EP1193006B1 - Process for manufacturing a cooled precision casting - Google Patents
Process for manufacturing a cooled precision casting Download PDFInfo
- Publication number
- EP1193006B1 EP1193006B1 EP01115998A EP01115998A EP1193006B1 EP 1193006 B1 EP1193006 B1 EP 1193006B1 EP 01115998 A EP01115998 A EP 01115998A EP 01115998 A EP01115998 A EP 01115998A EP 1193006 B1 EP1193006 B1 EP 1193006B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- casting
- core
- wax
- cooling
- wax model
- 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
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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
- B22C7/00—Patterns; Manufacture thereof so far as not provided for in other classes
- B22C7/02—Lost patterns
-
- 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
-
- 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
- Y10T29/4998—Combined manufacture including applying or shaping of fluent material
- Y10T29/49988—Metal casting
- Y10T29/49989—Followed by cutting or removing material
Definitions
- the invention relates to a method for producing a cooled Investment casting of a thermal turbomachine according to the preamble of Claim 1.
- Castings of thermal turbomachinery are known by Casting process produced.
- Cast furnaces for such casting processes are for example, from EP-A1-749 790, US-3,763,926 or US-3,690,367 known.
- the molds are generally by a Wax model provided.
- a method of making a complex Part of a gas turbine by means of a mold is for example from the Document US 5,296,308 known.
- a core is inserted into the wax model.
- This Core contains the structure of the cavity, which is inside the casting forms a specific cooling structure.
- the wax seal is made by hand on a Level, which is located next to the core, applied.
- Last but not least the stage the sense to record a cooling plate.
- the cooling plate is on the Stage soldered or welded and used by means of cooling holes for impingement cooling the underlying platform.
- Cooling air should be flat surface of a step. But this is in the Contrary to the attached wax seal, which after casting a Material accumulation above the stage gives.
- To the goal of a level Closing the surface of the stage is an additional procedural step such as grinding or eroding necessary.
- the invention is based on the object, a process for the preparation a thermally loaded and cooled casting of a thermal Turbomachine by means of a known casting process to provide, wherein the casting of the casting with a wax model and a ceramic Core is produced, and the subsequent manufacturing steps simplified and be optimized.
- the object is achieved by a method according to the Oberbegriff of claim 1 solved by the fact that before making the Casting of the casting between the wax model and the core Wax seal is applied only on a paragraph, which itself located above the step to the side of the core.
- the invention relates to a method for producing a thermal loaded and cooled investment casting of a thermal turbomachine.
- This can be in detail, for example, a Leit- or Blade or other cooled rotor or stator segments of a Gas turbine or a compressor act.
- the castings are generally known in the art Produces cast iron stoves. With such a casting furnace can be complex trained and high thermal and mechanical loads exposable components are manufactured. Depending on the process conditions it is possible to manufacture the casting body directionally solidified. There is the Possibility to use it as single crystal ("single crystal", SX) or polycrystalline as Stem crystals having a preferential direction ("directionally solidified ", DS) It is of particular importance that the directional solidification takes place under conditions in which between a cooled portion of a molten starting material receiving Cast mold and the still molten starting material a strong Heat exchange takes place. It can then become a zone directionally frozen Form materials with a solidification front, which in case of permanent withdrawal of heat to form the directly solidified Giess stressess by the Casting mold wanders.
- the document EP-A1-749 790 for example, such a method and a device for producing a directionally solidified Giess stresses known.
- the device consists of a vacuum chamber, which a upper heating chamber and a lower cooling chamber contains. Both chambers are separated by a baffle.
- the vacuum chamber takes up a mold, which is filled with a melt.
- Gas turbines for example, a superalloy based on Used nickel.
- In the middle of the baffles there is an opening through which slows the mold down from the heating chamber during the process is moved into the cooling chamber, allowing the casting from bottom to top directionally frozen.
- the downward movement is done by a drive rod, on which the mold is stored.
- the bottom of the mold is executed water-cooled.
- Below the baffles are means for generating and guiding a gas flow present.
