EP2265800B1 - Cooling duct arrangement within a hollow-cast casting - Google Patents

Cooling duct arrangement within a hollow-cast casting Download PDF

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Publication number
EP2265800B1
EP2265800B1 EP09727227.2A EP09727227A EP2265800B1 EP 2265800 B1 EP2265800 B1 EP 2265800B1 EP 09727227 A EP09727227 A EP 09727227A EP 2265800 B1 EP2265800 B1 EP 2265800B1
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EP
European Patent Office
Prior art keywords
ribs
line
contour
cooling
along
Prior art date
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EP09727227.2A
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German (de)
French (fr)
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EP2265800A1 (en
Inventor
Jose Anguisola Mcfeat
Erich Kreiselmaier
Christoph Nagler
Sergei Riazantsev
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Ansaldo Energia IP UK Ltd
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Ansaldo Energia IP UK Ltd
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the invention relates to a cooling channel arrangement within a hollow casted casting, with a flow area for a coolant which is delimited by at least two spaced-apart casting walls and which is subdivided into two cooling channels in the flow direction of at least one ribbed train connected to both casting walls.
  • Hollow-cast parts with intimately provided cooling channel arrangements relate to the purposes of the invention primarily in gas and steam turbine to be integrated components that are operationally exposed to high process temperatures and to avoid thermally induced material degradation of effective cooling.
  • Such castings in particular represent guide vanes and rotor blades within turbine stages, which are directly exposed to the hot gases of a gas turbine process.
  • the cooling of such blading by means of cooling air, which is branched off on the compressor side and is fed via openings within the respective Schaufeifsente in the cavities having over blades for cooling purposes.
  • FIG. 2 a and b shows a known guide vane, with a vane platform 1 and a Leitschaufeldeckband 2, between which extends the vane blade 3 with a vane leading edge 4 and a Leitschaufelhinterkante 5.
  • cooling air K passes through both openings Within the vane cover 2 as well as within the vane platform 1.
  • For effective cooling of the vane blade 3 are located in the interior of the vane flow contours, which ensure the most intimate possible thermal contact between the supplied cooling air and the inside to be cooled of the vane wall.
  • Rippenver 6 are located in the flow direction Rippenver 6, each delimiting individual cooling channels 7 from each other.
  • Such rib trains are also off, for example WO0100964 known.
  • the rib trains are designed as Querlenkarm, which are arranged in packets side by side and are separated by a wall. The wall prevents the flow of coolant within a packet from entering the flow paths of an adjacent packet.
  • lost cores are required for the casting process, in which the negative contours of all structures to be provided within the casting, in particular the flow contours affecting the cooling air flow, are to be incorporated.
  • FIG. 2b shown ribbed trains 6 and the pin-like pins 8 located therebetween form, for better illustration in FIG. 3a are shown again in a plan view, it is necessary to provide a casting core 9, the in FIG. 3b is also shown in a plan view, which must provide for the production of the individual rib trains via groove-like recesses 10 and for generating the pin-like pins 8 corresponding through holes 1 1.
  • Previously consistently trained ribbed trains 6 could completely separate the cooling air flows K contained within the cooling channels 7 from each other, as shown in the schematic plan view in FIG. 4a is shown, then occur by providing appropriate interruptions 13 along the Rippentors 6, due to the stabilizing connecting webs 12 within the casting core, by the interruptions 13 branching cooling air flows K ', which are able to irritate the cooling air flow in the adjacent cooling channels.
  • this reduces the cooling efficiency of the cooling air passing through the cooling channels 7, so that measures must be sought with which the passing through the interruptions 13 cooling air flow portions can be avoided.
  • the invention is based on the object, a cooling arrangement within a hollow cast casting, with one of at least two spaced apart casting walls delimiting flow area for a coolant, which is divided in the flow direction of at least one connected to two casting walls Rippenyak in two cooling channels, such on the one hand the measures taken to stabilize the casting core required for the production of the casting should remain largely unaffected, but the cooling effect of passing through the cooling channel arrangement coolant should be significantly improved.
  • a cooling arrangement within a hollow cast part is designed so that at least one interruption is provided along the at least one rib train, at which two rib ends are spaced apart, one end of the rib being contoured in the manner of a " Dog bone ".
  • a flow contour it is possible, as the further embodiments will show, to largely or completely prevent coolant flow through the interruption along a rib train.
  • the solution according to the measure only requires an additional contour along the Rippenzuges in the region of an interruption, by the stability of a casting core is not affected by any means. Even with the measure according to the solution, it is possible to provide connection areas between the cooling passages separated by the rib trains in order in this way to realize a self-contained and mechanically stable casting core.
  • FIG. 1 a shows the region of an interruption 13 along a rib train 6, wherein two rib ends 61, 62 are spaced apart from each other along the rib train 6.
  • a coolant flow K rests along the rib train 6 in the flow direction indicated by the arrows.
  • the rib end 61 which is provided upstream of the interruption 13, in this case according to the solution has a contour 14 in the manner of a dog bone, whereby the coolant flow K not as in the illustrated case in example FIG. 4b in the context of cross-currents K 'passes through the interruptions 13, but in each case on both sides of the interruption 13 along the respective cooling channel 7 flows past.
  • the contour 14 formed in the manner of a dog bone has an extension D oriented transversely to the rib longitudinal extension which corresponds at least to 1.5 times the respective rib width d.
  • the dog-bone-shaped rib end contour 14 is optimized under flow dynamic aspects and has a round and thus a flow resistance reducing surface contour. The axial distance between the two along the break 13 facing rib ends 61, 62 should not exceed three times the length of the lateral extension D of the dog-bone-shaped contour 14.
  • FIG. 1b A graphical simulation result is in FIG. 1b shown.
  • the dark line areas indicate the presence of coolant and it is assumed that the in FIG. 1b shown flow range from left to right with coolant K is flowed through.
  • FIG. 5 In a flow area that is like in FIG. 5 has multiple parallel ribs 6 for mutual separation of cooling channels 7 has been found to be advantageous that particularly good flow results are achieved when the Rippenendkonturen be provided in the manner of a dog bone in an arrangement and distribution, the FIG. 5 is apparent.
  • three ribs 6 running side by side are provided, along which interruptions 13 are provided for reasons of a more stable formation of the casting core.
  • the cooling channels 7 located between the ribs 6 are passed through by cooling air K with the flow direction indicated by the arrow representation.
  • An additional illustration of the longitudinally located along the cooling channels 7, pin-like pins is omitted for reasons of clarity, however, these are provided accordingly in reality.
  • FIG. 5 An additional illustration of the longitudinally located along the cooling channels 7, pin-like pins is omitted for reasons of clarity, however, these are provided accordingly in reality.
  • the dog-bone-like contours 14 are each provided at the upstream end of the rib for every single interruption 13.
  • the dog bone contour 14 is provided at the downstream end for each discrete interruption 13 along the ribcuff.
  • the dogbone contours 14 are again uniformly located at the upstream rib end at the location of each break 13. Further, in this ribcrack assembly, it is necessary to ensure that the breaks are along a ribcuff with the breaks along an adjacent ribcuff in the transverse direction do not overlap each other, like those out of ribs FIG. 5 can be seen.

