EP2300178B1 - Procédé de fabrication par technique de coulée une aube pour une turbine à gaz et noyeau de fonderie pour cette aube - Google Patents

Procédé de fabrication par technique de coulée une aube pour une turbine à gaz et noyeau de fonderie pour cette aube Download PDF

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Publication number
EP2300178B1
EP2300178B1 EP09761582.7A EP09761582A EP2300178B1 EP 2300178 B1 EP2300178 B1 EP 2300178B1 EP 09761582 A EP09761582 A EP 09761582A EP 2300178 B1 EP2300178 B1 EP 2300178B1
Authority
EP
European Patent Office
Prior art keywords
blade
mold
core
cavity
casting
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
EP09761582.7A
Other languages
German (de)
English (en)
Other versions
EP2300178A1 (fr
Inventor
Jose Anguisola Mcfeat
Jörg KRÜCKELS
Roland DÜCKERSHOFF
Brian Kenneth Wardle
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
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Priority to PL09761582T priority Critical patent/PL2300178T3/pl
Publication of EP2300178A1 publication Critical patent/EP2300178A1/fr
Application granted granted Critical
Publication of EP2300178B1 publication Critical patent/EP2300178B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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
    • B22C7/06—Core boxes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D25/00—Special casting characterised by the nature of the product
    • B22D25/02—Special casting characterised by the nature of the product by its peculiarity of shape; of works of art
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F05D2230/211—Manufacture essentially without removing material by casting by precision casting, e.g. microfusing or investment casting

