EP1247602B1 - Method for producing an airfoil - Google Patents

Method for producing an airfoil Download PDF

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Publication number
EP1247602B1
EP1247602B1 EP01108480A EP01108480A EP1247602B1 EP 1247602 B1 EP1247602 B1 EP 1247602B1 EP 01108480 A EP01108480 A EP 01108480A EP 01108480 A EP01108480 A EP 01108480A EP 1247602 B1 EP1247602 B1 EP 1247602B1
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EP
European Patent Office
Prior art keywords
blade
spacers
core
turbine blade
turbine
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
EP01108480A
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German (de)
French (fr)
Other versions
EP1247602A1 (en
Inventor
Winfried Dr. Esser
Michael Haendler
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
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Siemens AG
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Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to DE50113629T priority Critical patent/DE50113629D1/en
Priority to ES01108480T priority patent/ES2301504T3/en
Priority to EP01108480A priority patent/EP1247602B1/en
Priority to JP2002098225A priority patent/JP2002349285A/en
Priority to US10/117,633 priority patent/US6739381B2/en
Priority to CNB021054355A priority patent/CN1250361C/en
Publication of EP1247602A1 publication Critical patent/EP1247602A1/en
Application granted granted Critical
Publication of EP1247602B1 publication Critical patent/EP1247602B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • 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

