EP2243574A1 - Giessvorrichtung zum Herstellen einer Turbinenlaufschaufel einer Gasturbine und Turbinenlaufschaufel - Google Patents

Giessvorrichtung zum Herstellen einer Turbinenlaufschaufel einer Gasturbine und Turbinenlaufschaufel Download PDF

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Publication number
EP2243574A1
EP2243574A1 EP09005533A EP09005533A EP2243574A1 EP 2243574 A1 EP2243574 A1 EP 2243574A1 EP 09005533 A EP09005533 A EP 09005533A EP 09005533 A EP09005533 A EP 09005533A EP 2243574 A1 EP2243574 A1 EP 2243574A1
Authority
EP
European Patent Office
Prior art keywords
casting
turbine blade
blade
inlet channel
turbine
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.)
Withdrawn
Application number
EP09005533A
Other languages
German (de)
English (en)
French (fr)
Inventor
Fathi Ahmad
Uwe Dr. Paul
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP09005533A priority Critical patent/EP2243574A1/de
Priority to CN2010800275199A priority patent/CN102458715A/zh
Priority to EP10713950A priority patent/EP2421666A1/de
Priority to PCT/EP2010/054930 priority patent/WO2010121939A1/de
Priority to US13/265,185 priority patent/US20120039718A1/en
Publication of EP2243574A1 publication Critical patent/EP2243574A1/de
Withdrawn legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/02—Sand moulds or like moulds for shaped castings
    • B22C9/04—Use of lost patterns
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/08—Features with respect to supply of molten metal, e.g. ingates, circular gates, skim gates
    • B22C9/082—Sprues, pouring cups
    • 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
    • B22C9/108—Installation of cores
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D23/00—Casting processes not provided for in groups B22D1/00 - B22D21/00
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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

