EP1201879B1 - Composant refroidi, noyau de coulage et procédé pour la fabrication dudit composant - Google Patents

Composant refroidi, noyau de coulage et procédé pour la fabrication dudit composant Download PDF

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Publication number
EP1201879B1
EP1201879B1 EP01123193A EP01123193A EP1201879B1 EP 1201879 B1 EP1201879 B1 EP 1201879B1 EP 01123193 A EP01123193 A EP 01123193A EP 01123193 A EP01123193 A EP 01123193A EP 1201879 B1 EP1201879 B1 EP 1201879B1
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EP
European Patent Office
Prior art keywords
duct
cooling
casting core
cooling duct
component
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP01123193A
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German (de)
English (en)
Other versions
EP1201879A2 (fr
EP1201879A3 (fr
Inventor
Hartmut Haehnle
Ibrahim Dr. El-Nashar
Rudolf Dr. Kellerer
Beat Von Arx
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology AG
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Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1201879A2 publication Critical patent/EP1201879A2/fr
Publication of EP1201879A3 publication Critical patent/EP1201879A3/fr
Application granted granted Critical
Publication of EP1201879B1 publication Critical patent/EP1201879B1/fr
Anticipated expiration legal-status Critical
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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12Blades
    • F01D5/14Form or construction
    • F01D5/18Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187Convection cooling
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B22CASTING; POWDER METALLURGY
    • B22CFOUNDRY MOULDING
    • B22C9/00Moulds or cores; Moulding processes
    • B22C9/10Cores; Manufacture or installation of cores
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B22CASTING; POWDER METALLURGY
    • B22CFOUNDRY MOULDING
    • B22C9/00Moulds or cores; Moulding processes
    • B22C9/22Moulds for peculiarly-shaped castings
    • B22C9/24Moulds for peculiarly-shaped castings for hollow articles
    • YGENERAL 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
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10TTECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00Metal working
    • Y10T29/49Method of mechanical manufacture
    • Y10T29/49316Impeller making
    • Y10T29/49336Blade making
    • Y10T29/49339Hollow blade
    • Y10T29/49341Hollow blade with cooling passage