Definitions

  • the invention relates to a method for producing a turbine blade in a hollow profile.
  • Gas turbines are used in many areas to drive generators or work machines.
  • the energy content of a fuel is used to generate a rotational movement of a turbine shaft.
  • the fuel is burned in a combustion chamber, compressed air being supplied by an air compressor.
  • the working medium produced in the combustion chamber by the combustion of the fuel, under high pressure and at high temperature, is guided via a turbine unit arranged downstream of the combustion chambers, where it relaxes to perform its work.
  • the momentum transfer from the working medium required for generating the rotational movement of the turbine shaft is achieved via turbine blades.
  • a number of profiled blades are arranged on the turbine shaft, which are supplemented for guiding the flow medium in the turbine unit by associated with the turbine housing vanes.
  • the turbine blades usually have a profiled airfoil extending along a blade axis.
  • such gas turbines are usually thermodynamic reasons for particularly high outlet temperatures of the off of the combustion chamber and designed in the inflowing into the turbine unit working fluid of about 1200 ° C to about 1300 ° C.
  • the components of the gas turbine in particular the turbine blades, are exposed to comparatively high thermal loads.
  • a high reliability and a long life of the respective components To ensure the affected components are usually designed cooled.
  • the turbine blades are usually formed as a so-called hollow profile.
  • the profiled airfoil has for this purpose in its inner region also referred to as a vane core cavities in which a cooling medium can be performed.
  • a cooling medium can be performed.
  • the coolant channels thus formed, it is thus possible to apply the coolant to the areas of the respective airfoil that are subject to particular thermal stress.
  • a particularly favorable cooling effect and thus a particularly high level of operational reliability can be achieved in that the coolant channels occupy a comparatively large spatial area in the interior of the respective airfoil, and in that the coolant is guided as close as possible to the respective surface exposed to the hot gas.
  • the respective turbine blade can be flowed through in multiple channels, with a plurality of coolant channels, which can be acted upon by coolant and are separated from one another by comparatively thin partitions, being provided in the interior of the blade profile.
  • Such turbine blades are usually made by casting.
  • a mold adapted in its contour to the desired blade profile is poured out with blade material.
  • core elements are arranged during casting in the casting mold, which are removed after the casting process from the blade body, so that the desired for the coolant channels cavities arise.
  • a plurality of in each case form-specific adapted core elements is arranged in the casting mold.
  • core openings remain in the top and bottom of the turbine blade, which can be closed by appropriate measures. This is for example from the EP 1 027 943 A1 It is known to provide a further recess in the turbine blade which completely crosses the core opening originating from the core support. By inserting a closure piece in the recess then the inner opening of the core opening can be completely covered and thus closed. The core opening itself remains free.
  • spacers can additionally be used to position the core elements in the casting mold in order to achieve defined distances between core elements and casting molds for defined wall thicknesses of the turbine blade.
  • These spacers leave when removing the core elements undesirable additional cavities that hinder the actually intended fluidic decoupling of the respective core areas from each other and in particular from the outside of the turbine blade. Therefore, the spacers are usually designed tapered, so as to safely preclude the formation of unacceptably large openings.
  • the spacers are designed such that when casting the turbine blade as possible a continuous, not completely penetrated by the respective spacer surface or partition at the respective location results. Nevertheless, the cast turbine blade usually has weak points at the locations of the spacers which are at least one local one Promote cracking in the area in question. The error or reject rate in the manufacture of the turbine blades is thus comparatively high.
  • the invention is therefore based on the object to provide a method for producing a turbine blade in a hollow profile, with a particularly low error or reject rate is achievable.
  • This object is achieved according to the invention by connecting a first core element via a number of approximately cylindrical spacers to a further core element and / or to a casting mold, wherein the cavities left by the core elements in the casting mold are poured out by blade material, and wherein the after removal the core elements and the spacer in the turbine blade remaining, openings produced by the spacers are closed by plug elements.
  • the invention is based on the consideration that a possible cause of error in the manufacture of the turbine blades just to be seen in those vulnerabilities that arise as a result of the use of tapered spacers in the connection of the core elements.
  • cylindrical spacers are now used instead of conical or tapered spacers. Although these also leave weak points in the material of the cast turbine blade, which can be found without further ado. Contrary to the principle of keeping the weaknesses in the manufacture of the turbine blades particularly small, it is thus provided to make this particularly easy to find at the cost of comparatively larger vulnerabilities. The thus reliably detectable weak points can then be effectively closed by attaching a closure element and in a manner not affecting the subsequent operation of the turbine blade way.
  • the spacers are preferably dimensioned in their longitudinal extent such that their ends protrude beyond the resulting blade profile, so that arise during the casting of the turbine blade in any case through the respective structure completely continuous holes.
  • the plug elements are compressed in an advantageous development after their introduction into the respective opening. By such compression is ensured that the respective Plug element expands in width so that it receives a particularly intimate positive and non-positive connection with the edge of the respective opening. The opening is thus closed particularly effectively.
  • a suitable pin-shaped element can be used in each case.
  • blind rivets or impact pins are used as plug elements.
  • the advantages achieved by the invention are in particular that by the deliberate acceptance of comparatively large openings in the initially cast blade body each caused by the spacers vulnerability in the blade body is clearly identifiable. Hidden vulnerabilities are thus safely avoided.
  • the spacers can also be comparatively large dimensions, so that only a comparatively small number of spacers is required for reliable positioning of the core elements during the casting process. This also reduces the number of total resulting openings or weak points, so that the cost of resealing these vulnerabilities is kept particularly low.
  • the turbine blade 1 comprises an airfoil blade 2 which extends along a blade axis and is also referred to as a blade profile.
  • the airfoil 2 is, as in FIG FIG. 1 can be seen, profiled or curved on its surface, so that a particularly favorable guidance of the gas turbine flowing through the working medium is ensured.
  • the gas turbine is designed for thermodynamic reasons for an outlet temperature of their working medium from the combustion chamber of comparatively high temperatures of for example 1200 ° C to 1300 ° C.
  • the turbine blade 1 is designed to be coolable in addition to other components.
  • the blade 2 includes a number of integrated cavities 4, 6, each serving as a flow channel for a coolant.
  • the cavities 4 have a comparatively large cross-section and serve as the main flow path for the coolant.
  • a comparatively large wall thickness of the remaining structural parts of the turbine blade 1 is required for mechanical stabilization.
  • a casting mold which has a cavity adapted to the desired outer contour of the turbine blade 1.
  • 6 are in this mold in its outer contour to the desired cavities 4 and 6 adapted so-called core elements positioned.
  • the casting mold is poured out with blade material, wherein the intended cavities 4 and 6 are kept free of blade material by the core elements.
  • the core elements are removed again, so that the desired cavities 4 and 6 remain in the cast turbine blade 1.
  • the core element 10 comprises a base plate 12 which is adapted in shape to the contour desired for the respective cavity 6.
  • a number of spacers 14 are also arranged on the base plate 12.
  • Each spacer 14 is designed substantially cylindrical and formed in its length such that it completely penetrates the provided in its space area blade profile. In the embodiment, the spacers 14 are thus formed in their length so that it exceeds the thickness of the respective cavity 6 surrounding material walls. With their free ends, the spacers 14 are each in the mold or in an adjacent Core element anchored, so that there is a substantially stable structure during the casting process.
  • the thus cast blade body at those locations where the spacers 14 were located through openings. These are thus easily recognizable and can thus be subjected to further treatment.
  • the openings remaining after the removal of the core elements and the spacers in the turbine blade 1, generated by the spacers 14 are thereby closed by suitable plug elements, as for some different types of plug elements in FIG. 3 is shown.
  • FIG. 3 shows in the manner of several alternative embodiments, a number of different types of plug elements, with which the openings left by the spacers 14 may be closed.
  • a Einschlagpin 20 may be provided as a plug element for the respective opening, which includes a conically shaped fitting 22 in its center region in the manner of a barb.
  • a one-sided compressed impact pin 24 which is particularly suitable in the event that the opening to be closed on one side still the actual opening channel limiting projections 26 has.
  • a continuous pin 28 may be provided, which has been compressed on both sides after its penetration into the respective opening. Just by the compression occurs here as a result of the self-adjusting thickening in the central region of the pin 28 a particularly good sealing effect.
  • a pin 30 inserted in a continuous opening, the respective opening having bevels in its end regions. In a compression of the pin 30, this is deformed in its end regions, with its pin material in the corresponding Bevels of the respective openings inserts. Furthermore, the use of a pin 32 is possible, which is sealed in its end by attaching a soldering cap 34 and then soldering.

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

Description

Die Erfindung betrifft ein Verfahren zur Herstellung einer Turbinenschaufel in Hohlprofil.The invention relates to a method for producing a turbine blade in a hollow profile.

