as shown. The cores 34, 35 are supported on the elastic spacers 45 to each other and are pressed against the inner side 40. If a plurality of spacers 45 distributed over the entire length of the cores 34, 35 are used, shifts and deformations during casting can be significantly reduced.

Zur Herstellung der Schaufel 13, 14 werden zunächst die gewünschten Kerne 34,35 in einer geeigneten, nicht dargestellten Form vorgeformt und anschließend gebrannt. Sie werden danach in die bereitgestellte Außenform 30 eingesetzt. Die Vorsprünge 39 der Abschnitte 36a, 36b, 37a, 37b der beiden Kerne 34, 35 werden zur Anlage an der Innenseite 40 der Außenform 30 gebracht. Zu diesem Zweck werden entweder starre oder elastische Abstandshalter 44, 45 zwischen die beiden Kerne 34, 35 eingebracht. Danach werden die beiden Kerne 34, 35 in den Aufnahmen 43 fixiert.To produce the blade 13, 14, the desired cores 34, 35 are first preformed in a suitable mold, not shown, and then fired. They are then inserted into the provided outer mold 30. The projections 39 of the sections 36a, 36b, 37a, 37b of the two cores 34, 35 are brought into abutment against the inner side 40 of the outer mold 30. For this purpose, either rigid or elastic spacers 44, 45 are introduced between the two cores 34, 35. Thereafter, the two cores 34, 35 are fixed in the receptacles 43.

In den Zwischenraum zwischen die Kerne 34, 35 und die Innenseite 40 der Außenform 30 wird ein geeignetes Material, beispielsweise Wachs eingegossen. Nach dem Erstarren des Wachses wird die Außenform entfernt und der Wachskörper mit einer Schutzschicht versehen. Diese Schutzschicht kann, ebenso wie die Kerne 34, 35, aus einem keramischen Material bestehen.In the space between the cores 34, 35 and the inner side 40 of the outer mold 30, a suitable material, such as wax is poured. After solidification of the wax, the outer shape is removed and the wax body provided with a protective layer. This protective layer may, like the cores 34, 35, consist of a ceramic material.

Das mit der Schutzschicht versehene Wachswerkzeug wird erneut gebrannt. Anschließend wird in den Zwischenraum zwischen der Schutzschicht und den Kernen 34, 35 das gießfähige Material für die Schaufel 13, 14 eingebracht. Nach dem Erstarren dieses Materials werden die Schutzschicht und die Kerne 34, 35 auf geeignete Weise entfernt, beispielsweise mit einer Säure oder Lauge ausgespült.The waxed tool provided with the protective layer is fired again. Subsequently, the pourable material for the blade 13, 14 is introduced into the intermediate space between the protective layer and the cores 34, 35. After solidification of this material, the protective layer and the cores 34, 35 are removed in a suitable manner, for example, rinsed with an acid or alkali.

Die bei den bekannten Verfahren und Vorrichtungen vorliegenden Fertigungs- und Montagetoleranzen bei der Herstellung und Fixierung der Kerne 34, 35, des Wachswerkzeugs und der Schutzschicht können wesentlich verringert werden. Die Wandstärke der Außenwände 17, 18 der Schaufel 13, 14 kann daher deutlich reduziert werden. Hierdurch ergibt sich eine verbesserte Kühlwirkung. Die erforderliche Festigkeit der Schaufel 13, 14 wird durch den Mittelsteg 28 gewährleistet.The manufacturing and assembly tolerances in the production and fixing of the cores 34, 35, the wax tool and the protective layer which are present in the known methods and devices can be substantially reduced. The wall thickness of the outer walls 17, 18 of the blade 13, 14 can therefore be significantly reduced. This results in an improved cooling effect. The required strength of the blade 13, 14 is ensured by the central web 28.

Claims (13)