Definitions

  • the present invention relates to the field of gas turbines. It relates to a cooled component for gas turbines according to the preamble of Claim 1.
  • Such a component is in the form of a turbine blade e.g. from the publication GB-A-2 202 907.
  • the invention further relates to a casting core for the production of such Component and a method for producing such a component.
  • the efficiency of gas turbines which closely matches the height of the inlet temperature for the hot combustion gases and for reasons of efficient combustion Fuel efficiency and economy should be as high as possible, is out material-technical reasons in particular depends on an efficient Use of cooling air, which as a coolant usually the compressor stage is removed.
  • the operational safety and service life of the gas turbine require sufficient cooling of the thermally highly loaded turbine components or components, to which in particular the input-side guide vanes and blades of the first turbine stages include.
  • the cooling can do this be effected in different ways, e.g. by means of internal cooling (cooling the component by circulating cooling air inside) and / or by means of Film cooling (producing a cooling air film through suitably arranged outlet openings on the loaded outside of the component).
  • a well-known method for efficient internal cooling is a so-called “cyclone” (or “vortex chamber” in GB-A-2 202 907).
  • cyclone is an elongated cooling channel with a mostly circular or elliptical cross section through a series of tangentially opening feed bores with cooling air applied.
  • the incoming cooling air forms a vortex in the cooling channel, the order the longitudinal axis of the channel is rotated and due to the high speed and Turbulence in the edge area a particularly effective cooling of the channel wall and thus causing the cooled component.
  • Fig. 1 is a simplified perspective view of a turbine blade 10 reproduced with such a per se known cyclone cooling.
  • the turbine blade 10 is shown "transparent", so that the inner Cavities and channels are recognizable as solid lines.
  • the Turbine blade 10 has a leading edge 13 and a trailing edge ("trailing edge") 14, each extending in the longitudinal direction of the blade between the blade root 11 and the blade tip 12 extend.
  • the special one Training the blade root 11 for attachment of the blade on the rotor and to Supplying the blade with cooling air, as shown for example in US-A-4,293,275 or US-A-5,002,460 is shown in Fig. 1 for the sake of Simplification not reproduced.
  • Coolant channel 15 For internal cooling of the turbine blade 10 is from the blade root 11 ago a connection channel, not shown, cooling air in a longitudinal direction extending coolant channel 15 fed (vertical arrows in Fig. 1). Parallel to the coolant channel 15 and parallel to the to be cooled, especially thermally loaded front edge 13 of the turbine blade 10 extends a cylindrical cooling channel 16, which forms the cyclone. From the coolant channel 15 is a series of transverse Anspeisebohritch 17 to the cooling channel 16 and there opens approximately tangential. The tangentially through the Anspeisebohronne 17 in the cooling channel 16 incoming cooling air (horizontal arrows in Fig. 1) forms over the Channel extending vortex, which heat from the surrounding channel wall receives.
  • the heated cooling air either exits the cooling channel 16 from the front side from, or as shown in GB-A-2 202 907 through tangential outlets in FIG Shape of holes or slots.
  • Other indoor cooling facilities that simultaneously serve for film cooling and / or with the trailing edge 14 in conjunction are omitted in Fig. 1 for the sake of simplicity.
  • the object is solved by the entirety of the features of claim 1.
  • the essence of the invention is, by a suitable formation of the whole the feed bores to the rigidity of the associated casting core improve without adhering to the given diameter conditions for to give up the feed bores. This happens because the Anspeisebohrungen predominantly have a bore diameter, the smaller than half the hydraulic diameter of the cooling channel, and that to Improvement in the rate of application during the casting of the component Selected drilling holes have a bore diameter that is greater than that half hydraulic diameter of the cooling channel.
  • the selected Anspeisebohrept each at the ends of the cooling channel arranged, in particular the lowest and the uppermost Anspeisebohrung are used as a selected Anspeisebohrung. This can be over the entire interior of the cooling channel of the desired cooling air vortex form virtually unhindered and unfold its maximum cooling effect.
  • the component e.g. a turbine blade, especially long, but it can in With regard to the stability of the core, if according to another Embodiment additionally selected in the central region of the cooling channel Anspeisebohritch are provided.
  • the inventive casting core for the production of such a component which Cast core a first channel part to form the coolant channel and a second channel part for forming the cooling channel, and a plurality of Connecting webs which extend transversely between the two channel parts and serve the formation of Anspeisebohrept is characterized in that the Connecting webs predominantly have an outer diameter, the smaller is as half the hydraulic diameter of the cooling channel, and that selected Connecting webs have an outer diameter which is greater than half the hydraulic diameter of the cooling channel.
  • the selected connecting webs are each at the ends of the arranged second channel part, wherein in particular the lowermost and the uppermost Connecting web are used as a selected connecting web.
  • the inventive method for producing a component according to the invention By means of a metal casting process is characterized in that a Casting core according to the invention is used.
  • Fig. 3 is an embodiment of an internally cooled gas turbine component reproduced according to the invention a comparable to FIG. 1 turbine blade 10 '.
  • the same parts of the turbine blade 10 ' are denoted by the same reference numerals provided, as in the turbine blade 10 of Fig. 1.
  • Also in the turbine blade 10 ' are the coolant channel 15 and the cooling channel 16 through a superimposed series of feed bores 17 and 25, .., 27 connected.
  • the cast core 18 includes a first channel part 19, which requires the formation of the coolant channel 15 is, and a second channel portion 20, the 16 for the formation of the cooling channel responsible is. Both channel parts 19 and 20 are crossed by a series of arranged connecting webs 21 and 22, .., 24 connected, each one have round cross-section.
  • the majority of connecting webs, namely the "thin” connecting webs 21, serve to form the feed bores, the o.g. "Cyclone criterion" in terms of diameter suffice.
  • Only a few selected connecting webs, namely the connecting webs 22, 23 and 24, are “thicker” and thus strengthen the connection between the core parts 19 and 20 and thus the mechanical rigidity of the casting core 18 in total.
  • cooling channel 16 and the second channel part 20 is not very long, it is sufficient from, the two outer connecting webs 22 and 24 as selected Form connecting bridges with an enlarged cross-section. In this way can be practically on the entire length of the cooling channel 16 of the cooling air vortex form undisturbed, because there the "cyclone criterion" is fulfilled.
  • the diameter of the selected feed bores 25, .., 27 or the selected Connecting webs 22, .., 24 is chosen in each case larger than the half hydraulic diameter. How big the diameter actually is depends crucially on the geometry of the casting core and the casting process and must be determined on an individual basis.