Definitions

  • the present invention relates to the field of gas turbines. It relates to a method for producing a gas turbine blade for a gas turbine as well as a tool for producing a casting core for the casting production of the blade
  • Blades of gas turbines which are attached either as blades on the rotor or as vanes on the housing surrounding the rotor, are acted upon by the hot gas coming from the combustion chamber and are exposed to thermal stresses. These blades are increasingly flows around in the course of improving the thermal efficiency with even higher turbine inlet temperatures. It is therefore inevitable that these blades must be cooled inside and / or outside by a cooling medium, in particular cooling air, preferably via the blade root is introduced into the hollow interior of the airfoil, there the blade inside convectively applied cooling method or optionally by Impact cooling cools, and is then blown into the hot gas stream, where appropriate, on the outside of the blade to accomplish a so-called film cooling.
  • the cooling medium flows through the interior of the blade usually in several serpentine-like contiguous cooling channels extending in the radial direction through the airfoil.
  • a casting core In the casting production of such a blade, a casting core must be generated, which forms the inner cavity of the blade with the cooling channels and other details during casting of the blades and keeps free.
  • a core mold composed of two mold halves is used, which are pulled apart in a certain direction during demoulding of the finished casting core (see, for example, US Pat US-A-5,716,192 ). Due to the direction in which the two mold halves must be pulled apart, there are limitations in the design of the casting core and thus the design of the interior of the later blade. These restrictions play a role, especially in complex forms of the interior, as they are used in the WO-A1-03 / 042503 are shown. In order to produce the interior of the blade, which consists of different cooling circuits, and a multiplicity of pins and turbulators, several casting cores are produced and combined with one another, which leads to a very complex production process.
  • the publication DE 101 29 975 A1 discloses a mold for the core of a gas turbine blade with interchangeable inserts to produce blades with different cavity geometries, especially in final development.
  • the invention aims to remedy this situation. It is therefore an object of the invention to propose a manufacturing method for a blade, with respect to the internal cooling while overcoming certain restrictions caused by the casting core is improved and can be produced at the same time with little extra effort. It is a further object of the invention to specify a tool for producing a casting core for the casting production of the blade.
  • the turbulators or pins extend in a direction into the interior, which is substantially perpendicular to the associated inner surface.
  • the method according to the invention for producing the blade by casting in which in a first step a core mold is provided for molding a core free of the interior of the blade, in a second step by means of the core mold of the casting core, in a third step the casting core of FIG Core mold is demolded, and in a fourth step by means of the casting core, the blade is characterized, characterized in that the provided in the first step core shape comprises two mold halves, which are pulled apart during demolding in a first direction, wherein in the mold halves in At least one mold insert is provided for the formation of the turbulators or pins, and in the third step, after the mold halves have been pulled apart in the first direction, the at least one mold insert is pulled away from the molded mold core in a second direction deviating from the first direction approx.
  • An embodiment of the method according to the invention is characterized in that the second direction is perpendicular to the inner surface belonging to the turbulators or pins.
  • a plurality of mold inserts are arranged in the mold halves, which are removed during removal from the molded cast core in different directions deviating from the first direction.
  • FIG. 1 an embodiment of a gas turbine blade according to the invention is shown in cross-section in a highly simplified representation.
  • the blade 10 has a blade profile with a leading edge 11, a trailing edge 12 and a (convex) suction side 13 and a (concave) pressure side 14.
  • the blade 10 has a wall 15 enclosing a hollow interior 16 which is used to guide cooling air is that can flow out of other provided at the trailing edge 12deluftauslässen 17 in the outer space.
  • the interior 16 may be divided by one or more web (s) 29 into several subspaces.
  • a casting core 21 (FIG. Fig. 2 ), which must be generated beforehand.
  • a core mold 23 according to the in Fig. 3 used, which is composed of two along a parting plane 25 separable mold halves 23a and 23b, which in demolding in the by the arrows in Fig. 3 indicated direction are drawn apart. Due to the predetermined direction in which the two mold halves 23a and 23b have to be pulled apart during demolding (demoulding direction), the orientation of certain elements in the interior 16 of the blade is also predefined indirectly via the casting core 21.
  • the web 29 inevitably extends in the interior 16 of the blade in Entformungsraum, because only so the mold halves 23a and 23b can be pulled with their corresponding web elements 30 from the finished casting core.
  • additional elements 18 are now arranged or formed in the interior 16 in the trailing edge region of the blade 10, which may be formed as (round) pins or (rib-like) turbulators and the Heat transfer between the cooling air flowing in the interior 16 and the wall 15 improve.
  • the direction in which the elements 18 protrude from the wall 15, starting in the interior 16, is now in an angular range, regardless of the Entformungscardi the Fig. 3 be selectable, ie the orientation of the elements 18 may differ from the orientation of the web 29.
  • the elements 18 should be perpendicular to the inner surface 19 or 20 of the wall from which they emanate, for fluidic reasons, as in Fig. 1 indicated by the right angle.
  • the casting core 21 would have to have correspondingly shaped and oriented recesses 22 (FIG. Fig. 2 ).
  • the two-part core mold 23 of Fig. 3 would have to be arranged on the mold halves 23a and 23b to form the recesses 22 corresponding form elements 26.
  • the two mold halves 23a and 23b can no longer be pulled apart in the demoulding direction without deforming or destroying the recesses 22 formed, or shearing the mold elements 26.

Landscapes

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

Claims (5)