- FIG. 1 shows a wax model 10 of a casting 1, for example one to be cast turbine blade.
- the turbine blade has a platform 2, an airfoil 3 and a blade tip 2.
- This wax model 10 is then in a liquid, ceramic material, which also slip is dipped. This forms around the wax model 10 the later casting of the casting 1.
- the ceramic Dried material so that the mold, with which the casting 1 produced, arises.
- the casting mold is also fired, i.e. it contains its strength in this way.
- the casting 1 is with the so resulting mold by a known, further above described casting furnace produced in a known manner. Later, the ceramic mold and the core appropriately removed, so for Example by using an acid or a lye.
- the turbine blade of Figure 1 has a cavity into which during the Operation of the turbomachine cooling air is introduced. This cooling air can the leave the finished turbine blade again through cooling holes 5.
- a ceramic core 6 which represents the internal geometry of the cavity.
- the platform 2 in addition by an impingement cooling cooled. It is in the cast component on a level 7, which is located next to the ceramic core 6 and at the edge of the platform 2, a cooling plate 11, in which cooling holes 12 are located, soldered or welded. This cooling plate 11 is described in detail in FIG.
- This wax seal 8 has the goal of the unwanted ingress of slip to prevent the interior of the ceramic core 6.
- FIG. 2 shows a section according to the line II - II of FIG Stage 7, the wax seal 8 and through the ceramic core. 6
- the wax seal 8 is only on a paragraph 9th attached, which is above the stage 7 to the ceramic core 6 out located. From this procedure, there are several advantages.
- the Stage 7, at which the cooling plate 11 is soldered remains in spite of this additional processing operation unaffected, which in any case a smooth Level 7 surface guaranteed.
- the cooling air 13 penetrates through the Cooling holes 12 and can thus cool the platform 2 by impingement cooling.
- the smooth surface of level 7 is so important because even small Unevenness the cooling capacity of this impingement cooling due to leakage losses Reduce.
- Another advantage is that due to the existing Paragraph 9, the liquid solder, which is distributed throughout the level 7, is prevented from flowing into the cavity of the casting 1. As with the Operation of the casting 1 in the cavity is also an insert, it is important that no solder sticks to this insert and thus the proper functioning impaired.
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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 bezieht sich auf ein Verfahren zur Herstellung eines gekühlten
Feingussteils einer thermischen Turbomaschine gemäss dem Oberbegriff des
Anspruchs 1.The invention relates to a method for producing a cooled
Investment casting of a thermal turbomachine according to the preamble of
Gussteile thermischer Turbomaschinen werden durch bekannte Gussverfahren hergestellt. Gussöfen für solche Gussverfahren sind beispielsweise aus den Schriften EP-A1-749 790, US-3,763,926 oder US-3,690,367 bekannt. Die Gussformen werden im allgemeinen durch ein Wachsmodell bereitgestellt. Ein Verfahren zur Herstellung eines komplexen Teils einer Gasturbine mittels einer Giessform ist beispielsweise aus der Schrift US-5,296,308 bekannt.Castings of thermal turbomachinery are known by Casting process produced. Cast furnaces for such casting processes are for example, from EP-A1-749 790, US-3,763,926 or US-3,690,367 known. The molds are generally by a Wax model provided. A method of making a complex Part of a gas turbine by means of a mold is for example from the Document US 5,296,308 known.