  1. Blade for a turbine (10),
    in particular for a gas turbine, a medium being able to flow around the blade (13, 14) in the turbine (10) in the direction from the leading edge (22) to the trailing edge (23),
    having two outer walls (17, 18) and
    at least one cavity (24, 25, 26, 27) arranged between the outer walls (17, 18),
    a cavity (24) initially being present in the direction from the leading edge (22) to the trailing edge (23),
    at least one cavity (26, 27) adjoining the cavity (24) in the direction from the leading edge (22) to the trailing edge (23),
    a cavity (25) being arranged at the end as seen from the direction from the leading edge (22) to the trailing edge (23),
    characterized in that
    the at least one cavity (26, 27) is divided
    into in each case two passages (26a, 26b, 27a, 27b) by a centre web (28), which extends in the direction from the leading edge (22) to the trailing edge (23) and is arranged approximately in the axial profile centre,
    one passage (26a, 27a) being bounded by the one outer wall (17) and the centre web (28) and
    another passage (26b, 27b) being bounded by this centre web (28) and the other outer wall (18).
  2. Blade according to Claim 1, characterized in that the outer walls (17, 18) are connected to one another via a plurality of ribs (19, 20, 21) for forming a plurality of cavities (24, 25, 26, 27).
  3. Blade according to Claim 2, characterized in that a cavity (24, 25) at a leading edge (22) and/or a trailing edge (23) of the blade (13; 14) is free of the centre web (28).
  4. Blade according to one of Claims 1 to 3, characterized in that the wall thickness (D) of the centre web (28) is greater than the wall thickness (d) of the outer walls (17, 18).
  5. Device for producing a blade (13, 14) according to one of Claims 1 to 4,
    comprising an outer mould (30) and two cores (34, 45) for forming the at least one cavity (24, 25, 26, 27) and for forming the outer walls (17, 18),
    characterized in that
    each of the two cores (34, 35) has at least one section (36a, 36b, 37a, 37b) which extends from an associated outer wall (17, 18) up to a centre web (28) of the blade (13, 14) to be produced, which centre web (28) runs approximately in the axial profile centre, without being involved in the formation of the other outer wall (18, 17).
  6. Device according to Claim 5, characterized in that the cores (34, 35) are provided with projections (39) for supporting on the outer mould (30).
  7. Device according to Claim 6, characterized in that the projections (39) taper starting from the cores (34, 35) and in particular are of conical design.
  8. Device according to Claim 6 or 7, characterized in that the cores (34, 35) are supported on one another by means of rigid, in particular wedge-shaped, or elastic spacers (44; 45).
  9. Device according to one of Claims 5 to 8, characterized in that the cores (34, 35) are fixed at one or both ends in a receptacle (43) of the outer mould (30) in the longitudinal direction of the blade (13; 14).
  10. Method of producing a blade (13, 14) according to one of Claims 1 to 4 by means of a casting method,
    an outer mould (30) and two cores (34, 35) being provided
    for forming the outer walls (17, 18) and the at least one cavity (24, 25, 26, 27), characterized in that the two cores (34, 35) are supported on one another and are pressed against the inside (40) of the outer mould (30),
    in that at least one section (36a, 36b, 37a, 37b) of each core (34, 35) is supported in such a way
    that the distance between the outside (46a, 47a) of the section (36a, 37a) of the one core (34) and the inside (40) of the outer mould (30) is independent of the distance between the outside (46b, 47b) of the section (36b, 37b) of the other core (35) and the inside (40) of the outer mould (30),
    so that the wall thicknesses (d) of the two outer walls (17, 18), at least in the region of the sections (36a, 37a, 36b, 37b), are formed independently of one another.
  11. Method according to Claim 10, characterized in that the two cores (34, 35) are supported on the inside (40) of the outer mould (30) via projections (39) in order to ensure a minimum wall thickness (d) of the outer walls (17, 18).
  12. Method according to Claim 10 or 11, characterized in that the two cores (34, 35) are supported on one another and are pressed against the inside (40) of the outer mould (30).
  13. Method according to Claim 12, characterized in that the two cores (34, 35) are supported on one another by means of rigid or elastic spacers (44; 45).
EP00120035A 2000-09-14 2000-09-14 Apparatus and method for producing a turbine blade and turbine blade Expired - Lifetime EP1188500B1 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
DE50013334T DE50013334D1 (en) 2000-09-14 2000-09-14 Apparatus and method for producing a blade for a turbine as well as correspondingly produced blade
EP00120035A EP1188500B1 (en) 2000-09-14 2000-09-14 Apparatus and method for producing a turbine blade and turbine blade
CNB018027393A CN1213823C (en) 2000-09-14 2001-09-13 Device and method for producing blade for turbine and blade produced according to this method
JP2002526531A JP4350372B2 (en) 2000-09-14 2001-09-13 Turbine blade, manufacturing method and manufacturing apparatus thereof
US10/239,792 US6805535B2 (en) 2000-09-14 2001-09-13 Device and method for producing a blade for a turbine and blade produced according to this method
PCT/EP2001/010600 WO2002022291A1 (en) 2000-09-14 2001-09-13 Device and method for producing a blade for a turbine and blade produced according to this method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP00120035A EP1188500B1 (en) 2000-09-14 2000-09-14 Apparatus and method for producing a turbine blade and turbine blade

Publications (2)