Description

Technisches GebietTechnical area

Die Erfindung bezieht sich auf eine Kühlkanalanordnung innerhalb eines hohlgegossenen Gussteils, mit einem von wenigstens zwei voneinander beabstandeten Gussteilwänden begrenzten Strömungsbereich für ein Kühlmittel, der in Strömungsrichtung von wenigstens einem mit beiden Gussteilwänden verbundenen Rippenzug in zwei Kühlkanäle unterteilt ist.The invention relates to a cooling channel arrangement within a hollow casted casting, with a flow area for a coolant which is delimited by at least two spaced-apart casting walls and which is subdivided into two cooling channels in the flow direction of at least one ribbed train connected to both casting walls.

Stand der TechnikState of the art

Hohlgegossene Gussteile mit innwandig vorgesehenen Kühlkanalanordnungen betreffen im Sinne der Erfindung vornehmlich in Gas- und Dampfturbinenanlagen zu integrierende Komponenten, die betriebsbedingt hohen Prozesstemperaturen ausgesetzt sind und zur Vermeidung thermisch induzierter Materialdegradationen einer effektiven Kühlung bedürfen. Derartige Gussteile stellen insbesondere Leit- und Laufschaufeln innerhalb von Turbinenstufen dar, die den Heißgasen eines Gasturbinenprozesses unmittelbar ausgesetzt sind. In der Regel erfolgt die Kühlung derartiger Beschaufelungen mittels Kühlluft, die verdichterseitig abgezweigt und über Öffnungen innerhalb der jeweiligen Schaufeifüße in die über Hohlräume verfügenden Schaufelblätter zu Kühlzwecken eingespeist wird.Hollow-cast parts with intimately provided cooling channel arrangements relate to the purposes of the invention primarily in gas and steam turbine to be integrated components that are operationally exposed to high process temperatures and to avoid thermally induced material degradation of effective cooling. Such castings in particular represent guide vanes and rotor blades within turbine stages, which are directly exposed to the hot gases of a gas turbine process. In general, the cooling of such blading by means of cooling air, which is branched off on the compressor side and is fed via openings within the respective Schaufeifüße in the cavities having over blades for cooling purposes.