Je nach Ausführungsform wird ein Kern in das Wachsmodell eingefügt. Dieser Kern enthält die Struktur des Hohlraums, welcher im Inneren des Gussteils eine bestimmte Kühlstruktur bildet. Bei diesen Gussteilen muss zwischen dem Wachsmodell und dem Kern eine Wachsdichtung angebracht werden, um ein Eindringen des Schlickers, welcher getrocknet die Gussform bildet, in den Zwischenraum zu verhindern. Die Wachsdichtung wird von Hand auf eine Stufe, welche sich neben dem Kern befindet, aufgetragen. Letzten Endes hat die Stufe den Sinn, eine Kühlplatte aufzunehmen. Die Kühlplatte wird auf die Stufe gelötet oder geschweisst und dient mittels Kühllöchern zur Prallkühlung der sich darunter befindenden Plattform. Zur Vermeidung von Leckagen an der Kühlluft sollte die Oberfläche der Stufe eben sein. Dies steht aber im Gegensatz zur angebrachten Wachsdichtung, welche nach dem Giessen eine Materialansammlung oberhalb der Stufe ergibt. Um dem Ziel einer ebenen Oberfläche der Stufe näher zukommen, ist eine zusätzlicher Verfahrensschritt wie zum Beispiel Schleifen oder Erodieren notwendig.Depending on the embodiment, a core is inserted into the wax model. This Core contains the structure of the cavity, which is inside the casting forms a specific cooling structure. In these castings must be between the Wax model and the core to be attached to a wax seal Penetration of the slip which forms the mold in the dried To prevent gap. The wax seal is made by hand on a Level, which is located next to the core, applied. Last but not least the stage the sense to record a cooling plate. The cooling plate is on the Stage soldered or welded and used by means of cooling holes for impingement cooling the underlying platform. To avoid leaks Cooling air should be flat surface of a step. But this is in the Contrary to the attached wax seal, which after casting a Material accumulation above the stage gives. To the goal of a level Closing the surface of the stage is an additional procedural step such as grinding or eroding necessary.
Der Erfindung liegt die Aufgabe zu Grunde, ein Verfahren zur Herstellung eines thermisch belasteten und gekühlten Gussteils einer thermischen Turbomaschine mittels eines bekannten Gussverfahrens zu schaffen, wobei die Gussform des Gussteils mit einem Wachsmodell und einem keramischen Kern hergestellt wird, und die nachfolgenden Fertigungsschritte vereinfacht und optimiert werden.The invention is based on the object, a process for the preparation a thermally loaded and cooled casting of a thermal Turbomachine by means of a known casting process to provide, wherein the casting of the casting with a wax model and a ceramic Core is produced, and the subsequent manufacturing steps simplified and be optimized.
Erfindungsgemäss wird die Aufgabe durch ein Verfahren gemäss dem
Oberbegriff des Anspruchs 1 dadurch gelöst, dass vor Herstellen der
Gussform des Gussteils zwischen dem Wachsmodell und dem Kern die
Wachsdichtung lediglich auf einem Absatz aufgetragen wird, welcher sich
oberhalb der Stufe zur Seite des Kerns hin befindet.According to the invention, the object is achieved by a method according to the
Oberbegriff of
Vorteilhaft kann somit schon während des Giessverfahrens verhindert werden, dass auf der Stufe Unebenheiten entstehen, welche eine Leckage für die Kühlluft an der Kühlplatte bedeuten. Das Material, welches durch die Wachsdichtung und den Absatz während des Gussverfahrens entsteht, kann durch einen vereinheitlichten Verfahrensschritt abgeschliffen oder auf andere, geeignete Art und Weise abgetragen werden, ohne dass sich Unebenheiten auf der Stufe bilden. Auf dieser Stufe kann eine Kühlplatte ohne weitere Verfahrensschritte angelötet werden.Advantageously, thus already prevented during the casting process be that arise at the level unevenness, which is a leak for mean the cooling air on the cooling plate. The material, which by the Wax seal and the heel created during the casting process can ground by a unified process step or to others, Suitable manner to be removed without causing bumps form on the stage. At this stage, a cooling plate without further Process steps are soldered.
Die Erfindung wird anhand der beigefügten Zeichnungen dargestellt, wobei
- Fig. 1
- ein Modell einer Turbinenschaufel zeigt,
- Fig. 2
- einen Schnitt durch eine erfindungsgemässe Turbinenschaufel
gemäss der Linie II - II in der
Figur 1 zeigt und - Fig. 3
- einen Schnitt durch eine erfindungsgemässe Turbinenschaufel
gemäss der Linie II - II in der
Figur 1 nach erfolgreichem Gussverfahren zeigt.
