US20110236222A1 - Blade for a gas turbine and casting technique method for producing same - Google Patents

Blade for a gas turbine and casting technique method for producing same Download PDF

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Publication number
US20110236222A1
US20110236222A1 US12/961,659 US96165910A US2011236222A1 US 20110236222 A1 US20110236222 A1 US 20110236222A1 US 96165910 A US96165910 A US 96165910A US 2011236222 A1 US2011236222 A1 US 2011236222A1
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US
United States
Prior art keywords
blade
mold
cavity
core
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.)
Abandoned
Application number
US12/961,659
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English (en)
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
Assigned to ALSTOM TECHNOLOGY LTD reassignment ALSTOM TECHNOLOGY LTD ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: WARDLE, BRIAN KENNETH, DUCKERSHOFF, ROLAND, KRUCKELS, JORG, MCFEAT, JOSE ANGUISOLA
Publication of US20110236222A1 publication Critical patent/US20110236222A1/en
Priority to US14/075,555 priority Critical patent/US20140060766A1/en
Assigned to GENERAL ELECTRIC TECHNOLOGY GMBH reassignment GENERAL ELECTRIC TECHNOLOGY GMBH CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: ALSTOM TECHNOLOGY LTD
Abandoned legal-status Critical Current

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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 turbine technology. It refers to a blade for a gas turbine and a method for producing such a blade by a casting technique.
  • Blades of gas turbines which are fastened either as rotor blades on the rotor or fastened as stator blades on the casing which encloses the rotor, are subjected to impingement by hot gas which comes from the combustor and are exposed to thermal loads in the process. These blades, in the course of improving the thermal efficiency, are increasingly exposed to circumferential flow at still higher turbine inlet temperatures.
  • these blades have to be cooled internally and/or externally by a cooling medium, especially cooling air, being introduced preferably via the blade root into the hollow interior of the blade airfoil, cooling the blade internally there via convectively applied cooling methods or selectively by means of impingement cooling, and then being blown out into the hot gas flow, in order to carry out a so-called film cooling there if necessary on the external side of the blade.
  • the cooling medium flows through the interior of the blade mostly in a plurality of cooling passages which are connected in a serpentine-like manner and extend through the blade airfoil in the radial direction.
  • a casting core which forms and keeps the internal hollow cavity of the blade with the cooling passages free and further details during the casting of the blades, has to be created.
  • a core mold assembled from two halves which during demolding of the finished casting core are drawn apart in a specified direction (see U.S. Pat. No. 5,716,192, for example).
  • Contingent upon the direction in which the two mold halves have to be drawn apart limitations ensue in the design of the casting core and therefore in the design of the cavity of the subsequent blade. These limitations play a role particularly in the case of complex shapes of the cavity, as are described in WO-A1-03/042503, for example.
  • a plurality of casting cores are produced and combined with each other, which leads to a very costly production process.
  • the present disclosure is directed to a blade for a gas turbine.
  • the blade includes a leading edge and a trailing edge, and an interior cavity, which is delimited by internal surfaces, for guiding cooling air therethrough.
  • a multiplicity of members which are formed on the wall to improve cooling.
  • the members are arranged in a distributed manner in the region of the trailing edge and project from the internal surfaces into the cavity.
  • the members extend into the cavity in a direction which can be freely selected within an angular range.
  • the present disclosure is directed to method for producing the above blade.
  • the method includes, in a first step, providing a core mold for forming a casting core which keeps the cavity of the blade free.
  • the method also includes, in a second step, producing the casting core by means of the core mold, in a third step, removing the casting core from the core mold and, in a fourth step, casting the blade by the casting core.
  • the core mold which is provided in the first step comprises two mold halves, which during demolding are drawn apart in a first direction.
  • At least one mold insert, which is provided for forming the members, is arranged in the mold halves in the trailing edge region.
  • the at least one mold insert is withdrawn from the formed casting core in a second direction which differs from the first direction.
  • FIG. 1 shows in cross section in a greatly simplified view an exemplary embodiment of a blade according to the invention with turbulators or pins which project into the cavity perpendicularly to the wall surface in the region of the trailing edge;
  • FIG. 2 shows in section the simplified casting core for producing the blade from FIG. 1 by a casting technique
  • FIG. 3 shows the problems which are associated with the mold halves of the core mold when producing the casting core from FIG. 2 ;