Gasturbinen werden in vielen Bereichen zum Antrieb von Generatoren oder von Arbeitsmaschinen eingesetzt. Dabei wird der Energieinhalt eines Brennstoffs zur Erzeugung einer Rotationsbewegung einer Turbinenwelle benutzt. Der Brennstoff wird dazu in einer Brennkammer verbrannt, wobei von einem Luftverdichter verdichtete Luft zugeführt wird. Das in der Brennkammer durch die Verbrennung des Brennstoffs erzeugte, unter hohem Druck und unter hoher Temperatur stehende Arbeitsmedium wird dabei über eine der Brennkammern nachgeschaltete Turbineneinheit geführt, wo es sich arbeitsleistend entspannt. Der zur Erzeugung der Rotationsbewegung der Turbinenwelle erforderliche Impulsübertrag aus dem Arbeitsmedium wird dabei über Turbinenschaufeln erreicht. Dazu sind an der Turbinenwelle eine Anzahl von profilierten Laufschaufeln angeordnet, die zur Führung des Strömungsmediums in der Turbineneinheit durch mit dem Turbinengehäuse verbundene Leitschaufeln ergänzt sind. Für eine geeignete Führung des Strömungsmediums weisen die Turbinenschaufeln dabei üblicherweise ein profiliertes, entlang einer Schaufelachse erstrecktes Schaufelblatt auf.Gas turbines are used in many areas to drive generators or work machines. In this case, the energy content of a fuel is used to generate a rotational movement of a turbine shaft. For this purpose, the fuel is burned in a combustion chamber, compressed air being supplied by an air compressor. The working medium produced in the combustion chamber by the combustion of the fuel, under high pressure and at high temperature, is guided via a turbine unit arranged downstream of the combustion chambers, where it relaxes to perform its work. The momentum transfer from the working medium required for generating the rotational movement of the turbine shaft is achieved via turbine blades. For this purpose, a number of profiled blades are arranged on the turbine shaft, which are supplemented for guiding the flow medium in the turbine unit by associated with the turbine housing vanes. For a suitable guidance of the flow medium, the turbine blades usually have a profiled airfoil extending along a blade axis.

Zur Erreichung eines besonders günstigen Wirkungsgrads sind derartige Gasturbinen aus thermodynamischen Gründen üblicherweise für besonders hohe Austrittstemperaturen des aus der Brennkammer ab- und die in die in die Turbineneinheit einströmenden Arbeitsmediums von etwa 1200 °C bis etwa 1300 °C ausgelegt. Bei derartig hohen Temperaturen sind die Komponenten der Gasturbine, insbesondere die Turbinenschaufeln, vergleichsweise hohen thermischen Belastungen ausgesetzt. Um auch bei derartigen Betriebsbedingungen eine hohe Zuverlässigkeit und eine lange Lebensdauer der jeweiligen Komponenten zu gewährleisten, sind die betroffenen Bauteile üblicherweise kühlbar ausgebildet.To achieve a particularly favorable efficiency such gas turbines are usually thermodynamic reasons for particularly high outlet temperatures of the off of the combustion chamber and designed in the inflowing into the turbine unit working fluid of about 1200 ° C to about 1300 ° C. At such high temperatures, the components of the gas turbine, in particular the turbine blades, are exposed to comparatively high thermal loads. Even with such operating conditions, a high reliability and a long life of the respective components To ensure the affected components are usually designed cooled.

Daher sind in modernen Gasturbinen die Turbinenschaufeln üblicherweise als sogenanntes Hohlprofil ausgebildet. Das profilierte Schaufelblatt weist dazu in seinem Innenbereich auch als Schaufelkern bezeichnete Hohlräume auf, in denen ein Kühlmedium geführt werden kann. Durch die solchermaßen gebildeten Kühlmittelkanäle ist somit eine Beaufschlagung der thermisch besonders beanspruchten Bereiche des jeweiligen Schaufelblatts mit Kühlmittel ermöglicht. Eine besonders günstige Kühlwirkung und somit eine besonders hohe Betriebssicherheit ist dabei erreichbar, indem die Kühlmittelkanäle einen vergleichsweise großen Raumbereich im Inneren des jeweiligen Schaufelblatts einnehmen, und indem das Kühlmittel möglichst nah an der jeweiligen, dem Heißgas ausgesetzten Oberfläche geführt ist. Um bei einer derartigen Auslegung andererseits eine ausreichende mechanische Stabilität und Belastbarkeit sicherzustellen, kann die jeweilige Turbinenschaufel mehrkanalig durchströmt sein, wobei im Inneren des Schaufelprofils eine Mehrzahl von mit Kühlmittel beaufschlagbaren, jeweils voneinander durch vergleichsweise dünne Trennwände getrennte Kühlmittelkanäle vorgesehen sind.Therefore, in modern gas turbines, the turbine blades are usually formed as a so-called hollow profile. The profiled airfoil has for this purpose in its inner region also referred to as a vane core cavities in which a cooling medium can be performed. By means of the coolant channels thus formed, it is thus possible to apply the coolant to the areas of the respective airfoil that are subject to particular thermal stress. A particularly favorable cooling effect and thus a particularly high level of operational reliability can be achieved in that the coolant channels occupy a comparatively large spatial area in the interior of the respective airfoil, and in that the coolant is guided as close as possible to the respective surface exposed to the hot gas. On the other hand, in order to ensure a sufficient mechanical stability and load capacity in such a design, the respective turbine blade can be flowed through in multiple channels, with a plurality of coolant channels, which can be acted upon by coolant and are separated from one another by comparatively thin partitions, being provided in the interior of the blade profile.