- Fig. 1
- shows a model of a turbine blade,
- Fig. 2
- a section through a turbine blade according to the invention according to the line II - II in Figure 1 shows and
- Fig. 3
- a section through a turbine blade according to the invention according to the line II - II in Figure 1 by successful casting process shows.
Es werden nur die für die Erfindung wesentlichen Elemente dargestellt. Gleiche Elemente sind in unterschiedlichen Zeichnungen mit gleichen Bezugszeichen versehen.Only the elements essential to the invention are shown. Same elements are the same in different drawings Provided with reference numerals.
Die Erfindung bezieht sich auf ein Verfahren zur Herstellung eines thermisch belasteten und gekühlten Feingussteils einer thermischen Turbomaschine. Dabei kann es sich im einzelnen beispielsweise um eine Leit- oder Laufschaufel oder um andere gekühlte Rotor- oder Statorsegmente einer Gasturbine oder eines Kompressors handeln. Diese Gussteile und das erfindungsgemässe Verfahren zu ihrer Herstellung werden im folgenden anhand der beiliegenden Figuren näher erläutert.The invention relates to a method for producing a thermal loaded and cooled investment casting of a thermal turbomachine. This can be in detail, for example, a Leit- or Blade or other cooled rotor or stator segments of a Gas turbine or a compressor act. These castings and the Processes according to the invention for their preparation are described below explained in more detail with reference to the accompanying figures.
Die Gussteile werden mit allgemein aus dem Stand der Technik bekannten Gussöfen herstellt. Mit einem solchen Gussofen können komplex ausgebildete und hohen thermischen und mechanischen Belastungen aussetzbare Bauteile hergestellt werden. Je nach Verfahrenbedingungen ist es möglich, den Giesskörper gerichtet erstarrt herzustellen. Dabei besteht die Möglichkeit, ihn als Einkristall ("single crystal", SX) oder polykristallin als Stengelkristalle, welche eine Vorzugsrichtung aufweisen, ("directionally solidified", DS) auszubilden. Von besonderer Bedeutung ist es, dass die gerichtete Erstarrung unter Bedingungen stattfindet, bei denen zwischen einem gekühlten Teil einer geschmolzenes Ausgangsmaterial aufnehmenden Gussform und dem noch geschmolzenen Ausgangsmaterial ein starker Wärmeaustausch stattfindet. Es kann sich dann eine Zone gerichtet erstarrten Materials mit einer Erstarrungsfront ausbilden, welche bei dauerndem Entzug von Wärme unter Bildung des direkt erstarrten Giesskörpers durch die Gussform wandert.The castings are generally known in the art Produces cast iron stoves. With such a casting furnace can be complex trained and high thermal and mechanical loads exposable components are manufactured. Depending on the process conditions it is possible to manufacture the casting body directionally solidified. There is the Possibility to use it as single crystal ("single crystal", SX) or polycrystalline as Stem crystals having a preferential direction ("directionally solidified ", DS) It is of particular importance that the directional solidification takes place under conditions in which between a cooled portion of a molten starting material receiving Cast mold and the still molten starting material a strong Heat exchange takes place. It can then become a zone directionally frozen Form materials with a solidification front, which in case of permanent withdrawal of heat to form the directly solidified Giesskörpers by the Casting mold wanders.