Zur Illustration der bisher eingesetzten Kühltechnik von Leitschaufeln zum Einsatz in Gasturbinenanlagen sei auf die Figur 2 a und b verwiesen, die eine an sich bekannte Leitschaufel zeigt, mit einer Leitschaufelplattform 1 sowie einem Leitschaufeldeckband 2, zwischen denen sich das Leitschaufelblatt 3 mit einer Leitschaufelvorderkante 4 und einer Leitschaufelhinterkante 5 erstreckt. Zur Kühlung der innen hohl ausgebildeten Leitschaufel 3, die in Figur 2a zur Illustration der inneren hohlen Kühlkanalanordnung partiell im Anriss dargestellt ist, gelangt Kühlluft K sowohl durch Öffnungen innerhalb des Leitschaufeldeckbandes 2 als auch innerhalb der Leitschaufelplattform 1. Zur effektiven Kühlung des Leitschaufelblattes 3 befinden sich im Inneren der Leitschaufel Strömungskonturen, die für einen möglichst innigen thermischen Kontakt zwischen der zugeführten Kühlluft und der zu kühlenden Innenseite der Leitschaufelwand sorgen. Insbesondere im Strömungsbereich unmittelbar stromauf zur Hinterkante 5, der in Figur 2b vergrößert dargestellt ist, befinden sich in Strömungsrichtung verlaufende Rippenzüge 6, die jeweils einzelne Kühlkanäle 7 voneinander abgrenzen.To illustrate the previously used cooling technology of vanes for use in gas turbine plants is on the FIG. 2 a and b, which shows a known guide vane, with a vane platform 1 and a Leitschaufeldeckband 2, between which extends the vane blade 3 with a vane leading edge 4 and a Leitschaufelhinterkante 5. For cooling the internally hollow guide vane 3, which in FIG. 2a to illustrate the inner hollow cooling channel arrangement is shown partially in the plan view, cooling air K passes through both openings Within the vane cover 2 as well as within the vane platform 1. For effective cooling of the vane blade 3 are located in the interior of the vane flow contours, which ensure the most intimate possible thermal contact between the supplied cooling air and the inside to be cooled of the vane wall. Especially in the flow area immediately upstream of the trailing edge 5, the in FIG. 2b is shown enlarged, are located in the flow direction Rippenzüge 6, each delimiting individual cooling channels 7 from each other.

Solche Rippenzüge sind zum Beispiel auch aus WO0100964 bekannt. In WO0100964 sind die Rippenzüge als Querlenkarm ausgebildet, die paketweise nebeneinander angeordnet sind und durch eine Wand voneinander getrennt sind. Die Wand vermeidet dass die Kühlmittelströmung innerhalb eines Packets in die Strömungswege eines benachbarten Packets eindringen kann.Such rib trains are also off, for example WO0100964 known. In WO0100964 the rib trains are designed as Querlenkarm, which are arranged in packets side by side and are separated by a wall. The wall prevents the flow of coolant within a packet from entering the flow paths of an adjacent packet.

Die zueinander parallel orientierten Rippenzüge 6, die in Figur 2b der vorliegenden Anmeldung dargestellt sind, sind jeweils beidseitig mit den sich gegenüber liegenden Leitschaufel-Innenwänden verbunden und schließen somit zwei unmittelbar benachbarte Kühlkanäle 7 voneinander ab. Zur Verbesserung des Kühleffektes in diesem Strömungsbereich sind längs der Kühlkanäle 7 eine Vielzahl einzelner stiftartiger Verbindungsstege, sog. Pins 8 zwischen den sich beabstandet gegenüberliegenden Innenseiten der Leitschaufelwände vorgesehen, durch die Kühlluft eine effektive Durchmischung erfährt und somit in innigem Kontakt mit den Innenseiten der Leitschaufelwände kommt.The mutually parallel ribs 6, the in FIG. 2b The present application are shown, in each case connected on both sides with the opposing guide vane inner walls and thus close two immediately adjacent cooling channels 7 from each other. To improve the cooling effect in this flow region along the cooling channels 7 a plurality of individual pin-like connecting webs, so-called. Pins 8 between the spaced opposite inner sides of the guide vane walls provided by the cooling air undergoes effective mixing and thus comes into intimate contact with the inner sides of the vane walls ,