Derartige Turbinenschaufeln werden üblicherweise durch Gießen hergestellt. Dazu wird eine in ihrer Kontur an das gewünschte Schaufelprofil angepaßte Gießform mit Schaufelmaterial ausgegossen. Zur Herstellung der genannten Schaufelkerne oder Strömungskanäle für das Kühlmittel werden beim Gießen in der Gießform sogenannte Kernelemente angeordnet, die nach erfolgtem Gießvorgang aus dem Schaufelkörper entfernt werden, so daß die für die Kühlmittelkanäle gewünschten Hohlräume entstehen. Bei der Herstellung einer Turbinenschaufel mit mehreren, durch Trennwände voneinander getrennten Kühlmittelkanälen wird dabei eine Mehrzahl jeweils formspezifisch angepaßter Kernelemente in der Gießform angeordnet.Such turbine blades are usually made by casting. For this purpose, a mold adapted in its contour to the desired blade profile is poured out with blade material. To produce said blade cores or flow channels for the coolant so-called core elements are arranged during casting in the casting mold, which are removed after the casting process from the blade body, so that the desired for the coolant channels cavities arise. In the manufacture of a turbine blade with a plurality of coolant channels which are separated from one another by partitions, a plurality of in each case form-specific adapted core elements is arranged in the casting mold.

Die Positionierung der Kernelemente in der Gießform erfolgt über damit verbundene Kernstützen, welche zumeist kopf- und fußseitig die Turbinenschaufel durchdringen. Nach dem Gießen der Turbinenschaufel und dem Entfernen der Kernelemente und Kernstützen verbleiben Kernöffnungen im Kopf- und Fußbereich der Turbinenschaufel, welche durch geeignete Maßnahmen verschlossen werden können. Hierzu ist beispielsweise aus der EP 1 027 943 A1 bekannt, eine weitere Aussparung in der Turbinenschaufel vorzusehen, welche die von der Kernstütze herrührende Kernöffnung vollständig kreuzt. Durch das Einsetzen eines Verschlussstückes in die Aussparung kann dann die innen liegende Öffnung der Kernöffnung vollständig abgedeckt und somit verschlossen werden. Die Kernöffnung selber bleibt frei.The positioning of the core elements in the mold takes place via associated core supports, which usually penetrate the turbine blade on the head and foot sides. After casting the turbine blade and removing the core elements and core posts, core openings remain in the top and bottom of the turbine blade, which can be closed by appropriate measures. This is for example from the EP 1 027 943 A1 It is known to provide a further recess in the turbine blade which completely crosses the core opening originating from the core support. By inserting a closure piece in the recess then the inner opening of the core opening can be completely covered and thus closed. The core opening itself remains free.

Neben der Verwendung von Kernstützen können zur Positionierung der Kernelemente zusätzlich noch Abstandhalter diese mit der Gießform verbinden, um definierte Abstände zwischen Kernelementen und Gießformen für definierte Wandstärken der Turbinenschaufel zu erreichen. Diese Abstandhalter hinterlassen beim Entfernen der Kernelemente unerwünschte zusätzliche Hohlräume, die die eigentlich vorgesehene strömungstechnische Entkopplung der jeweiligen Kernbereiche voneinander und insbesondere vom Außenbereich der Turbinenschaufel behindern. Daher sind die Abstandhalter üblicherweise spitz zulaufend ausgestaltet, um somit die Bildung von inakzeptabel großen Öffnungen sicher auszuschließen. Die Abstandhalter sind dabei derart ausgelegt, daß sich beim Gießen der Turbinenschaufel möglichst eine durchgehende, nicht vom jeweiligen Abstandhalter vollständig durchdrungene Oberfläche oder Trennwand an der jeweiligen Stelle ergibt. Dennoch weist die gegossene Turbinenschaufel an den Stellen der Abstandhalter üblicherweise Schwachstellen auf, die zumindest eine lokale Rißbildung im fraglichen Bereich fördern. Die Fehler- oder Ausschußquote bei der Herstellung der Turbinenschaufeln ist somit vergleichsweise hoch.In addition to the use of core posts, spacers can additionally be used to position the core elements in the casting mold in order to achieve defined distances between core elements and casting molds for defined wall thicknesses of the turbine blade. These spacers leave when removing the core elements undesirable additional cavities that hinder the actually intended fluidic decoupling of the respective core areas from each other and in particular from the outside of the turbine blade. Therefore, the spacers are usually designed tapered, so as to safely preclude the formation of unacceptably large openings. The spacers are designed such that when casting the turbine blade as possible a continuous, not completely penetrated by the respective spacer surface or partition at the respective location results. Nevertheless, the cast turbine blade usually has weak points at the locations of the spacers which are at least one local one Promote cracking in the area in question. The error or reject rate in the manufacture of the turbine blades is thus comparatively high.

Der Erfindung liegt daher die Aufgabe zugrunde, ein Verfahren zur Herstellung einer Turbinenschaufel in Hohlprofil anzugeben, mit dem eine besonders geringe Fehler- oder Ausschußquote erreichbar ist.The invention is therefore based on the object to provide a method for producing a turbine blade in a hollow profile, with a particularly low error or reject rate is achievable.