Aus der Schrift EP-A1-749 790 ist beispielsweise ein solches Verfahren und eine Vorrichtung zur Herstellung eines gerichtet erstarrten Giesskörpers bekannt. Die Vorrichtung besteht aus einer Vakuumkammer, welche eine obere Heizkammer und eine untere Kühlkammer enthält. Beide Kammern sind durch ein Baffle getrennt. Die Vakuumkammer nimmt eine Gussform auf, welche mit einer Schmelze gefüllt wird. Für die Herstellung von thermisch und mechanisch belastbaren Teilen, wie im Falle von Leit- und Laufschaufeln von Gasturbinen, wird beispielsweise eine Superlegierung auf der Basis von Nickel verwendet. In der Mitte des Baffles ist eine Öffnung vorhanden, durch welche die Gussform während des Verfahrens langsam von der Heizkammer in die Kühlkammer bewegt wird, so dass das Gussstück von unten nach oben gerichtet erstarrt. Die Abwärtsbewegung geschieht durch eine Antriebsstange, auf welcher die Gussform gelagert ist. Der Boden der Gussform ist wassergekühlt ausgeführt. Unterhalb des Baffles sind Mittel zum Erzeugen und Führen einer Gasströmung vorhanden. Diese Mittel sorgen durch die Gasströmung neben der unteren Kühlkammer für eine zusätzliche Kühlung und dadurch für einen grösseren Temperaturgradienten an der Erstarrungsfront.The document EP-A1-749 790, for example, such a method and a device for producing a directionally solidified Giesskörpers known. The device consists of a vacuum chamber, which a upper heating chamber and a lower cooling chamber contains. Both chambers are separated by a baffle. The vacuum chamber takes up a mold, which is filled with a melt. For the production of thermal and mechanically loadable parts, as in the case of guide vanes and rotor blades Gas turbines, for example, a superalloy based on Used nickel. In the middle of the baffles there is an opening through which slows the mold down from the heating chamber during the process is moved into the cooling chamber, allowing the casting from bottom to top directionally frozen. The downward movement is done by a drive rod, on which the mold is stored. The bottom of the mold is executed water-cooled. Below the baffles are means for generating and guiding a gas flow present. These funds provide by the Gas flow adjacent to the lower cooling chamber for additional cooling and thereby for a larger temperature gradient at the Solidification front.
Ein ähnliches Verfahren, welches neben Heiz- und Kühlkammer mit einer zusätzlichen Gaskühlung arbeitet, ist beispielsweise auch aus der Patentschrift US 3,690,367 bekannt.A similar process, which in addition to heating and cooling chamber with a additional gas cooling works, for example, is also from the Patent US 3,690,367 known.
Ein weiteres Verfahren zur Herstellung eines gerichtet erstarrten Giesskörpers ist aus der Druckschrift US 3,763,926 bekannt. Bei diesem Verfahren wird eine mit einer aufgeschmolzenen Legierung gefüllte Gussform kontinuierlich in ein auf ca. 260° C aufgeheiztes Bad getaucht. Hierdurch wird eine besonders rasche Abfuhr von Wärme aus der Gussform erreicht. Dieses und andere, ähnliche Verfahren sind unter dem Begriff LMC (liquid metal cooling) bekannt.Another method for producing a directionally solidified Giesskörpers is known from the document US 3,763,926. In this method is a mold filled with a molten alloy continuously immersed in a heated to about 260 ° C bath. This will be a particularly rapid removal of heat from the mold achieved. This and other similar processes are termed LMC (liquid metal cooling) known.
Es ist für die Erfindung vorteilhaft, diese Art von Gussöfen zur Herstellung von einkristallinen oder gerichtet erstarrten Gussteilen zu benutzen, sie ist jedoch nicht darauf beschränkt. Im Prinzip kann die Erstarrung auch ungerichtet erfolgen.It is advantageous for the invention to use this type of casting furnaces for the production of it is, however, to use single-crystal or directionally solidified castings not limited to this. In principle, the solidification can also undirected respectively.
Die Figur 1 zeigt ein Wachsmodell 10 eines Gussteils 1 beispielsweise einer
zu giessenden Turbinenschaufel. Die Turbinenschaufel weist eine Plattform 2,
ein Schaufelblatt 3 und eine Schaufelspitze 2 auf. Dieses Wachsmodell 10
wird dann in ein flüssiges, keramisches Material, welches auch Schlicker
genannt wird, eingetaucht. Dabei bildet sich um das Wachsmodell 10 die
spätere Gussform des Gussteils 1. Anschliessend wird das keramische
Material getrocknet, so dass die Gussform, mit welcher das Gussteil 1
hergestellt wird, entsteht. Nach dem Trocknungsvorgang des Schlickers wird
das Wachs durch eine geeignete Wärmebehandlung entfernt, d.h.