Zur Herstellung derart filigraner Kühlstrukturen im Inneren einer im Wege eines Gießverfahrens herzustellenden Leit- oder Laufschaufel sind für den Gießprozess sog. verlorene Kerne erforderlich, in denen die Negativkonturen sämtlicher innerhalb des Gussteils vorzusehenden Strukturen, insbesondere die Kühlluftströmung beeinflussenden Strömungskonturen einzuarbeiten sind. Um bspw. die in der Detaildarstellung gemäß Figur 2b gezeigten Rippenzüge 6 sowie die dazwischen befindlichen stiftartigen Pins 8 auszubilden, die zur besseren Veranschaulichung in Figur 3a in einer Draufsichtdarstellung nochmals gezeigt sind, gilt es einen Gusskern 9 bereitzustellen, der in Figur 3b gleichfalls in einer Draufsicht gezeigt ist, der zur Erzeugung der einzelnen Rippenzüge über nutartige Ausnehmungen 10 und zur Erzeugung der stiftartigen Pins 8 entsprechende Durchgangsöffnungen 1 1 vorsehen muss. Die Gesamtheit aller innerhalb des Gusskerns 9 vorzusehenden Ausnehmungen führt letzten Endes zu einer umfangreichen Perforation des Gusskerns und trägt entscheidend zur mechanischen Schwächung des Gusskernes bei, so dass letztlich mechanische Stabilitätsgrenzen erreicht und überschritten werden, die eine schadlose Bearbeitung und letztlich die Ausbildung kleinster Strömungskonturen innerhalb des Gussteiles nicht mehr gestatten. Um den Gusskern zu stabilisieren, sind insbesondere bei der Ausbildung der vorstehend beschriebenen Rippenzüge Modifikationen vorgenommen worden, so dass der Gusskern quer zur Längserstreckung der jeweiligen Rippenzüge den Gusskern stabilisierende Verbindungsstege 12 vorsieht. Durch die Massnahme sind jedoch die Rippenzüge 6 im fertig gegossenen Gussteil nicht mehr durchgängig ausgebildet, wie dies aus der Darstellung in Figur 4 a zu entnehmen ist, sondern weisen dort, wo im Gusskern die Verbindungsstege 12 vorgesehen waren nun entsprechende Unterbrechungen 13 auf (siehe Figur 4b).For the production of filigree cooling structures in the interior of a guide or moving blade to be produced by means of a casting process, lost cores are required for the casting process, in which the negative contours of all structures to be provided within the casting, in particular the flow contours affecting the cooling air flow, are to be incorporated. For example, in the detailed representation according to FIG. 2b shown ribbed trains 6 and the pin-like pins 8 located therebetween form, for better illustration in FIG. 3a are shown again in a plan view, it is necessary to provide a casting core 9, the in FIG. 3b is also shown in a plan view, which must provide for the production of the individual rib trains via groove-like recesses 10 and for generating the pin-like pins 8 corresponding through holes 1 1. The entirety of all to be provided within the casting core 9 recesses ultimately leads to extensive perforation of the casting core and contributes significantly to the mechanical weakening of the casting core, so that ultimately reaches and exceeded mechanical stability limits that a harmless processing and ultimately the formation of smallest flow contours within the Castings no longer allow. In particular, to stabilize the casting core In the formation of the above-described ribbed trains modifications have been made so that the casting core transverse to the longitudinal extent of the respective ribs trains the casting core stabilizing connecting webs 12 provides. By the measure, however, the ribs 6 in the finished cast casting are no longer formed continuously, as is apparent from the illustration in FIG. 4 a can be seen, but have, where in the casting core, the connecting webs 12 were provided now corresponding interruptions 13 (see FIG. 4b ).

Konnten bisher durchgängig ausgebildete Rippenzüge 6 die innerhalb der Kühlkanäle 7 enthaltene Kühlluftströmungen K vollständig voneinander separieren, wie dies in der schematisierten Draufsichtdarstellung in Figur 4a gezeigt ist, so treten nun durch Vorsehen entsprechender Unterbrechungen 13 längs der Rippenzüge 6, bedingt durch die stabilisierenden Verbindungsstege 12 innerhalb des Gusskernes, durch die Unterbrechungen 13 abzweigende Kühlluftströmungen K' auf, die die Kühlluftströmung in den benachbarten Kühlkanälen zu irritieren vermögen. Dies jedoch verringert die Kühleffizienz der durch die Kühlkanäle 7 hindurchtretenden Kühlluft, so dass nach Maßnahmen gesucht werden muss, mit denen die durch die Unterbrechungen 13 hindurchtretenden Kühlluftströmungsanteile vermieden werden können.Previously consistently trained ribbed trains 6 could completely separate the cooling air flows K contained within the cooling channels 7 from each other, as shown in the schematic plan view in FIG FIG. 4a is shown, then occur by providing appropriate interruptions 13 along the Rippenzüge 6, due to the stabilizing connecting webs 12 within the casting core, by the interruptions 13 branching cooling air flows K ', which are able to irritate the cooling air flow in the adjacent cooling channels. However, this reduces the cooling efficiency of the cooling air passing through the cooling channels 7, so that measures must be sought with which the passing through the interruptions 13 cooling air flow portions can be avoided.

Darstellung der ErfindungPresentation of the invention

Der Erfindung liegt die Aufgabe zugrunde, eine Kühlanordnung innerhalb eines hohlgegossenen Gussteils, mit einem von wenigstens zwei voneinander beabstandeten Gussteilwänden begrenzenden Strömungsbereich für ein Kühlmittel, der in Strömungsrichtung von wenigstens einem mit beiden Gussteilwänden verbundenen Rippenzug in zwei Kühlkanälen unterteilt ist, derart weiterzubilden, dass einerseits die getroffenen Maßnahmen zur Stabilisierung des für die Herstellung des Gussteils erforderlichen Gusskernes weitgehend unbeeinflusst bleiben sollen, jedoch die Kühlwirkung des durch die Kühlkanalanordnung hindurchtretenden Kühlmittels merklich verbessert werden soll.The invention is based on the object, a cooling arrangement within a hollow cast casting, with one of at least two spaced apart casting walls delimiting flow area for a coolant, which is divided in the flow direction of at least one connected to two casting walls Rippenzug in two cooling channels, such on the one hand the measures taken to stabilize the casting core required for the production of the casting should remain largely unaffected, but the cooling effect of passing through the cooling channel arrangement coolant should be significantly improved.