Diese Aufgabe wird erfindungsgemäß gelöst, indem ein erstes Kernelement über eine Anzahl annähernd zylindrischer Abstandhalter mit einem weiteren Kernelement und/oder mit einer Gießform verbunden wird, wobei die durch die Kernelemente in der Gießform gelassenen Hohlräume durch Schaufelmaterial ausgegossen werden, und wobei die nach der Entfernung der Kernelemente und der Abstandhalter in der Turbinenschaufel verbleibenden, durch die Abstandhalter erzeugten Öffnungen durch Stopfenelemente verschlossen werden.This object is achieved according to the invention by connecting a first core element via a number of approximately cylindrical spacers to a further core element and / or to a casting mold, wherein the cavities left by the core elements in the casting mold are poured out by blade material, and wherein the after removal the core elements and the spacer in the turbine blade remaining, openings produced by the spacers are closed by plug elements.

Die Erfindung geht dabei von der Überlegung aus, daß eine mögliche Fehlerursache bei der Herstellung der Turbinenschaufeln gerade in denjenigen Schwachstellen zu sehen ist, die sich infolge der Verwendung von spitz zulaufenden Abstandhaltern bei der Verbindung der Kernelemente einstellen. Diese Schwachstellen beeinträchtigen einerseits die Stabilität des Schaufelmaterials an der fraglichen Stelle, sind aber andererseits bei einer Materialprüfung nur schwer oder überhaupt nicht identifizierbar. Somit können unentdeckte Schwachstellen im Material verbleiben, die später durch Rißbildung an der fraglichen Stelle zu einem Ausfall der Turbinenschaufel insgesamt führen können.The invention is based on the consideration that a possible cause of error in the manufacture of the turbine blades just to be seen in those vulnerabilities that arise as a result of the use of tapered spacers in the connection of the core elements. These weaknesses, on the one hand, affect the stability of the blade material at the point in question, but on the other hand are difficult or impossible to identify in a material test. Thus, undetected weak spots can remain in the material, which can subsequently lead to failure of the turbine blade as a whole due to crack formation at the point in question.

Um dem wirksam zu begegnen, werden statt konischer oder spitz zulaufender Abstandhalter nunmehr zylindrische Abstandhalter verwendet. Diese hinterlassen zwar auch Schwachstellen im Material der gegossenen Turbinenschaufel, die aber ohne weiteres auffindbar sind. Unter Abkehr vom Grundsatz, die Schwachstellen bei der Herstellung der Turbinenschaufeln besonders klein zu halten, ist somit vorgesehen, unter Inkaufnahme vergleichsweise größerer Schwachstellen diese besonders einfach auffindbar zu machen. Die somit zuverlässig auffindbaren Schwachstellen können anschließend durch Anbringen eines Verschlußelements wirksam und in einer den späteren Betrieb der Turbinenschaufel nicht beeinträchtigenden Weise verschlossen werden.To counteract this effectively, cylindrical spacers are now used instead of conical or tapered spacers. Although these also leave weak points in the material of the cast turbine blade, which can be found without further ado. Contrary to the principle of keeping the weaknesses in the manufacture of the turbine blades particularly small, it is thus provided to make this particularly easy to find at the cost of comparatively larger vulnerabilities. The thus reliably detectable weak points can then be effectively closed by attaching a closure element and in a manner not affecting the subsequent operation of the turbine blade way.

Die Abstandhalter sind dabei vorzugsweise in ihrer Längsausdehnung derart bemessen, daß ihre Enden über das entstehende Schaufelprofil hinausstehen, so daß beim Gießen der Turbinenschaufel in jedem Fall durch die jeweilige Struktur vollständig durchgehende Löcher entstehen.The spacers are preferably dimensioned in their longitudinal extent such that their ends protrude beyond the resulting blade profile, so that arise during the casting of the turbine blade in any case through the respective structure completely continuous holes.

Um die Dichtigkeit der durch die Abstandhalter gelassenen Öffnungen auch bei einem Betrieb der Turbinenschaufel unter vergleichsweise widrigen Betriebsbedingungen sicherzustellen, werden die Stopfenelemente in vorteilhafter Weiterbildung nach ihrem Einbringen in die jeweilige Öffnung gestaucht. Durch eine derartige Stauchung ist gewährleistet, daß das jeweilige Stopfenelement sich in seiner Breite derart ausdehnt, daß es eine besonders innige formschlüssige und kraftschlüssige Verbindung mit dem Rand der jeweiligen Öffnung eingeht. Die Öffnung ist somit besonders wirkungsvoll verschlossen.In order to ensure the tightness of the openings left by the spacers even during operation of the turbine blade under comparatively adverse operating conditions, the plug elements are compressed in an advantageous development after their introduction into the respective opening. By such compression is ensured that the respective Plug element expands in width so that it receives a particularly intimate positive and non-positive connection with the edge of the respective opening. The opening is thus closed particularly effectively.

Zum weiteren Absichern des Stopfenelements in seiner jeweiligen Öffnung wird dieses vorteilhafterweise nach seinem Einbringen in die jeweilige Öffnung verlötet.To further secure the plug element in its respective opening, this is advantageously soldered after its introduction into the respective opening.

Als Stopfenelement kann jeweils ein geeignetes stiftförmiges Element verwendet werden. Vorteilhafterweise werden als Stopfenelemente jedoch Blindnieten oder Einschlagpins verwendet.As a plug element, a suitable pin-shaped element can be used in each case. Advantageously, however, blind rivets or impact pins are used as plug elements.