ausgebrannt. Bei diesem Verfahrensschritt wird auch die Gussform gebrannt,
d.h. sie enthält auf diese Weise ihre Festigkeit. Das Gussteil 1 wird mit der so
entstandenen Gussform durch einen bekannten, weiter oben näher
beschriebenen Gussofen auf bekannte Weise hergestellt. Später wird die
keramische Gussform und der Kern auf geeignete Weise entfernt, so zum
Beispiel durch Anwendung einer Säure oder einer Lauge.FIG. 1 shows a
Die Turbinenschaufel der Figur 1 besitzt einen Hohlraum, in den während des
Betriebs der Turbomaschine Kühlluft eingeleitet wird. Diese Kühlluft kann die
fertige Turbinenschaufel wieder durch Kühllöcher 5 verlassen. Wie aus der
Figur 1 sichtbar, befindet sich im späteren Hohlraum des Wachsmodells 10
während des Herstellungsvorgangs der Giessform ein keramischer Kern 6,
welcher die innere Geometrie des Hohlraums wiedergibt. Bei der dargestellten
Turbinenschaufel wird die Plattform 2 zusätzlich durch eine Prallkühlung
gekühlt. Dabei wird bei der gegossenen Komponente auf eine Stufe 7, welche
sich neben dem keramischen Kern 6 und am Rand der Plattform 2 befindet,
eine Kühlplatte 11, in welcher sich Kühllöcher 12 befinden, angelötet oder
angeschweisst. Diese Kühlplatte 11 wird in der Figur 3 näher beschrieben.The turbine blade of Figure 1 has a cavity into which during the
Operation of the turbomachine cooling air is introduced. This cooling air can the
leave the finished turbine blade again through cooling holes 5. Like from the
FIG. 1 is visible, located in the later cavity of the
Zwischen dem keramischen Kern 6 und dem Absatz 9 wird vor der
Herstellung der Giessform von Hand eine Wachsdichtung 8 angebracht.
Diese Wachsdichtung 8 hat das Ziel das ungewollte Eindringen von Schlicker
in den Innenraum des keramischen Kerns 6 zu verhindern.Between the
Die Figur 2 zeigt einen Schnitt gemäss der Linie II - II der Figur 1 durch die
Stufe 7, die Wachsdichtung 8 und durch den keramischen Kern 6.
Erfindungsgemäss wird die Wachsdichtung 8 lediglich auf einen Absatz 9
angebracht, welcher sich oberhalb der Stufe 7 zum keramischen Kern 6 hin
befindet. Aus dieser Vorgehensweise ergeben sich verschiedene Vorteile.
Während des Giessvorgangs entsteht durch die Stufe 7 und die
Wachsdichtung 8 zusätzliches, ebenfalls gegossenes Material an der
Turbinenschaufel. Dieses hat, wie in der Figur 3 ersichtlich, eine bestimmte
Höhe s, und kann unabhängig von der Stufe 7 bzw. unabhängig von der
Oberfläche der Stufe 7 bearbeitet, d.h. abgeschliffen, werden. Dieser
vereinheitlichte Verfahrensschritt kann auch durch Erosion geschehen. Die
Stufe 7, an der die Kühlplatte 11 angelötet wird, bleibt trotz dieses
zusätzlichen Bearbeitungsvorgangs unberührt, was in jedem Fall eine glatte
Oberfläche der Stufe 7 gewährleistet. Die Kühlluft 13 dringt durch die
Kühllöcher 12 und kann die Plattform 2 somit durch Prallkühlung kühlen. Die
glatte Oberfläche der Stufe 7 ist deshalb so wichtig, da schon geringe
Unebenheiten die Kühlleistung dieser Prallkühlung durch Leckageverluste
vermindern. Ein weitere Vorteil besteht darin, dass durch den vorhandenen
Absatz 9 das flüssige Lot, welches sich auf der ganzen Stufe 7 verteilt,
gehindert wird, in den Hohlraum des Gussteils 1 zu fliessen. Da sich bei dem
Betrieb des Gussteils 1 im Hohlraum ebenfalls ein Einsatz befindet, ist es
wichtig, dass keinerlei Lot an diesem Einsatz klebt und somit die
ordnungsgemässe Funktionsweise beeinträchtigt. FIG. 2 shows a section according to the line II - II of
- 11
- Gussteil, beispielsweise TurbinenschaufelCasting, for example turbine blade
- 22
- Plattformplatform
- 33
- Schaufelblattairfoil
- 44
- Spitze der TurbinenschaufelTop of the turbine blade
- 55