Die Lösung der der Erfindung zugrunde liegenden Aufgabe ist im Anspruch 1 angegeben. Den erfindungsgemäßen Gedanken vorteilhafte weiterbildende Merkmale sind Gegenstand der Unteransprüche sowie der weiteren Beschreibung insbesondere unter Bezugnahme auf die Ausführungsbeispiele zu entnehmen.The solution of the problem underlying the invention is specified in claim 1. The inventive concept advantageous further development features are the subject of the dependent claims and the further description in particular with reference to the exemplary embodiments.

Lösungsgemäß ist eine Kühlanordnung innerhalb eines hohlgegossenen Gussteils nach den Merkmalen des Oberbegriffes des Anspruches 1 derart ausgebildet, dass längs des wenigstens einen Rippenzuges wenigstens eine Unterbrechung vorgesehen ist, an der sich zwei Rippenenden beabstandet gegenüber stehen, von denen ein Rippenende eine Kontur in Art eines "Hundeknochens" aufweist. Mit Hilfe einer derartigen Strömungskontur ist es möglich, wie die weiteren Ausführungen zeigen werden, einen Kühlmittelströmungsfluss durch die Unterbrechung längs eines Rippenzuges weitgehend oder vollständig zu unterbinden.According to the solution, a cooling arrangement within a hollow cast part according to the features of the preamble of claim 1 is designed so that at least one interruption is provided along the at least one rib train, at which two rib ends are spaced apart, one end of the rib being contoured in the manner of a " Dog bone ". With the help of such a flow contour, it is possible, as the further embodiments will show, to largely or completely prevent coolant flow through the interruption along a rib train.

Die lösungsgemäße Maßnahme erfordert lediglich eine zusätzliche Kontur längs des Rippenzuges im Bereich einer Unterbrechung, durch die die Stabilität eines Gusskernes keineswegs in Mitleidenschaft gezogen wird. Auch mit der lösungsgemäßen Maßnahme ist es möglich, Verbindungsbereiche zwischen den durch die Rippenzüge getrennten Kühlkanälen vorzusehen, um auf diese Weise einen in sich geschlossenen und mechanisch stabilen Gusskern zu realisieren.The solution according to the measure only requires an additional contour along the Rippenzuges in the region of an interruption, by the stability of a casting core is not affected by any means. Even with the measure according to the solution, it is possible to provide connection areas between the cooling passages separated by the rib trains in order in this way to realize a self-contained and mechanically stable casting core.

Zur Illustration des lösungsgemäßen Gedankens wird auf die nachstehenden illustrierten Ausführungsbeispiele verwiesen.To illustrate the idea according to the solution, reference is made to the following illustrated exemplary embodiments.

Kurze Beschreibung der ErfindungBrief description of the invention

Die Erfindung wird nachstehend ohne Beschränkung des allgemeinen Erfindungsgedankens anhand von Ausführungsbeispielen unter Bezugnahme auf die Zeichnung exemplarisch beschrieben. Alle für das unmittelbare Verständnis der Erfindung nicht wesentlichen Elemente sind weggelassen worden. Gleiche Elemente sind in den verschiedenen Figuren mit den gleichen Bezugszeichen versehen. Die Strömungsrichtung der Medien ist mit Pfeilen angegeben. Es zeigen:

Fig. 1a und
b Draufsicht auf einen Rippenzug im Bereich einer Unterbrechung sowie modelliertes Strömungsbild,
Fig. 2a und b
Illustration einer Leitschaufel im innen liegenden Kühlkanälen gemäß Stand der Technik,
Fig. 3a, b, c
Illustration zur Ausbildung eines Gusskernes zur Schaffung von Kühlkanälen mit Rippenzügen und stiftartigen Pins,
Fig. 4a und b
Darstellung von Kühlmittelströmungsverhältnissen längs von Kühlkanälen ohne und mit unterbrochenen Rippenzügen sowie
Fig. 5
Darstellung mehrerer erfindungsgemäß ausgebildeter parallel zueinander verlaufender Rippenzüge.
The invention will now be described by way of example without limitation of the general inventive idea by means of embodiments with reference to the drawing. All elements not essential to the instant understanding of the invention have been omitted. The same elements are provided in the various figures with the same reference numerals. The flow direction of the media is indicated by arrows. Show it:
Fig. 1a and
b top view of a rib train in the area of an interruption and modeled flow pattern,
Fig. 2a and b
Illustration of a guide vane in the inside cooling channels according to the prior art,
Fig. 3a, b, c
Illustration for forming a casting core for creating cooling channels with ribbed and pin-like pins,
Fig. 4a and b
Representation of coolant flow conditions along cooling channels with and without interrupted Rippenzügen and
Fig. 5
Representation of several inventively designed parallel ribs.