  1. Procédé de fabrication par technique de coulée d'une aube (10) pour une turbine à gaz, laquelle aube (10) comprend un bord avant (11) et un bord arrière (12), ainsi qu'à l'intérieur un espace intérieur (16) délimité par des surfaces intérieures (19, 20) pour faire passer de l'air de refroidissement, l'espace intérieur (16) étant divisé en plusieurs espaces partiels par au moins une nervure (29) s'étendant entre les surfaces intérieures (19, 20), et une pluralité de moyens (18) formés sur la paroi (15) pour améliorer le refroidissement étant disposés de manière répartie dans la région du bord arrière (12) pour améliorer le transfert de chaleur entre la paroi (15) de l'aube et l'air de refroidissement, lesquels moyens pénètrent dans l'espace intérieur (16) à partir des surfaces intérieures (19, 20), et un moule à noyau (23) pour mouler un noyau de coulée (21) maintenant libre l'espace intérieur (16) de l'aube (10) étant fourni lors d'une première étape, le noyau de coulée (21) étant fabriqué au moyen du moule à noyau (23) lors d'une deuxième étape, le noyau de coulée (21) étant démoulé hors du moule à noyau (23) lors d'une troisième étape, et l'aube (10) étant coulée au moyen du noyau de coulée (21) lors d'une quatrième étape,
    caractérisé en ce que le moule à noyau (23) fourni lors de la première étape comporte deux demi-moules (23a, 23b) qui comprennent au moins un élément de nervure (30) pour la formation de l'au moins une nervure (29) de l'aube, et en ce que, lors du démoulage, les deux demi-moules (23a, 23b) sont séparés par traction dans une première direction dans laquelle s'étend l'au moins un élément de nervure (30), au moins un insert de moule (27, 28) prévu pour la formation des moyens (18) et doté d'éléments de moule (26) qui servent à la formation d'évidements (22) pour la formation des moyens (18) sur l'aube (10) étant disposé dans les demi-moules (23a, 23b) dans la région du bord arrière, et en ce que lors de la troisième étape après la séparation par traction des demi-moules (23a, 23b) dans la première direction, l'au moins un insert de moule (27, 28) est retiré du noyau de coulée formé (21) dans une deuxième direction qui est différente de la première direction et dans laquelle les moyens (18) pénètrent dans l'espace intérieur (16).
  2. Procédé selon la revendication 1,
    caractérisé en ce que la deuxième direction est orientée perpendiculairement à la surface intérieure (19, 20) appartenant aux moyens (18).
  3. Procédé selon la revendication 1 ou 2,
    caractérisé en ce que plusieurs inserts de moule (27, 28) sont disposés dans les demi-moules (23a, b), lesquels inserts de moule sont tirés dans diverses directions différentes de la première direction lors du démoulage du noyau de coulée formé (21).
  4. Procédé de fabrication d'un noyau de coulée (21) pour la fabrication par technique de coulée d'une aube (10) pour une turbine à gaz, laquelle aube (10) comprend un bord avant (11) et un bord arrière (12), ainsi qu'à l'intérieur un espace intérieur (16) délimité par des surfaces intérieures (19, 20) pour faire passer de l'air de refroidissement, l'espace intérieur (16) étant divisé en plusieurs espaces partiels par au moins une nervure (29) s'étendant entre les surfaces intérieures (19, 20), et une pluralité de moyens (18) formés sur la paroi (15) pour améliorer le refroidissement étant disposés de manière répartie dans la région du bord arrière (12) pour améliorer le transfert de chaleur entre la paroi (15) de l'aube et l'air de refroidissement, lesquels moyens pénètrent dans l'espace intérieur (16) à partir des surfaces intérieures (19, 20), caractérisé en ce qu'un moule à noyau (23) est prévu, lequel est composé de deux demi-moules (23a et 23b) séparables le long d'un plan de séparation (25) sur lesquels est prévu au moins un élément de nervure (30) pour la formation de la nervure (29) de l'aube (10), l'orientation de l'au moins un élément de nervure (30) correspondant à la direction de démoulage pour la séparation par traction des deux demi-moules (23a, 23b) et
    en ce qu'au moins un insert de moule (27, 28) prévu pour la formation des moyens (18) et doté d'éléments de moule (26) qui servent à la formation d'évidements (22) pour la formation des moyens (18) sur l'aube (10) est disposé dans les demi-moules (23a, 23b) dans la région du bord arrière, l'au moins un insert de moule (27, 28) pouvant être retiré du noyau de coulée (21) séparément des demi-moules (23a, 23b) dans une direction qui correspond à l'orientation des moyens (18) et qui diffère de la direction de démoulage.
  5. Outil selon la revendication 4,
    caractérisé en ce que les moyens (18) sont des turbulateurs ou des chevilles qui s'étendent dans l'espace intérieur (16) dans une direction qui est perpendiculaire à la surface intérieure associée.
EP09761582.7A 2008-06-12 2009-05-20 Procédé de fabrication par technique de coulée une aube pour une turbine à gaz et noyeau de fonderie pour cette aube Not-in-force EP2300178B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL09761582T PL2300178T3 (pl) 2008-06-12 2009-05-20 Sposób wytwarzania łopatki do turbiny gazowej za pomocą techniki odlewniczej i narzędzie do wytwarzania rdzenia odlewniczego do łopatki