- Kühllöchercooling holes
- 66
- Keramischer KernCeramic core
- 77
- Stufestep
- 88th
- Wachsdichtungwax seal
- 99
- Absatzparagraph
- 1010
- Wachsmodell der TurbinenschaufelWax model of the turbine blade
- 1111
- Platteplate
- 1212
-
Kühlloch in Platte 11Cooling hole in
plate 11 - 1313
- Kühlluftcooling air
- ss
-
Höhe des Absatzes 9Height of
paragraph 9
Claims (5)
- Process for producing a cooled casting (1) of a thermal turbomachine using a known casting process, in which the cooled casting (1) is produced by means of a casting mould, this casting mould being produced by means of a wax model (10) and by means of a core (6) located within the wax model (10), a step (7) for securing a cooling plate (11) to the finished casting (1) being located directly adjacent to the core (6), and a wax seal (8) being arranged between the core (6) and the wax model (10) by hand prior to production of the casting mould, characterized in that prior to production of the casting mould for the casting (1), the wax seal (8), between the wax model (10) and the core (6), is merely placed onto a shoulder (9) which is located above the step (7) towards the side of the core (6).
- Process according to Claim 1, characterized in that, after the casting process, the material on the casting (1) which is located at the position of the shoulder (9) and the wax seal (8) is partially ground away or eroded, with the step (7) being left unaffected by this process step.
- Process according to Claim 2, characterized in that the cooling plate (11), in which there are cooling holes (12), is soldered or welded to the surface of the step (7).
- Process according to one of the preceding claims, characterized in that a casting process for producing single-crystal, directionally or non-directionally solidified castings is used.
- Process according to one of the preceding claims, characterized in that it is a process for producing a guide vane or a rotor blade of a gas turbine or of a compressor with impingement cooling of the platform (2).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE10038453 | 2000-08-07 | ||
| DE10038453A DE10038453A1 (en) | 2000-08-07 | 2000-08-07 | Production of a cooled cast part of a thermal turbo machine comprises applying a wax seal to an offset between a wax model a core before producing the casting mold, the offset being located above the step to the side of the core. |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| EP1193006A2 EP1193006A2 (en) | 2002-04-03 |
| EP1193006A3 EP1193006A3 (en) | 2003-05-21 |
| EP1193006B1 true EP1193006B1 (en) | 2005-08-31 |
Family
ID=7651569
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP01115998A Expired - Lifetime EP1193006B1 (en) | 2000-08-07 | 2001-06-30 | Process for manufacturing a cooled precision casting |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US6435256B1 (en) |
| EP (1) | EP1193006B1 (en) |
| DE (2) | DE10038453A1 (en) |
Families Citing this family (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7752384B2 (en) * | 2002-11-08 | 2010-07-06 | Crossroads Systems, Inc. | System and method for controlling access to media libraries |
| DE10255346A1 (en) * | 2002-11-28 | 2004-06-09 | Alstom Technology Ltd | Method of making a turbine blade |
| GB0413027D0 (en) * | 2004-06-11 | 2004-07-14 | Rolls Royce Plc | A wax recovery method |
| US20080257517A1 (en) * | 2005-12-16 | 2008-10-23 | General Electric Company | Mold assembly for use in a liquid metal cooled directional solidification furnace |
| US9403208B2 (en) | 2010-12-30 | 2016-08-02 | United Technologies Corporation | Method and casting core for forming a landing for welding a baffle inserted in an airfoil |