Landscapes

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

Claims (9)

  1. Composant refroidi, notamment aube de turbine (10, 10') pour turbines à gaz, lequel composant (10, 10') présente, pour un refroidissement interne efficace, un canal de refroidissement (16) interne avec une section transversale de canal ronde, dans lequel canal de refroidissement (16) débouche essentiellement tangentiellement, pour la création d'un tourbillon de réfrigérant, une rangée d'alésages d'alimentation (17) pour le réfrigérant, partant d'un canal de réfrigérant commun (15) et disposés les uns au-dessus des autres dans la direction de l'axe longitudinal du canal de refroidissement (16), caractérisé en ce que les alésages d'alimentation (17) présentent essentiellement un diamètre d'alésage qui est plus petit que le demi-diamètre hydraulique du canal de refroidissement (16), et en ce que pour l'amélioration du rendement lors de la coulée du composant (10'), des alésages d'alimentation sélectionnés (25, .., 27) présentent un diamètre d'alésage qui est supérieur au demi-diamètre hydraulique du canal de refroidissement (16).
  2. Composant selon la revendication 1, caractérisé en ce que les alésages d'alimentation sélectionnés (25, 27) sont disposés à chaque fois aux extrémités du canal de refroidissement (16).
  3. Composant selon la revendication 2, caractérisé en ce que l'alésage d'alimentation le plus inférieur et le plus supérieur (25, respectivement 27) sont utilisés comme alésage d'alimentation sélectionné.
  4. Composant selon l'une quelconque des revendications 2 et 3, caractérisé en ce que l'on prévoit en outre dans la région centrale du canal de refroidissement (16) des alésages d'alimentation sélectionnés (26).
  5. Noyau de fonte (18) pour la fabrication d'un composant selon la revendication 1, lequel noyau de fonte (18) comprend une première partie de canal (19) pour la formation du canal de réfrigérant (15) et une deuxième partie de canal (20) pour la formation du canal de refroidissement (16), ainsi qu'une pluralité d'arêtes de connexion (21 ; 22, .., 24) qui s'étendent transversalement entre les deux parties de canal (19, 20) et servent à former les alésages d'alimentation (17 ; 25,.., 27) caractérisé en ce que les arêtes de connexion (21) présentent essentiellement un diamètre extérieur qui est inférieur au demi-diamètre hydraulique du canal de refroidissement (16) et en ce que des arêtes de connexion sélectionnées (22,.., 24) présentent un diamètre extérieur qui est supérieur au demi-diamètre hydraulique du canal de refroidissement (16).
  6. Noyau de fonte selon la revendication 5, caractérisé en ce que les arêtes de connexion sélectionnées (22, 24) sont disposées à chaque fois aux extrémités de la deuxième partie de canal (20).
  7. Noyau de fonte selon la revendication 6, caractérisé en ce que l'arête de connexion la plus inférieure et la plus supérieure (22, respectivement 24), sont utilisées comme arête de connexion sélectionnée.
  8. Noyau de fonte selon l'une quelconque des revendications 6 et 7, caractérisé en ce que l'on prévoit en outre dans la région centrale de la deuxième partie de canal (20) des arêtes de connexion sélectionnées (23).
  9. Procédé de fabrication d'un composant selon la revendication 1, au moyen d'un procédé de fonte de métal, caractérisé en ce que l'on utilise un noyau de fonte selon l'une quelconque des revendications 5 à 8.
EP01123193A 2000-10-27 2001-09-28 Composant refroidi, noyau de coulage et procédé pour la fabrication dudit composant Expired - Lifetime EP1201879B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10053356A DE10053356A1 (de) 2000-10-27 2000-10-27 Gekühltes Bauteil, Gusskern für die Herstellung eines solchen Bauteils, sowie Verfahren zum Herstellen eines solchen Bauteils
DE10053356 2000-10-27

Publications (3)

Publication Number Publication Date
EP1201879A2 EP1201879A2 (fr) 2002-05-02
EP1201879A3 EP1201879A3 (fr) 2003-07-16
EP1201879B1 true EP1201879B1 (fr) 2004-11-10

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP01123193A Expired - Lifetime EP1201879B1 (fr) 2000-10-27 2001-09-28 Composant refroidi, noyau de coulage et procédé pour la fabrication dudit composant

Country Status (3)