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH8982008 2008-06-12
PCT/EP2009/056150 WO2009150019A1 (fr) 2008-06-12 2009-05-20 Aube pour une turbine à gaz et procédé de fabrication par technique de coulée d’une telle aube

Publications (2)

Publication Number Publication Date
EP2300178A1 EP2300178A1 (fr) 2011-03-30
EP2300178B1 true EP2300178B1 (fr) 2013-06-19

Family

ID=39698763

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09761582.7A Not-in-force EP2300178B1 (fr) 2008-06-12 2009-05-20 Procédé de fabrication par technique de coulée une aube pour une turbine à gaz et noyeau de fonderie pour cette aube

Country Status (7)

Country Link
US (2) US20110236222A1 (fr)
EP (1) EP2300178B1 (fr)
JP (1) JP5717627B2 (fr)
DK (1) DK2300328T3 (fr)
ES (2) ES2427616T3 (fr)
PL (1) PL2300178T3 (fr)
WO (1) WO2009150019A1 (fr)

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US8353329B2 (en) 2010-05-24 2013-01-15 United Technologies Corporation Ceramic core tapered trip strips
EP2441537A1 (fr) * 2010-10-18 2012-04-18 Siemens Aktiengesellschaft Outil à noyau doté de crayons variables et procédé de fabrication d'un noyau
EP2450122A1 (fr) * 2010-11-03 2012-05-09 Siemens Aktiengesellschaft Optimisation d'un outil por la fabrication de noyaux, procédé de fabrication d'un outil pour la fabrication de noyaux et un outil pour la fabrication de noyaux
EP2489836A1 (fr) 2011-02-21 2012-08-22 Karlsruher Institut für Technologie Composant pouvant être refroidi
US9587492B2 (en) * 2012-05-04 2017-03-07 General Electric Company Turbomachine component having an internal cavity reactivity neutralizer and method of forming the same
DE102013000320B4 (de) 2013-01-10 2018-10-31 Audi Ag Werkzeugvorrichtung für die Herstellung eines Gussbauteils
US9835035B2 (en) * 2013-03-12 2017-12-05 Howmet Corporation Cast-in cooling features especially for turbine airfoils
US9695696B2 (en) * 2013-07-31 2017-07-04 General Electric Company Turbine blade with sectioned pins
WO2015094420A1 (fr) * 2013-12-20 2015-06-25 United Technologies Corporation Fixation élastique pour composant composite à matrice organique
WO2016060653A1 (fr) * 2014-10-15 2016-04-21 Siemens Aktiengesellschaft Système de coulage sous pression destiné à former un composant utilisable dans une à turbine a gaz
GB2553331A (en) * 2016-09-02 2018-03-07 Rolls Royce Plc Gas turbine engine
US20210276077A1 (en) * 2018-07-18 2021-09-09 Poly6 Technologies, Inc. Articles and methods of manufacture

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Also Published As

Publication number Publication date
JP5717627B2 (ja) 2015-05-13
WO2009150019A1 (fr) 2009-12-17
JP2011522991A (ja) 2011-08-04
US20110236222A1 (en) 2011-09-29
PL2300178T3 (pl) 2013-11-29
ES2427616T3 (es) 2013-10-31
DK2300328T3 (da) 2012-11-26
ES2393887T3 (es) 2012-12-28
US20140060766A1 (en) 2014-03-06
EP2300178A1 (fr) 2011-03-30

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