Die mit der Erfindung erzielten Vorteile bestehen insbesondere darin, daß durch die bewußte Inkaufnahme vergleichsweise großer Öffnungen im zunächst gegossenen Schaufelkörper jede durch die Abstandhalter hervorgerufene Schwachstelle im Schaufelkörper eindeutig identifizierbar ist. Verborgene Schwachstellen sind somit sicher vermieden. Durch das anschließende Einbringen der Stopfenelemente ist zudem ein besonders wirksames Verschließen der jeweiligen Öffnungen gewährleistet, so daß die Turbinenschaufel auch unter vergleichsweise widrigen Betriebsbedingungen besonders belastbar ist. Die Abstandhalter können zudem vergleichsweise groß dimensioniert sein, so daß für eine zuverlässige Positionierung der Kernelemente während des Gießvorgangs nur eine vergleichsweise geringe Anzahl von Abstandhaltern erforderlich ist. Damit reduziert sich auch die Anzahl der insgesamt entstehenden Öffnungen oder Schwachstellen, so daß der Aufwand beim Wiederverschließen dieser Schwachstellen besonders gering gehalten ist.The advantages achieved by the invention are in particular that by the deliberate acceptance of comparatively large openings in the initially cast blade body each caused by the spacers vulnerability in the blade body is clearly identifiable. Hidden vulnerabilities are thus safely avoided. By the subsequent introduction of the plug elements also a particularly effective closure of the respective openings is ensured, so that the turbine blade is particularly resilient even under relatively adverse operating conditions. The spacers can also be comparatively large dimensions, so that only a comparatively small number of spacers is required for reliable positioning of the core elements during the casting process. This also reduces the number of total resulting openings or weak points, so that the cost of resealing these vulnerabilities is kept particularly low.

Ein Ausführungsbeispiel der Erfindung wird anhand einer Zeichnung näher erläutert. Darin zeigen:

Figur 1
eine profilierte Turbinenschaufel im Querschnitt,
Figur 2
ein Kernelement, und
Figur 3
eine Anzahl von Stopfenelementen in jeweils verschiedenartiger Ausführungsform.
An embodiment of the invention will be explained in more detail with reference to a drawing. Show:
FIG. 1
a profiled turbine blade in cross-section,
FIG. 2
a core element, and
FIG. 3
a number of plug elements in each different embodiment.

Gleiche Teile sind in beiden Figuren mit denselben Bezugszeichen versehen.Identical parts are provided in both figures with the same reference numerals.

Die Turbinenschaufel 1, die in Figur 1 im Querschnitt gezeigt ist, ist zum Einsatz in einer nicht näher dargestellten Gasturbine vorgesehen. Die Turbinenschaufel 1 umfaßt ein entlang einer Schaufelachse erstrecktes, auch als Schaufelprofil bezeichnetes Schaufelblatt 2. Das Schaufelblatt 2 ist, wie in Figur 1 erkennbar ist, profiliert oder an seiner Oberfläche gekrümmt, so daß eine besonders günstige Führung des die Gasturbine durchströmenden Arbeitsmediums gewährleistet ist.The turbine blade 1, which in FIG. 1 is shown in cross-section, is intended for use in a gas turbine, not shown. The turbine blade 1 comprises an airfoil blade 2 which extends along a blade axis and is also referred to as a blade profile. The airfoil 2 is, as in FIG FIG. 1 can be seen, profiled or curved on its surface, so that a particularly favorable guidance of the gas turbine flowing through the working medium is ensured.

Die Gasturbine ist aus thermodynamischen Gründen für eine Austrittstemperatur ihres Arbeitsmediums aus der Brennkammer von vergleichsweise hohen Temperaturen von beispielsweise 1200 °C bis 1300 °C ausgelegt. Um auch bei diesen Betriebsbedingungen eine hohe Zuverlässigkeit und lange Lebensdauer der jeweiligen Komponenten zu gewährleisten, ist neben anderen Komponenten auch die Turbinenschaufel 1 kühlbar ausgebildet. Dazu umfaßt das Schaufelblatt 2 eine Anzahl von integrierten Hohlräumen 4, 6, die jeweils als Strömungskanal für ein Kühlmittel dienen. Die Hohlräume 4 weisen dabei einen vergleichsweise großen Querschnitt auf und dienen als Hauptströmungsweg für das Kühlmittel. Gerade bei im Querschnitt vergleichsweise groß gehaltenen Strömungskanälen für das Kühlmittel ist jedoch zur mechanischen Stabilisierung eine vergleichsweise große Wandstärke der verbleibenden Strukturteile der Turbinenschaufel 1 erforderlich. Andererseits besteht das Bestreben, den Strömungsweg des Kühlmittels möglichst nah an der heißgasbeaufschlagten Oberseite der Turbinenschaufel 1 zu halten. Um dies auch bei hoher mechanischer Stabilität der Turbinenschaufel 1 zu gewährleisten, sind zusätzlich zu den den Hauptströmungsweg für das Kühlmittel bildenden ersten Hohlräumen 4 zweite Hohlräume 6 vorgesehen, die vergleichsweise dicht unter der Oberfläche der Turbinenfläche 1 verlaufen. Diese zweiten Hohlräume 6 bilden Nebenkanäle für das Kühlmittel und kommunizieren einlaß- und auslaßseitig mit den ersten Hohlräumen 4.The gas turbine is designed for thermodynamic reasons for an outlet temperature of their working medium from the combustion chamber of comparatively high temperatures of for example 1200 ° C to 1300 ° C. In order to ensure high reliability and long life of the respective components even under these operating conditions, the turbine blade 1 is designed to be coolable in addition to other components. For this purpose, the blade 2 includes a number of integrated cavities 4, 6, each serving as a flow channel for a coolant. The cavities 4 have a comparatively large cross-section and serve as the main flow path for the coolant. However, in the case of a comparatively large flow channel for the coolant, which is relatively large in cross-section, a comparatively large wall thickness of the remaining structural parts of the turbine blade 1 is required for mechanical stabilization. On the other hand, there is a desire to keep the flow path of the coolant as close as possible to the Heißgasbeaufschlagten top of the turbine blade 1. To ensure this even with high mechanical stability of the turbine blade 1, in addition to the 4 second cavities 6, which run comparatively close to the surface of the turbine surface 1, are provided in the main flow path for the coolant-forming first cavities 4. These second cavities 6 form secondary channels for the coolant and communicate with the first cavities 4 on the inlet and outlet side.