| FR3035604B1 (en) * | 2015-04-30 | 2023-01-13 | Snecma | PATTERN MANUFACTURING PROCESS FOR LOST PATTERN FOUNDRY |
| US11154956B2 (en) | 2017-02-22 | 2021-10-26 | General Electric Company | Method of repairing turbine component using ultra-thin plate |
| US20180238173A1 (en) * | 2017-02-22 | 2018-08-23 | General Electric Company | Method of manufacturing turbine airfoil and tip component thereof |
| US10610933B2 (en) * | 2017-02-22 | 2020-04-07 | General Electric Company | Method of manufacturing turbine airfoil with open tip casting and tip component thereof |
| US10702958B2 (en) | 2017-02-22 | 2020-07-07 | General Electric Company | Method of manufacturing turbine airfoil and tip component thereof using ceramic core with witness feature |
| US10717130B2 (en) | 2017-02-22 | 2020-07-21 | General Electric Company | Method of manufacturing turbine airfoil and tip component thereof |
| US10625342B2 (en) | 2017-02-22 | 2020-04-21 | General Electric Company | Method of repairing turbine component |
| US20190309629A1 (en) * | 2018-04-05 | 2019-10-10 | United Technologies Corporation | Turbine blades and vanes for gas turbine engine |
| US10830354B2 (en) | 2018-05-18 | 2020-11-10 | General Electric Company | Protection system with gasket for ceramic core processing operation and related method |
Family Cites Families (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3177537A (en) * | 1962-12-27 | 1965-04-13 | Prec Metalsmiths Inc | Methods and apparatus for forming investment molds and mold produced thereby |
| US3494709A (en) * | 1965-05-27 | 1970-02-10 | United Aircraft Corp | Single crystal metallic part |
| US3690367A (en) * | 1968-07-05 | 1972-09-12 | Anadite Inc | Apparatus for the restructuring of metals |
| US3648760A (en) * | 1970-04-27 | 1972-03-14 | Abraham J Cooper | Precision investment casting apparatus |
| US3763926A (en) * | 1971-09-15 | 1973-10-09 | United Aircraft Corp | Apparatus for casting of directionally solidified articles |
| GB2111359A (en) * | 1981-10-23 | 1983-06-29 | Howmet Turbine Components | Microwave heating |
| GB2205261B (en) * | 1987-06-03 | 1990-11-14 | Rolls Royce Plc | Method of manufacture and article manufactured thereby |
| US5489194A (en) * | 1990-09-14 | 1996-02-06 | Hitachi, Ltd. | Gas turbine, gas turbine blade used therefor and manufacturing method for gas turbine blade |
| US5296308A (en) * | 1992-08-10 | 1994-03-22 | Howmet Corporation | Investment casting using core with integral wall thickness control means |
| FR2714858B1 (en) * | 1994-01-12 | 1996-02-09 | Snecma | Method for manufacturing a shell mold made of ceramic material for a lost model foundry. |
| DE19539770A1 (en) * | 1995-06-20 | 1997-01-02 | Abb Research Ltd | Process for producing a directionally solidified casting and device for carrying out this process |
| DE19726111C1 (en) * | 1997-06-20 | 1998-11-12 | Mtu Muenchen Gmbh | Process for the production of a turbomachine blade by casting |
| EP0894558A1 (en) * | 1997-07-29 | 1999-02-03 | Siemens Aktiengesellschaft | Turbine blade and method of fabrication of a turbine blade |
-
2000
- 2000-08-07 DE DE10038453A patent/DE10038453A1/en not_active Withdrawn
-
2001
- 2001-06-30 EP EP01115998A patent/EP1193006B1/en not_active Expired - Lifetime
- 2001-06-30 DE DE50107262T patent/DE50107262D1/en not_active Expired - Lifetime
- 2001-08-06 US US09/921,587 patent/US6435256B1/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| US20020029863A1 (en) | 2002-03-14 |
| EP1193006A2 (en) | 2002-04-03 |
| EP1193006A3 (en) | 2003-05-21 |
| DE50107262D1 (en) | 2005-10-06 |
| DE10038453A1 (en) | 2002-02-21 |
| US6435256B1 (en) | 2002-08-20 |
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