Country Link
US (1) US6547525B2 (fr)
EP (1) EP1201879B1 (fr)
DE (2) DE10053356A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106687232A (zh) * 2014-09-04 2017-05-17 赛峰航空器发动机 用于制造陶瓷芯的方法

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EP1529580B1 (fr) * 2003-10-29 2009-01-07 Siemens Aktiengesellschaft Moule de fonderie
US7128533B2 (en) * 2004-09-10 2006-10-31 Siemens Power Generation, Inc. Vortex cooling system for a turbine blade
US7690894B1 (en) 2006-09-25 2010-04-06 Florida Turbine Technologies, Inc. Ceramic core assembly for serpentine flow circuit in a turbine blade
US9056795B2 (en) * 2009-08-09 2015-06-16 Rolls-Royce Corporation Support for a fired article
GB0921818D0 (en) * 2009-12-15 2010-01-27 Rolls Royce Plc Casting of internal features within a product (
DE102010046331A1 (de) 2010-09-23 2012-03-29 Rolls-Royce Deutschland Ltd & Co Kg Gekühlte Turbinenschaufeln für ein Gasturbinentriebwerk
DE102012017491A1 (de) 2012-09-04 2014-03-06 Rolls-Royce Deutschland Ltd & Co Kg Turbinenschaufel einer Gasturbine mit Drallerzeugungselement
EP2964891B1 (fr) 2013-03-05 2019-06-12 Rolls-Royce North American Technologies, Inc. Agencement de composant pour moteur à turbine à gaz
WO2014163698A1 (fr) 2013-03-07 2014-10-09 Vandervaart Peter L Pièce refroidie de turbine à gaz
US10012090B2 (en) * 2014-07-25 2018-07-03 United Technologies Corporation Airfoil cooling apparatus
US9988912B2 (en) * 2015-05-08 2018-06-05 United Technologies Corporation Thermal regulation channels for turbomachine components
US10240465B2 (en) * 2016-10-26 2019-03-26 General Electric Company Cooling circuits for a multi-wall blade
US10465521B2 (en) 2016-10-26 2019-11-05 General Electric Company Turbine airfoil coolant passage created in cover
US10352176B2 (en) 2016-10-26 2019-07-16 General Electric Company Cooling circuits for a multi-wall blade
US10450950B2 (en) 2016-10-26 2019-10-22 General Electric Company Turbomachine blade with trailing edge cooling circuit
US10450875B2 (en) 2016-10-26 2019-10-22 General Electric Company Varying geometries for cooling circuits of turbine blades
US10301946B2 (en) 2016-10-26 2019-05-28 General Electric Company Partially wrapped trailing edge cooling circuits with pressure side impingements
US10273810B2 (en) 2016-10-26 2019-04-30 General Electric Company Partially wrapped trailing edge cooling circuit with pressure side serpentine cavities
US10598028B2 (en) 2016-10-26 2020-03-24 General Electric Company Edge coupon including cooling circuit for airfoil
US10309227B2 (en) * 2016-10-26 2019-06-04 General Electric Company Multi-turn cooling circuits for turbine blades
EP3832069A1 (fr) 2019-12-06 2021-06-09 Siemens Aktiengesellschaft Aube de turbine pour turbine à gaz fixe
US11814965B2 (en) 2021-11-10 2023-11-14 General Electric Company Turbomachine blade trailing edge cooling circuit with turn passage having set of obstructions
CN114215607A (zh) * 2021-11-29 2022-03-22 西安交通大学 一种涡轮叶片前缘旋流冷却结构
CN114109518A (zh) * 2021-11-29 2022-03-01 西安交通大学 一种涡轮叶片前缘带肋旋流-气膜复合冷却结构
CN114412577B (zh) * 2022-01-24 2024-03-15 杭州汽轮动力集团股份有限公司 涡轮动叶长叶片

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106687232A (zh) * 2014-09-04 2017-05-17 赛峰航空器发动机 用于制造陶瓷芯的方法
CN106687232B (zh) * 2014-09-04 2019-04-05 赛峰航空器发动机 用于制造陶瓷芯的方法

Also Published As

Publication number Publication date
US20020051706A1 (en) 2002-05-02
EP1201879A2 (fr) 2002-05-02
EP1201879A3 (fr) 2003-07-16
DE10053356A1 (de) 2002-05-08
DE50104476D1 (de) 2004-12-16
US6547525B2 (en) 2003-04-15

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