Bei der Herstellung der Turbinenschaufel 1 wird eine Gießform verwendet, die einen an die gewünschte Außenkontur der Turbinenschaufel 1 angepaßten Hohlraum aufweist. Zur Herstellung der Hohlräume 4, 6 werden in dieser Gießform in ihrer Außenkontur an die gewünschten Hohlräume 4 bzw. 6 angepaßte sogenannte Kernelemente positioniert. Anschließend wird die Gießform mit Schaufelmaterial ausgegossen, wobei durch die Kernelemente die vorgesehenen Hohlräume 4 bzw. 6 von Schaufelmaterial freigehalten werden. Nach dem Erstarren des Schaufelmaterials werden die Kernelemente wieder entfernt, so daß die gewünschten Hohlräume 4 bzw. 6 in der gegossenen Turbinenschaufel 1 verbleiben.In the manufacture of the turbine blade 1, a casting mold is used which has a cavity adapted to the desired outer contour of the turbine blade 1. To produce the cavities 4, 6 are in this mold in its outer contour to the desired cavities 4 and 6 adapted so-called core elements positioned. Subsequently, the casting mold is poured out with blade material, wherein the intended cavities 4 and 6 are kept free of blade material by the core elements. After solidification of the blade material, the core elements are removed again, so that the desired cavities 4 and 6 remain in the cast turbine blade 1.

Ein für die Herstellung eines der zweiten Hohlräume 6 vorgesehenes Kernelement 10 ist in Figur 2 gezeigt. Das Kernelement 10 umfaßt eine Grundplatte 12, die in ihrer Form an die für den jeweiligen Hohlraum 6 gewünschte Kontur angepaßt ist. Zur räumlichen Positionierung und Fixierung des Kernelements 10 während des Gießvorgangs sind an der Grundplatte 12 zudem eine Anzahl von Abstandhaltern 14 angeordnet.An intended for the preparation of one of the second cavities 6 core element 10 is in FIG. 2 shown. The core element 10 comprises a base plate 12 which is adapted in shape to the contour desired for the respective cavity 6. For spatial positioning and fixing of the core element 10 during the casting process, a number of spacers 14 are also arranged on the base plate 12.

Jeder Abstandhalter 14 ist dabei im wesentlichen zylindrisch ausgestaltet und in seiner Länge derart ausgebildet, daß er das in seinem Raumbereich vorgesehene Schaufelprofil vollständig durchdringt. Im Ausführungsbeispiel sind die Abstandhalter 14 somit in ihrer Länge derart ausgebildet, daß diese die Dicke der den jeweiligen Hohlraum 6 umgebenden Materialwände übersteigt. Mit ihren freien Enden sind die Abstandhalter 14 dabei jeweils in der Gießform oder in einem benachbarten Kernelement verankert, so daß sich eine auch während des Gießvorgangs im wesentlichen stabile Struktur ergibt.Each spacer 14 is designed substantially cylindrical and formed in its length such that it completely penetrates the provided in its space area blade profile. In the embodiment, the spacers 14 are thus formed in their length so that it exceeds the thickness of the respective cavity 6 surrounding material walls. With their free ends, the spacers 14 are each in the mold or in an adjacent Core element anchored, so that there is a substantially stable structure during the casting process.

Nach dem Gießvorgang und dem Erstarren des Schaufelmaterials weist der so gegossene Schaufelkörper an denjenigen Stellen, an denen sich die Abstandhalter 14 befanden, durchgehende Öffnungen auf. Diese sind somit leicht erkennbar und können somit einer weiteren Behandlung unterzogen werden. Die nach der Entfernung der Kernelemente und der Abstandhalter in der Turbinenschaufel 1 verbleibenden, durch die Abstandhalter 14 erzeugten Öffnungen werden dabei durch geeignete Stopfenelemente verschlossen, wie dies für einige verschiedene Typen von Stopfenelementen in Figur 3 gezeigt ist.After the casting process and the solidification of the blade material, the thus cast blade body at those locations where the spacers 14 were located, through openings. These are thus easily recognizable and can thus be subjected to further treatment. The openings remaining after the removal of the core elements and the spacers in the turbine blade 1, generated by the spacers 14 are thereby closed by suitable plug elements, as for some different types of plug elements in FIG. 3 is shown.