Wege zur Ausführung der Erfindung, gewerbliche VerwendbarkeitWays to carry out the invention, industrial usability

Figur 1 a zeigt den Bereich einer Unterbrechung 13 längs eines Rippenzuges 6, wobei sich zwei Rippenenden 61, 62 längs des Rippenzuges 6 beabstandet gegenüber stehen. In der Bilddarstellung gemäß Figur 1a sei angenommen, dass eine Kühlmittelströmung K längs des Rippenzuges 6 in der durch die Pfeile angegebene Strömungsrichtung anliegt. Das Rippenende 61, das stromauf zur Unterbrechung 13 vorgesehen ist, weist hierbei lösungsgemäß eine Kontur 14 in Art eines Hundeknochens auf, wodurch die Kühlmittelströmung K nicht wie im erläuterten Fallbeispiel in Figur 4b im Rahmen von Querströmungen K' durch die Unterbrechungen 13 hindurchtritt, sondern jeweils beidseitig an der Unterbrechung 13 längs des jeweiligen Kühlkanals 7 vorbeiströmt. Durch die in Art eines Hundeknochens ausgebildete Rippenendkontur 14 am Rippenende 61 werden die beidseits zur Rippe 6 angrenzenden Strömungsanteile quer zur Längserstreckung des Rippenzuges 6 abgedrängt. Vorzugsweise weist die in Art eines Hundeknochens ausgebildete Kontur 14 eine quer zur Rippenlängserstreckung orientierte Ausdehnung D auf, die wenigstens dem 1,5fachen der jeweiligen Rippenbreite d entspricht. Die hundeknochenartig ausgebildete Rippenendkontur 14 ist unter strömungsdynamischen Gesichtspunkten optimiert und weist eine runde und damit eine Strömungswiderstand reduzierende Oberflächenkontur auf. Der axiale Abstand zwischen den beiden sich längs der Unterbrechung 13 gegenüberstehenden Rippenenden 61, 62 sollte die dreifache Länge der lateralen Ausdehnung D der hundeknochenförmig ausgebildeten Kontur 14 nicht überschreiten. FIG. 1 a shows the region of an interruption 13 along a rib train 6, wherein two rib ends 61, 62 are spaced apart from each other along the rib train 6. In the image representation according to FIG. 1a Let it be assumed that a coolant flow K rests along the rib train 6 in the flow direction indicated by the arrows. The rib end 61, which is provided upstream of the interruption 13, in this case according to the solution has a contour 14 in the manner of a dog bone, whereby the coolant flow K not as in the illustrated case in example FIG. 4b in the context of cross-currents K 'passes through the interruptions 13, but in each case on both sides of the interruption 13 along the respective cooling channel 7 flows past. By designed in the manner of a dog bone Rippenendkontur 14 at the rib end 61, the both sides of the rib 6 adjacent flow components are pushed transversely to the longitudinal extent of the Rippenzuges 6. Preferably, the contour 14 formed in the manner of a dog bone has an extension D oriented transversely to the rib longitudinal extension which corresponds at least to 1.5 times the respective rib width d. The dog-bone-shaped rib end contour 14 is optimized under flow dynamic aspects and has a round and thus a flow resistance reducing surface contour. The axial distance between the two along the break 13 facing rib ends 61, 62 should not exceed three times the length of the lateral extension D of the dog-bone-shaped contour 14.

Mittels strömungstechnischer Simulationen konnte der Effekt der Vermeidung eines Kühlmitteldurchtrittes durch die jeweils vorhandenen Unterbrechungen 13 längs eines Rippenzuges 6 bestätigt und nachgewiesen werden. Ein graphisches Simulationsergebnis ist in Figur 1b dargestellt. Hier kennzeichnen die dunklen Linienbereiche die Präsenz von Kühlmittel und es sei angenommen, dass der in Figur 1b dargestellte Strömungsbereich von links nach rechts mit Kühlmittel K durchströmt wird. Durch die hundeknochenartig ausgebildete Rippenendkontur 14, die stromauf zur Unterbrechung 13 vorgesehen ist, können nachweislich jene Strömungsanteile auf einen Minimum reduziert werden, die durch die Unterbrechung 13 von einem Kühlkanal 7 in den benachbarten Kühlkanal gelangen. Auf diese Weise ist es möglich die Kühleffizienz des Kühlmittels K innerhalb eines Kühlkanals 7 sicherzustellen, trotz des Vorsehens konstruktionsbedingter Unterbrechungen 13.By means of fluidic simulations, the effect of avoiding a coolant passage through the respectively present interruptions 13 along a rib train 6 could be confirmed and demonstrated. A graphical simulation result is in FIG. 1b shown. Here, the dark line areas indicate the presence of coolant and it is assumed that the in FIG. 1b shown flow range from left to right with coolant K is flowed through. Due to the dog-bone-shaped rib end contour 14, which is provided upstream of the interruption 13, it is demonstrably possible to reduce to a minimum those flow portions which pass through the interruption 13 from a cooling channel 7 into the adjacent cooling channel. In this way, it is possible to ensure the cooling efficiency of the coolant K within a cooling passage 7, despite the provision of design-related interruptions 13.