  • FIG. 4 shows in a view which is comparable to FIG. 3 a core mold, which is modified within the scope of the invention, with mold inserts for overcoming the limitations which are associated with the core mold according to FIG. 3 , and
  • FIG. 5 shows one of the mold inserts from FIG. 4 .
  • the invention should provide a remedy here. It is therefore an object of the invention to propose a blade which is improved with regard to internal cooling, overcoming certain limitations created by the casting core, and which at the same time can be produced with little additional cost. It is furthermore an object of the invention to disclose a method for producing such a blade.
  • the turbulators or pins which are formed on the wall in the region of the trailing edge for improving the heat transfer between the wall of the blade and the cooling air extend into the cavity in a direction which can be freely selected within an angular range.
  • the turbulators or pins extend into the cavity in a direction which is essentially perpendicular to the associated internal surface.
  • the method according to the invention for producing the blade by a casting technique in which, in a first step, a core mold is provided for forming a casting core which keeps the cavity of the blade free, in a second step, the casting core is produced by means of the core mold, in a third step, the casting core is removed from the core mold, and in a fourth step, the blade is cast by means of the casting core.
  • the core mold which is provided in the first step, comprises two mold halves which during demolding are drawn apart in a first direction, wherein at least one mold insert, which is provided for forming the turbulators or pins, is arranged in the mold halves in the trailing edge region, and in the third step, after the parting of the mold halves in the first direction, the at least one mold insert is withdrawn from the formed casting core in a second direction which differs from the first direction.
  • the second direction is perpendicular to the internal surface which is associated with the turbulators or pins.
  • a plurality of mold inserts are arranged in the mold halves and during demolding of the formed casting core are withdrawn in different directions which differ from the first direction.
  • FIG. 1 shows, in cross section in a greatly simplified view, an exemplary embodiment of a gas turbine blade according to the invention.
  • the blade 10 has an airfoil profile with a leading edge 11 , a trailing edge 12 and also a (convex) suction side 13 and a (concave) pressure side 14 .
  • the blade 10 has a wall 15 which encloses a hollow cavity 16 which is used for the guiding of cooling air which inter alia can discharge into the outside space from cooling air outlets 17 which are provided at the trailing edge 12 .
  • the cavity 16 can be divided into a plurality of sub-chambers by means of one or more ribs 29 .
  • a casting core 21 ( FIG. 2 ), which has to be produced in advance, is required when producing the blade 10 by a casting technique.
  • a core mold 23 according to the type shown in FIG. 3 , which is assembled from two mold halves 23 a and 23 b which can separated along a parting plane 25 and which during demolding are drawn apart in the direction which is indicated by the arrows in FIG. 3 .
  • the orientation of specific elements in the cavity 16 of the blade is also indirectly determined via the casting core 21 .
  • the rib 29 in the cavity 16 of the blade extends inevitably in the demolding direction because the mold halves 23 a and 23 b with their corresponding rib elements 30 can only be withdrawn from the finished casting core in this way.
  • additional elements 18 in the cavity which can be formed as (round) pins or (rib-like) turbulators and improve the transfer of heat between the cooling air which flows in the cavity 16 and the wall 15 , are now arranged or formed in the trailing edge region of the blade 10 .
  • the direction in which the elements 18 project from the wall 15 into the cavity 16 should now be able to be selected within an angular range independently of the demolding direction of FIG. 3 , i.e. the orientation of the elements 18 can differ from the orientation of the rib 29 .
  • the elements 18 for fluidic reasons, are intended to be perpendicular to the internal surface 19 or 20 of the wall from which they extend, as is indicated by the right angle in FIG. 1 .
  • the casting core 21 would have to have correspondingly formed and oriented recesses 22 ( FIG. 2 ).
  • corresponding mold elements 26 would have to be arranged on the mold halves 23 a and 23 b for forming the recesses 22 .
  • FIGS. 4 and 5 provision is made for separate mold inserts 27 , 28 for the region in which the elements 18 are to be arranged, which mold inserts are responsible for forming the recesses 22 and can be withdrawn separately from the mold halves 23 a and 23 b.
  • the mold halves 23 a and 23 b during demolding, are first of all drawn apart in the demolding direction (vertically upwards and downwards in FIG. 4 ).
  • the mold inserts 27 and 28 remain on the casting core 21 in this phase. If the mold halves 23 a and 23 b are removed, the mold inserts 27 and 28 can be withdrawn from the casting core in those directions which correspond to the orientation of the elements 18 (inclined arrows in FIG. 4 ). In this way, it is possible within the scope of the customary casting process to create in a simple way elements 18 in the cavity 16 of the blade 10 which are optimized for cooling and the orientation of which differs from the (main) demolding direction of the core mold.