Publication Number Publication Date
EP1188500A1 EP1188500A1 (en) 2002-03-20
EP1188500B1 true EP1188500B1 (en) 2006-08-16

Family

ID=8169834

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00120035A Expired - Lifetime EP1188500B1 (en) 2000-09-14 2000-09-14 Apparatus and method for producing a turbine blade and turbine blade

Country Status (6)

Country Link
US (1) US6805535B2 (en)
EP (1) EP1188500B1 (en)
JP (1) JP4350372B2 (en)
CN (1) CN1213823C (en)
DE (1) DE50013334D1 (en)
WO (1) WO2002022291A1 (en)

Families Citing this family (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2852999B1 (en) * 2003-03-28 2007-03-23 Snecma Moteurs TURBOMACHINE RIDDLE AUBE AND METHOD OF MANUFACTURING THE SAME
US20050000674A1 (en) * 2003-07-01 2005-01-06 Beddard Thomas Bradley Perimeter-cooled stage 1 bucket core stabilizing device and related method
FR2874186B1 (en) * 2004-08-12 2008-01-25 Snecma Moteurs Sa PROCESS FOR THE PRODUCTION BY LOST WAX MOLDING OF PARTS COMPRISING AT LEAST ONE CAVITY.
GB0418906D0 (en) * 2004-08-25 2004-09-29 Rolls Royce Plc Internally cooled aerofoils
US7481623B1 (en) * 2006-08-11 2009-01-27 Florida Turbine Technologies, Inc. Compartment cooled turbine blade
US8087447B2 (en) * 2006-10-30 2012-01-03 United Technologies Corporation Method for checking wall thickness of hollow core airfoil
US7487819B2 (en) * 2006-12-11 2009-02-10 General Electric Company Disposable thin wall core die, methods of manufacture thereof and articles manufactured therefrom
US7762774B2 (en) * 2006-12-15 2010-07-27 Siemens Energy, Inc. Cooling arrangement for a tapered turbine blade
US8277193B1 (en) * 2007-01-19 2012-10-02 Florida Turbine Technologies, Inc. Thin walled turbine blade and process for making the blade
US8506256B1 (en) * 2007-01-19 2013-08-13 Florida Turbine Technologies, Inc. Thin walled turbine blade and process for making the blade
US8066052B2 (en) * 2007-06-07 2011-11-29 United Technologies Corporation Cooled wall thickness control
FR2933884B1 (en) * 2008-07-16 2012-07-27 Snecma PROCESS FOR MANUFACTURING AN AUBING PIECE
GB0901129D0 (en) * 2009-01-26 2009-03-11 Rolls Royce Plc Rotor blade
US8013569B2 (en) * 2009-03-06 2011-09-06 Sustainable Structures LLC Renewable energy vehicle charging station
US8453327B2 (en) * 2010-02-05 2013-06-04 Siemens Energy, Inc. Sprayed skin turbine component
US11000899B2 (en) * 2012-01-29 2021-05-11 Raytheon Technologies Corporation Hollow airfoil construction utilizing functionally graded materials
US8408446B1 (en) 2012-02-13 2013-04-02 Honeywell International Inc. Methods and tooling assemblies for the manufacture of metallurgically-consolidated turbine engine components
US9033670B2 (en) 2012-04-11 2015-05-19 Honeywell International Inc. Axially-split radial turbines and methods for the manufacture thereof
US9115586B2 (en) 2012-04-19 2015-08-25 Honeywell International Inc. Axially-split radial turbine
BR112014026360A2 (en) 2012-04-23 2017-06-27 Gen Electric turbine airfoil and turbine blade
EP2706195A1 (en) * 2012-09-05 2014-03-12 Siemens Aktiengesellschaft Impingement tube for gas turbine vane with a partition wall
US9476305B2 (en) 2013-05-13 2016-10-25 Honeywell International Inc. Impingement-cooled turbine rotor
WO2015026535A1 (en) * 2013-08-23 2015-02-26 Siemens Energy, Inc. Turbine component casting core with high resolution region
CN104015247B (en) * 2014-05-30 2016-07-06 西安交通大学 The method that the sintering creep of Integral hollow turbo blade ceramic-mould core controls
US20170232506A1 (en) * 2014-10-15 2017-08-17 Siemens Aktiengesellschaft Die cast system with ceramic casting mold for forming a component usable in a gas turbine engine
FR3030333B1 (en) * 2014-12-17 2017-01-20 Snecma PROCESS FOR MANUFACTURING A TURBOMACHINE BLADE COMPRISING A TOP COMPRISING A COMPLEX TYPE BATHTUB
US10052683B2 (en) * 2015-12-21 2018-08-21 General Electric Company Center plenum support for a multiwall turbine airfoil casting
US10286450B2 (en) * 2016-04-27 2019-05-14 General Electric Company Method and assembly for forming components using a jacketed core
US20180161866A1 (en) 2016-12-13 2018-06-14 General Electric Company Multi-piece integrated core-shell structure for making cast component
US11813669B2 (en) 2016-12-13 2023-11-14 General Electric Company Method for making an integrated core-shell structure
US10815791B2 (en) * 2017-12-13 2020-10-27 Solar Turbines Incorporated Turbine blade cooling system with upper turning vane bank
US20240218828A1 (en) 2022-11-01 2024-07-04 General Electric Company Gas Turbine Engine