In einem Strömungsbereich, der wie in Figur 5 mehrere parallel zueinander orientierte Rippenzüge 6 zur gegenseitigen Abtrennung von Kühlkanälen 7 aufweist, hat sich in vorteilhafter Weise herausgestellt, dass besonders gute Strömungsergebnisse erzielt werden, wenn die Rippenendkonturen in Art eines Hundeknochens in einer Anordnung und Verteilung vorgesehen werden, die aus Figur 5 ersichtlich ist. Hier sei angenommen, dass drei nebeneinander verlaufende Rippenzüge 6 vorgesehen sind, längs denen jeweils Unterbrechungen 13 aus Gründen einer stabileren Ausbildung des Gusskernes vorgesehen sind. Ferner sei angenommen, dass die zwischen den Rippenzügen 6 befindlichen Kühlkanäle 7 von Kühlluft K mit der durch die Pfeildarstellung angegebenen Strömungsrichtung durchströmt werden. Auf eine zusätzliche Darstellung der längs der Kühlkanäle 7 befindlichen, stiftartig ausgebildeten Pins wird aus Gründen einer besseren Übersichtlichkeit verzichtet, gleichwohl diese in der Realität entsprechend vorzusehen sind. Längs des in der Bilddarstellung gemäß Figur 5 obersten Rippenzuges 6 sind die hundeknochenartig ausgebildeten Konturen 14 jeweils am stromaufwärtigen Rippenende zur jeder einzelnen Unterbrechung 13 vorgesehen. In dem dazu unmittelbar benachbarten mittleren Rippenzug hingegen ist die Hundeknochenkontur 14 am stromabwärtigen Ende zu jeder einzelnen Unterbrechung 13 längs des Rippenzuges vorgesehen. In dem unteren Rippenzug befinden sich die hundeknochenartig ausgebildeten Konturen 14 wieder einheitlich jeweils am stromaufwärtigen Rippenende am Ort jeder Unterbrechung 13. Ferner gilt es in dieser Rippenzuganordnung darauf zuachten, dass sich die Unterbrechungen längs jeweils eines Rippenzuges mit den Unterbrechungen längs eines benachbarten Rippenzuges in Richtung quer zur Rippenzuglängserstreckung nicht gegenseitig überlappen, wie die aus Figur 5 zu entnehmen ist.In a flow area that is like in FIG. 5 has multiple parallel ribs 6 for mutual separation of cooling channels 7 has been found to be advantageous that particularly good flow results are achieved when the Rippenendkonturen be provided in the manner of a dog bone in an arrangement and distribution, the FIG. 5 is apparent. Here it is assumed that three ribs 6 running side by side are provided, along which interruptions 13 are provided for reasons of a more stable formation of the casting core. Furthermore, it is assumed that the cooling channels 7 located between the ribs 6 are passed through by cooling air K with the flow direction indicated by the arrow representation. An additional illustration of the longitudinally located along the cooling channels 7, pin-like pins is omitted for reasons of clarity, however, these are provided accordingly in reality. Along the in the image representation according to FIG. 5 uppermost Rippenzuges 6, the dog-bone-like contours 14 are each provided at the upstream end of the rib for every single interruption 13. In contrast, in the immediately adjacent middle ridge train is the dog bone contour 14 is provided at the downstream end for each discrete interruption 13 along the ribcuff. In the lower ribcuff, the dogbone contours 14 are again uniformly located at the upstream rib end at the location of each break 13. Further, in this ribcrack assembly, it is necessary to ensure that the breaks are along a ribcuff with the breaks along an adjacent ribcuff in the transverse direction do not overlap each other, like those out of ribs FIG. 5 can be seen.

Es konnte gezeigt werden, dass mit der in Figur 5 illustrierten Anordnung der hundeknochenartig ausgebildeten Rippenendkonturen14 eine sehr gute Kühleffizienz erreichbar ist, die letztlich durch die Minimierung der durch die Unterbrechungen 13 hindurchtretenden Strömungsanteile erklärt werden kann.It could be shown that with the in FIG. 5 illustrated arrangement of the dog-bone-shaped Rippenendkonturen14 a very good cooling efficiency is achievable, which can ultimately be explained by minimizing the passing through the interruptions 13 flow components.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Leitschaufelplattformvane platform
22
LeitschaufeldeckbandLeitschaufeldeckband
33
Leitschaufelblattairfoil
44
Leitschaufelvorderkantevane leading edge
55
Leitschaufelhinterkantevane trailing
66
RippenzugRippenzug
77
Kühlkanalcooling channel
88th
Stiftartig ausgebildete PinsPin-like pins
99
Gusskerncasting core
1010
Nutförmige Ausnehmung innerhalb des GusskernsGrooved recess within the casting core
1111
Lochartige Ausnehmungen innerhalb des GusskernsHole-like recesses within the casting core
1212
Verbindungsbereich, VerbindungsstegConnection area, connecting bridge
1313
Unterbrechunginterruption
1414
Knochenartig ausgebildete KonturBone-shaped contour
61, 6261, 62
Rippenendenrib ends
KK
Kühlmittelcoolant
DD
Laterale Ausdehnung der knochenartig ausgebildeten KonturLateral extension of the bone-like contour
dd
Rippendickerib thickness
K'K '
Kühlmittelströmungsanteile die durch die Unterbrechung 13 hindurchtretenCoolant flow components passing through the break 13