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  • 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)
US12/961,659 2008-06-12 2010-12-07 Blade for a gas turbine and casting technique method for producing same Abandoned US20110236222A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US14/075,555 US20140060766A1 (en) 2008-06-12 2013-11-08 Blade for a gas turbine and casting technique method for producing same

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
CH8982008 2008-06-12
CH00898/08 2008-06-12
PCT/EP2009/056150 WO2009150019A1 (de) 2008-06-12 2009-05-20 Schaufel für eine gasturbine sowie verfahren zum gusstechnischen herstellen einer solchen schaufel

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2009/056150 Continuation WO2009150019A1 (de) 2008-06-12 2009-05-20 Schaufel für eine gasturbine sowie verfahren zum gusstechnischen herstellen einer solchen schaufel

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US14/075,555 Division US20140060766A1 (en) 2008-06-12 2013-11-08 Blade for a gas turbine and casting technique method for producing same

Publications (1)

Publication Number Publication Date
US20110236222A1 true US20110236222A1 (en) 2011-09-29

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US12/961,659 Abandoned US20110236222A1 (en) 2008-06-12 2010-12-07 Blade for a gas turbine and casting technique method for producing same
US14/075,555 Abandoned US20140060766A1 (en) 2008-06-12 2013-11-08 Blade for a gas turbine and casting technique method for producing same

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Country Status (7)

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

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120118524A1 (en) * 2010-10-18 2012-05-17 Fathi Ahmad Core die with variable pins and process for producing a core
US20130291513A1 (en) * 2012-05-04 2013-11-07 General Electric Company Turbomachine component having an internal cavity reactivity neutralizer and method of forming the same
US20160326891A1 (en) * 2013-12-20 2016-11-10 United Technologies Corporation Compliant attachment for an organic matrix composite component
US20170297085A1 (en) * 2014-10-15 2017-10-19 Siemens Aktiengesellschaft Die cast system for forming a component usable in a gas turbine engine

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8353329B2 (en) 2010-05-24 2013-01-15 United Technologies Corporation Ceramic core tapered trip strips
EP2450122A1 (de) * 2010-11-03 2012-05-09 Siemens Aktiengesellschaft Optimierung eines Kernwerkzeugs, Verfahren zur Herstellung eines Kernwerkzeugs und ein Kernwerkzeug
EP2489836A1 (de) 2011-02-21 2012-08-22 Karlsruher Institut für Technologie Kühlbares Bauteil
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
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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US4752186A (en) * 1981-06-26 1988-06-21 United Technologies Corporation Coolable wall configuration
US5716192A (en) * 1996-09-13 1998-02-10 United Technologies Corporation Cooling duct turn geometry for bowed airfoil
US5931638A (en) * 1997-08-07 1999-08-03 United Technologies Corporation Turbomachinery airfoil with optimized heat transfer
US6379118B2 (en) * 2000-01-13 2002-04-30 Alstom (Switzerland) Ltd Cooled blade for a gas turbine
DE10129975A1 (de) * 2000-12-27 2002-07-04 Alstom Switzerland Ltd Giessform für den Kern einer Gasturbinenschaufel oder dergleichen
US20050281674A1 (en) * 2004-06-17 2005-12-22 Siemens Westinghouse Power Corporation Internal cooling system for a turbine blade
US20060239820A1 (en) * 2005-04-04 2006-10-26 Nobuaki Kizuka Member having internal cooling passage
US20060292005A1 (en) * 2005-06-23 2006-12-28 United Technologies Corporation Method for forming turbine blade with angled internal ribs
US20080019840A1 (en) * 2006-07-21 2008-01-24 United Technologies Corporation Serpentine microcircuit vortex turbulatons for blade cooling