Figur 3 zeigt in der Art mehrerer alternativer Ausführungsbeispiele eine Anzahl verschiedenartiger Stopfenelemente, mit denen die durch die Abstandhalter 14 gelassenen Öffnungen verschlossen sein können. Dabei kann als Stopfenelement für die jeweilige Öffnung ein Einschlagpin 20 vorgesehen sein, der in seinem Mittenbereich in der Art eines Widerhakens ein konisch ausgebildetes Formstück 22 umfaßt. Alternativ kann ein einseitig gestauchter Einschlagpin 24 vorgesehen sein, der sich besonders für den Fall eignet, daß die zu verschließende Öffnung einseitig noch den eigentlichen Öffnungskanal begrenzende Überstände 26 aufweist. Falls eine vollständig durchgehende Öffnung vorliegt, kann jedoch auch ein durchgehender Stift 28 vorgesehen sein, der nach seinem Eindringen in die jeweilige Öffnung beidseitig gestaucht wurde. Gerade durch die Stauchung tritt hierbei infolge der sich einstellenden Verdickung im Mittenbereich des Stifts 28 eine besonders gute Dichtwirkung ein. FIG. 3 shows in the manner of several alternative embodiments, a number of different types of plug elements, with which the openings left by the spacers 14 may be closed. In this case, a Einschlagpin 20 may be provided as a plug element for the respective opening, which includes a conically shaped fitting 22 in its center region in the manner of a barb. Alternatively it can be provided a one-sided compressed impact pin 24, which is particularly suitable in the event that the opening to be closed on one side still the actual opening channel limiting projections 26 has. If there is a completely continuous opening, however, a continuous pin 28 may be provided, which has been compressed on both sides after its penetration into the respective opening. Just by the compression occurs here as a result of the self-adjusting thickening in the central region of the pin 28 a particularly good sealing effect.

Alternativ kann auch ein in einer durchgehenden Öffnung eingesetzter Stift 30 zum Einsatz kommen, wobei die jeweilige Öffnung in ihren Endbereichen Abschrägungen aufweist. Bei einer Stauchung des Stifts 30 wird dieser in seinen Endbereichen verformt, wobei sich sein Stiftmaterial in die entsprechenden Abschrägungen der jeweiligen Öffnungen einfügt. Weiterhin ist auch die Verwendung eines Stifts 32 möglich, der in seinem Endbereich durch Anbringen einer Lötkappe 34 und anschließendes Verlöten dicht abgeschlossen ist.Alternatively, it is also possible to use a pin 30 inserted in a continuous opening, the respective opening having bevels in its end regions. In a compression of the pin 30, this is deformed in its end regions, with its pin material in the corresponding Bevels of the respective openings inserts. Furthermore, the use of a pin 32 is possible, which is sealed in its end by attaching a soldering cap 34 and then soldering.

Claims (5)

  1. Method of producing a turbine blade (1) in hollow section, in which a first core element (10) is connected via a number of approximately cylindrical spacers (14) to a further core element and/or to a casting mold, the cavities (4, 6) left in the casting mold by the core elements (10) being filled by blade material, and in which the openings remaining in the turbine blade (1) after the removal of the core elements (10) and the spacers (14) and produced by the spacers (14) are closed by stopper elements.
  2. Method according to Claim 1, in which the stopper elements are upset after they have been inserted into the respective opening.
  3. Method according to Claim 1 or 2, in which the stopper elements are brazed after they have been inserted into the respective opening.
  4. Method according to one of Claims 1 to 3, in which the stopper elements used are blind rivets.
  5. Method according to one of Claims 1 to 3, in which the stopper elements used are drive-in pins (24).
EP01108480A 2001-04-04 2001-04-04 Method for producing an airfoil Expired - Lifetime EP1247602B1 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
DE50113629T DE50113629D1 (en) 2001-04-04 2001-04-04 Method for producing a turbine blade
ES01108480T ES2301504T3 (en) 2001-04-04 2001-04-04 PROCEDURE TO PRODUCE A TURBINE ALABE.
EP01108480A EP1247602B1 (en) 2001-04-04 2001-04-04 Method for producing an airfoil
JP2002098225A JP2002349285A (en) 2001-04-04 2002-04-01 Method of manufacturing turbine blade
US10/117,633 US6739381B2 (en) 2001-04-04 2002-04-04 Method of producing a turbine blade
CNB021054355A CN1250361C (en) 2001-04-04 2002-04-04 Method for making turbine vanes

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01108480A EP1247602B1 (en) 2001-04-04 2001-04-04 Method for producing an airfoil

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EP1247602B1 true EP1247602B1 (en) 2008-02-20

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EP (1) EP1247602B1 (en)
JP (1) JP2002349285A (en)
CN (1) CN1250361C (en)
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ES (1) ES2301504T3 (en)

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DE50113629D1 (en) 2008-04-03
US6739381B2 (en) 2004-05-25
CN1378890A (en) 2002-11-13
ES2301504T3 (en) 2008-07-01
CN1250361C (en) 2006-04-12
US20020157251A1 (en) 2002-10-31
EP1247602A1 (en) 2002-10-09
JP2002349285A (en) 2002-12-04

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