Claims (7)

  1. Cooling duct arrangement within a hollow-cast casting, having a flow region for a coolant (K), which flow region is delimited by at least two casting walls spaced apart from each other and is divided in the flow direction into two cooling ducts (7) by at least one line of ribs (6) which is connected to both casting walls, characterized in that along the at least one line of ribs (6), at least one gap (13) is provided at which two rib ends (61, 62) stand opposite each other and spaced apart, of which one rib end has a contour in the shape of a dog's bone (14), wherein the dogbone contour (14) has two symmetrically formed bulges each protruding laterally from the line of ribs and each having a round outer contour favourable for flow dynamics, the dogbone contour (14) has an extension (D) transversely to the longitudinal extension of the line of ribs (6) which corresponds to at least 1.5 times a width (d) which may be assigned to the line of ribs (6).
  2. Cooling duct arrangement according to claim 1, characterised in that several gaps (13) are provided along the line of ribs (6), at each of which an upstream and a downstream rib end (61, 62) stand opposite each other, and that along a line of ribs (6), the dogbone contour (14) is provided uniformly in each case at the upstream or downstream rib end (61, 62) per gap.
  3. Cooling duct arrangement according to claim 1 or 2, characterised in that at least two lines of ribs (6) are provided running substantially parallel to each other, and that along the one line of ribs (6), the dogbone contour (14) is arranged uniformly at the downstream rib end (62) per gap (13), and along the other line of ribs (6) the dogbone contour (14) is arranged uniformly at each upstream rib end (61) per gap (13).
  4. Cooling duct arrangement according to any of claims 1 to 3, characterised in that at least two lines of ribs (6) are provided running substantially parallel to each other, and that the gaps (13) along the least two lines of ribs (6) do not overlap transversely to the course of the line of ribs (6).
  5. Cooling duct arrangement according to any of claims 1 to 4, characterised in that the region of the cooling ducts (7), pin-like connecting webs (8) are provided, known as pins, which are locally connected to both casting walls.
  6. Cooling duct arrangement according to any of claims 1 to 5, characterised in that the casting constitutes a guide vane or rotor blade of a flow rotation machine, preferably a gas turbine.
  7. Cooling duct arrangement according to claim 6, characterised in that the flow region provided for a coolant, preferably in the form of cooling air, is arranged directly upstream of the rear edge inside the guide vane or rotor blade.
EP09727227.2A 2008-03-31 2009-03-17 Cooling duct arrangement within a hollow-cast casting Not-in-force EP2265800B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH4712008 2008-03-31
PCT/EP2009/053108 WO2009121715A1 (en) 2008-03-31 2009-03-17 Cooling duct arrangement within a hollow-cast casting

Publications (2)

Publication Number Publication Date
EP2265800A1 EP2265800A1 (en) 2010-12-29
EP2265800B1 true EP2265800B1 (en) 2017-11-01

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EP09727227.2A Not-in-force EP2265800B1 (en) 2008-03-31 2009-03-17 Cooling duct arrangement within a hollow-cast casting

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US (1) US8360725B2 (en)
EP (1) EP2265800B1 (en)
WO (1) WO2009121715A1 (en)

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US9810071B2 (en) * 2013-09-27 2017-11-07 Pratt & Whitney Canada Corp. Internally cooled airfoil
WO2015065717A1 (en) * 2013-10-29 2015-05-07 United Technologies Corporation Pedestals with heat transfer augmenter
DE102015203175A1 (en) * 2015-02-23 2016-08-25 Siemens Aktiengesellschaft Guide or blade device and casting core
US10641174B2 (en) 2017-01-18 2020-05-05 General Electric Company Rotor shaft cooling
EP3421721A1 (en) * 2017-06-28 2019-01-02 Siemens Aktiengesellschaft A turbomachine component and method of manufacturing a turbomachine component
EP3425772B1 (en) 2017-07-03 2020-11-25 GE Energy Power Conversion Technology Limited Rotary electrical machine comprising a stator and a rotor
US10830072B2 (en) * 2017-07-24 2020-11-10 General Electric Company Turbomachine airfoil
US20200149401A1 (en) * 2018-11-09 2020-05-14 United Technologies Corporation Airfoil with arced baffle
US10975710B2 (en) * 2018-12-05 2021-04-13 Raytheon Technologies Corporation Cooling circuit for gas turbine engine component

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US5772397A (en) * 1996-05-08 1998-06-30 Alliedsignal Inc. Gas turbine airfoil with aft internal cooling
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US6234754B1 (en) * 1999-08-09 2001-05-22 United Technologies Corporation Coolable airfoil structure
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Publication number Publication date
EP2265800A1 (en) 2010-12-29
US20110064585A1 (en) 2011-03-17
WO2009121715A1 (en) 2009-10-08
US8360725B2 (en) 2013-01-29

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