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JPH0644508Y2 (ja) * 1989-04-17 1994-11-16 トヨタ自動車株式会社 鋳型構造
JPH03208617A (ja) * 1990-01-12 1991-09-11 Kyokuto Shokai:Kk 一体型玉形弁の製造方法
DE10041505A1 (de) * 1999-12-23 2001-09-06 Alstom Schweiz Ag Baden Werkzeug zur Herstellung von Gusskernen
JP3772620B2 (ja) * 2000-01-12 2006-05-10 日本精工株式会社 組立式カムシャフトに使用するためのカムロブの製造方法
US6974308B2 (en) 2001-11-14 2005-12-13 Honeywell International, Inc. High effectiveness cooled turbine vane or blade
US20110132562A1 (en) * 2009-12-08 2011-06-09 Merrill Gary B Waxless precision casting process

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Publication number Priority date Publication date Assignee Title
US4752186A (en) * 1981-06-26 1988-06-21 United Technologies Corporation Coolable wall configuration
US5716192A (en) * 1996-09-13 1998-02-10 United Technologies Corporation Cooling duct turn geometry for bowed airfoil
US5931638A (en) * 1997-08-07 1999-08-03 United Technologies Corporation Turbomachinery airfoil with optimized heat transfer
US6379118B2 (en) * 2000-01-13 2002-04-30 Alstom (Switzerland) Ltd Cooled blade for a gas turbine
DE10129975A1 (de) * 2000-12-27 2002-07-04 Alstom Switzerland Ltd Giessform für den Kern einer Gasturbinenschaufel oder dergleichen
US20050281674A1 (en) * 2004-06-17 2005-12-22 Siemens Westinghouse Power Corporation Internal cooling system for a turbine blade
US20060239820A1 (en) * 2005-04-04 2006-10-26 Nobuaki Kizuka Member having internal cooling passage
US20060292005A1 (en) * 2005-06-23 2006-12-28 United Technologies Corporation Method for forming turbine blade with angled internal ribs
US20080019840A1 (en) * 2006-07-21 2008-01-24 United Technologies Corporation Serpentine microcircuit vortex turbulatons for blade cooling

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120118524A1 (en) * 2010-10-18 2012-05-17 Fathi Ahmad Core die with variable pins and process for producing a core
US20130291513A1 (en) * 2012-05-04 2013-11-07 General Electric Company Turbomachine component having an internal cavity reactivity neutralizer and method of forming the same
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
US20160326891A1 (en) * 2013-12-20 2016-11-10 United Technologies Corporation Compliant attachment for an organic matrix composite component
US10422234B2 (en) * 2013-12-20 2019-09-24 United Technologies Corporation Compliant attachment for an organic matrix composite component
US20170297085A1 (en) * 2014-10-15 2017-10-19 Siemens Aktiengesellschaft Die cast system for forming a component usable in a gas turbine engine

Also Published As

Publication number Publication date
JP5717627B2 (ja) 2015-05-13
WO2009150019A1 (de) 2009-12-17
JP2011522991A (ja) 2011-08-04
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
EP2300178B1 (de) 2013-06-19
EP2300178A1 (de) 2011-03-30

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Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:MCFEAT, JOSE ANGUISOLA;KRUCKELS, JORG;DUCKERSHOFF, ROLAND;AND OTHERS;SIGNING DATES FROM 20110114 TO 20110606;REEL/FRAME:026438/0667

STCB Information on status: application discontinuation

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