EP2265800B1 - Agencement de canaux de refroidissement à l intérieur d une pièce moulée creuse - Google Patents

Agencement de canaux de refroidissement à l intérieur d une pièce moulée creuse 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
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.)
Not-in-force
Application number
EP09727227.2A
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German (de)
English (en)
Other versions
EP2265800A1 (fr
Inventor
Jose Anguisola Mcfeat
Erich Kreiselmaier
Christoph Nagler
Sergei Riazantsev
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.)
Ansaldo Energia IP UK Ltd
Original Assignee
Ansaldo Energia IP UK Ltd
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Publication of EP2265800A1 publication Critical patent/EP2265800A1/fr
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Publication of EP2265800B1 publication Critical patent/EP2265800B1/fr
Not-in-force legal-status Critical Current
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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.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (7)

  1. Disposition de canaux de refroidissement à l'intérieur d'une pièce en fonte coulée en creux, avec une zone d'écoulement, délimitée par au moins deux parois de pièce en fonte écartées l'une de l'autre, pour un fluide de refroidissement (K), qui est divisée, dans le sens de l'écoulement, par au moins une rangée de nervures (6), reliées avec les deux parois de la pièce en fonte, en deux canaux de refroidissement (7), caractérisée en ce que, le long de l'au moins une rangée de nervures (6), est prévue au moins une interruption (13), au niveau de laquelle se font face, à une certaine distance, deux extrémités de nervures (61, 62), dont une extrémité de nervure présente un contour en forme d'os de chien (14), le contour en forme d'os de chien (14) comprenant deux bombements symétriques dépassant chacun latéralement la rangée de nervure, qui présentent chacun un contour extérieur rond favorisant l'écoulement et le contour en forme d'os de chien (14) possédant une extension (D) transversale par rapport à l'extension longitudinale de la rangée de nervures (6), qui correspond au moins à 1,5 fois une largeur (d) pouvant être attribuée à la rangée de nervures (6).
  2. Disposition de canaux de refroidissement selon la revendication 1, caractérisée en ce que, le long d'une rangée de nervures (6), sont prévues plusieurs interruptions (13), au niveau desquelles se font face des extrémités de nervures amont et aval (61, 62) et en ce que, le long d'une rangée de nervures (6), le contour en forme d'un os de chien (14) est prévu une fois par interruption sur l'extrémité de nervure amont ou aval (61, 62).
  3. Disposition de canaux de refroidissement selon la revendication 1 ou 2, caractérisée en ce qu'au moins deux rangées de nervures (6) globalement parallèles sont prévues et en ce que, le long d'une rangée de nervures (6), le contour en forme d'os de chien (14) est présent une fois par interruption (13) sur l'extrémité de nervure aval (62) et, le long de l'autre rangée de nervures (6), le contour en forme d'os de chien (14) est présent une fois par interruption (13) sur l'extrémité de nervure amont (61).
  4. Disposition de canaux de refroidissement selon l'une des revendications 1 à 3, caractérisée en ce qu'au moins deux rangées de nervures (6) globalement parallèles sont prévues et en ce que, les interruptions (13) ne se superposent pas le long des au moins deux rangées de nervures (6) transversalement par rapport à l'extension des rangées de nervures (6).
  5. Disposition de canaux de refroidissement selon l'une des revendications 1 à 4, caractérisée en ce que, au niveau des canaux de refroidissement (7), sont prévues des ponts de liaison (8) sous la forme de goupilles, appelés broches, qui sont reliés localement avec les deux parois de la pièce en fonte.
  6. Disposition de canaux de refroidissement selon l'une des revendications 1 à 5, caractérisée en ce que la pièce en fonte constitué une aube directrice ou une pale d'une turbomachine, de préférence d'une turbine à gaz.
  7. Disposition de canaux de refroidissement selon la revendication 6, caractérisée en ce que la zone d'écoulement prévue pour un fluide de refroidissement, de préférence sous la forme d'air de refroidissement, est disposée immédiatement en amont de l'arête arrière à l'intérieur de l'aube directrice ou de la pale.
EP09727227.2A 2008-03-31 2009-03-17 Agencement de canaux de refroidissement à l intérieur d une pièce moulée creuse Not-in-force EP2265800B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH4712008 2008-03-31
PCT/EP2009/053108 WO2009121715A1 (fr) 2008-03-31 2009-03-17 Agencement de canaux de refroidissement à l’intérieur d’une pièce moulée creuse

Publications (2)

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

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EP09727227.2A Not-in-force EP2265800B1 (fr) 2008-03-31 2009-03-17 Agencement de canaux de refroidissement à l intérieur d une pièce moulée creuse

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

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US9810071B2 (en) * 2013-09-27 2017-11-07 Pratt & Whitney Canada Corp. Internally cooled airfoil
US10247099B2 (en) * 2013-10-29 2019-04-02 United Technologies Corporation Pedestals with heat transfer augmenter
DE102015203175A1 (de) * 2015-02-23 2016-08-25 Siemens Aktiengesellschaft Leit- oder Laufschaufeleinrichtung und Gießkern
US10641174B2 (en) 2017-01-18 2020-05-05 General Electric Company Rotor shaft cooling
EP3421721A1 (fr) * 2017-06-28 2019-01-02 Siemens Aktiengesellschaft Composant de turbomachine et procédé de fabrication d'un composant de turbomachine
EP3425772B1 (fr) 2017-07-03 2020-11-25 GE Energy Power Conversion Technology Limited Machine électrique tournante comprenant un stator et un 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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US5536143A (en) * 1995-03-31 1996-07-16 General Electric Co. Closed circuit steam cooled bucket
US5772397A (en) * 1996-05-08 1998-06-30 Alliedsignal Inc. Gas turbine airfoil with aft internal cooling
US6213714B1 (en) * 1999-06-29 2001-04-10 Allison Advanced Development Company Cooled airfoil
US6234754B1 (en) * 1999-08-09 2001-05-22 United Technologies Corporation Coolable airfoil structure
US6254334B1 (en) * 1999-10-05 2001-07-03 United Technologies Corporation Method and apparatus for cooling a wall within a gas turbine engine
US6402470B1 (en) 1999-10-05 2002-06-11 United Technologies Corporation Method and apparatus for cooling a wall within a gas turbine engine
US6602047B1 (en) * 2002-02-28 2003-08-05 General Electric Company Methods and apparatus for cooling gas turbine nozzles
US6902372B2 (en) * 2003-09-04 2005-06-07 Siemens Westinghouse Power Corporation Cooling system for a turbine blade
US7186084B2 (en) * 2003-11-19 2007-03-06 General Electric Company Hot gas path component with mesh and dimpled cooling
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Publication number Publication date
EP2265800A1 (fr) 2010-12-29
US20110064585A1 (en) 2011-03-17
WO2009121715A1 (fr) 2009-10-08
US8360725B2 (en) 2013-01-29

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