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB628522A (en) * 1946-07-26 1949-08-30 Philippe Robert Device for ensuring the fixity of a core in a mould
US5813835A (en) * 1991-08-19 1998-09-29 The United States Of America As Represented By The Secretary Of The Air Force Air-cooled turbine blade
US5296308A (en) * 1992-08-10 1994-03-22 Howmet Corporation Investment casting using core with integral wall thickness control means
DE19821770C1 (en) 1998-05-14 1999-04-15 Siemens Ag Mold for producing a hollow metal component
DE19905887C1 (en) * 1999-02-11 2000-08-24 Abb Alstom Power Ch Ag Hollow cast component

Also Published As

Publication number Publication date
US6805535B2 (en) 2004-10-19
EP1188500A1 (en) 2002-03-20
JP2004508201A (en) 2004-03-18
CN1213823C (en) 2005-08-10
CN1392809A (en) 2003-01-22
US20030047298A1 (en) 2003-03-13
DE50013334D1 (en) 2006-09-28
JP4350372B2 (en) 2009-10-21
WO2002022291A1 (en) 2002-03-21

Similar Documents

Publication Publication Date Title
EP1188500B1 (en) Apparatus and method for producing a turbine blade and turbine blade
DE3211139C1 (en) Axial turbine blades, in particular axial turbine blades for gas turbine engines
DE60017166T2 (en) GUN CORE FOR AN INNER COOLED TURBINE BLADE WHICH DOES NOT HAVE TO BE FASTENED TO FOOD OPENING
EP1247602B1 (en) Method for producing an airfoil
EP2300178B1 (en) Method for producing blade for a gas turbine by a casting process and mould core for the blade
EP2611990B1 (en) Turbine blade for a gas turbine
EP1267040A2 (en) Gas turbine blade
CH697919A2 (en) Turbine blade having a concave cooling passage and arranged therein opposite swirling currents causing turbulators.
EP1113145A1 (en) Blade for gas turbines with metering section at the trailing edge
EP2615243B1 (en) Blade ring segment for a fluid flow engine and method for producing the same
WO1999059748A1 (en) Method and device for producing a metallic hollow body
EP2143883A1 (en) Turbine blade and corresponding casting core
EP1245785B1 (en) Turbine airfoil manufacturing method
EP1895096A1 (en) Cooled turbine rotor blade
WO2008092725A1 (en) Turbine bucket
EP3062054A1 (en) Heat exchanger, in particular for a motor vehicle
DE102016118026A1 (en) Rotor, in particular rotor for an electric machine, electric machine and method for producing a rotor
DE69503127T2 (en) COOLED GAS TURBINE SHOVEL
DE10033271A1 (en) Water jacket core
DE69110777T2 (en) Stator blades for turbines, made of a thermostructural composite material.
EP1857244A1 (en) Cooled mold insert for injection moulds
DE10129975B4 (en) Mold for the core of a gas turbine blade or the like
EP2163726A1 (en) Turbine blade with a modular, tiered trailing edge
WO2010121939A1 (en) Casting apparatus for producing a turbine rotor blade of a gas turbine and turbine rotor blade
EP3527353A2 (en) Monolithic remote control

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB IT

Kind code of ref document: A1

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

17P Request for examination filed

Effective date: 20020506

AKX Designation fees paid

Free format text: DE FR GB IT

17Q First examination report despatched

Effective date: 20040223

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB IT

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 50013334

Country of ref document: DE

Date of ref document: 20060928

Kind code of ref document: P

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20061026

ET Fr: translation filed
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20070518

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 17

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 18

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20180926

Year of fee payment: 19

Ref country code: FR

Payment date: 20180924

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20180911

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20181119

Year of fee payment: 19

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 50013334

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20200401

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190914

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20190914

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190914

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190930