Definitions

  • the invention relates to a casting apparatus for producing a turbine blade of a gas turbine according to the preamble of claim 1. Furthermore, the invention relates to a turbine blade according to the preamble of claim 6.
  • Casting devices also called casting devices, for producing a turbine blade of a gas turbine are known from the prior art for the longest time.
  • a casting device comprises a plurality of shell-like arranged mold shells for the simultaneous casting of a plurality of turbine blades.
  • Each mold shell is hollow, wherein the cavity represents the negative mold of the turbine blade to be produced. Since turbine blades, in particular the blades of front turbine stages, usually have to be cooled, these are also hollow.
  • a cooling medium usually cooling air, can be carried out through the cavities of the turbine blade so that the turbine blades have a particularly long service life and do not prematurely suffer thermal damage due to the flow of hot gas past them.
  • the mold shell for producing such a turbine blade generally comprises one or more casting cores, which are arranged in the cavity of the casting apparatus.
  • the casting cores after their removal in the cast turbine blade, leave the cavities through which the coolant flows during operation of the gas turbine.
  • the casting device has at least one inlet channel, usually called feeder, through which the casting material can be fed into the cavity of the shell mold during casting of the blade. Consequently, the inlet channel opens with its inlet opening in the surface that defines the cavity of the mold shell.
  • the object of the invention is therefore to provide a turbine blade with an increased service life and to provide a casting device for producing such a turbine blade.
  • the object directed to the casting device is achieved with a casting device designed according to the features of patent claim 1.
  • the task relating to the turbine blade is achieved with a turbine blade formed according to claim 6.
  • the invention is based on the finding that the formation of cracks during the solidification of the melt in the walls of the cooling channels in the blade-root-side region of the turbine blade is production-related.
  • turbine blades are cast in a standing position by default, with the cavity in the mold shell being formed such that the negative mold of the blade of the turbine blade is formed at the bottom and above that the platform and the blade root.
  • top and bottom refer to the horizontal plane.
  • the feed for the molten casting material is usually also on top, since it has been found to be advantageous Turbine blades are produced in falling casting, in which the place of the last solidification of the casting material is above and thus at the massive blade root.
  • the blade root is usually formed hammer-shaped or fir tree symmetrical, and the cooling channels are usually positioned centrally in the blade root, occurred in the conventional casting always situations in which the inflowing into the cavity of the shell mold liquid casting material transversely applied to the positioned before the inlet opening casting cores .
  • the molten casting material hit the foot area of the centered casting core.
  • the casting cores warmed up more at the point of impact of the hot casting material than in other areas. These hotter core areas are also referred to as hot spots.
  • the other areas of the casting cores were not so extremely heated up.
  • the invention proposes that the feed of hot liquid casting material into the cavity of the mold shell when casting the turbine blade now has to be done so that it does not occur directly on casting cores. According to the casting material is now freely and undisturbed flow into the cavity and on the shell mold bottom, which forms the blade tip impinge.
  • the cast cores are rod-shaped at least in the section of the blade root, their off-center placement in the shell results in the openings of cooling channels in the blade root of the turbine blade also being arranged off-center, relative to the generally symmetrical outer contour of the blade root.
  • the symmetry is here on the in the Cross-section fir-tree-shaped or hammer-shaped contour of the blade base related.
  • the inlet channel opens into that part of the surface of the cavity of the mold shell, which forms the negative of the end face of the blade root of the turbine blade.
  • This makes it possible to form a sufficiently large inlet channel.
  • a falling cast of turbine blades with the blade root on the top makes it possible to cast turbine blades, whose largest-volume area, namely the blade root, finally solidifies. Possibly. Shrinkage of the casting material occurring during solidification can be compensated by the inflow of molten casting material from the casting area. In addition, so that a compact casting device can be specified.
  • the surface of the shell mold for the blade root of the turbine blade on a symmetrical fir-tree or hammer-shaped contour are also arranged centrally and one of the casting cores arranged eccentrically to the symmetry, at least in the region of the inlet opening. Due to the eccentric arrangement of the casting cores and the blade root to be held compactly, it is necessary that the cross-sectional area of the previous casting core is divided into two casting cores. By dividing the previous, centrally placed cooling channels in two parallel eccentrically positioned cooling channels required for the cooling air cross-sectional area can be further maintained, however, the existing cross-sectional area then distributed to the two cooling channels, which then each half of the previous cross-sectional area exhibit. As a result, a prior art cooling channel input becomes two Cooling channel inputs divided at a turbine blade according to the invention.
  • the casting cores furthest away from the inlet opening can also lie in the imaginary extension of the inlet channel in the event that the casting material flowing into the cavity does not reach it.
  • FIG. 1 shows a perspective, schematic representation of a part of a casting apparatus 10 for producing a turbine blade of a gas turbine.
  • the casting apparatus 10 comprises at least one mold shell 12 with a cavity 14.
  • the cavity 14 is delimited by a surface 16, which is the negative mold of the turbine blade to be produced.
  • a total of six casting cores 18 are arranged in the cavity 14 .
  • the casting cores 18 are always arranged in pairs. In total there are three pairs of cores. Of course, a larger or a smaller number of casting core (pairs) may also be present in the shell 12.
  • an inlet channel 20 is provided in the mold shell 12 for the filling of the liquid casting material. Its inlet opening 22 opens in the surface 16, which limits the cavity 14.
  • the cavity 14 is formed in the mold shell 12 such that the negative mold of the airfoil tip of the turbine blade is located at the bottom.
  • the overlying part of the surface forms the negative of the blade.
  • the part of the surface is contoured so that the negative mold of the platform of the turbine blade is formed.
  • the remaining part of the surface 16 forms the contour of the blade root.
  • the inlet channel 20 opens with its inlet opening 22 in that part of the surface which predetermines an end face of the blade root.
  • the inlet channel 20 has a straight line immediately upstream of the inlet opening 22 in the illustrated casting device Longitudinal extent.
  • the longitudinal extent of the inlet channel 20 extends approximately parallel or slightly inclined relative to the horizontal plane.
  • the casting cores 18 are in FIG. 1 not fully illustrated. In FIG. 1 Only those portions of the casting cores 18 are shown, which are arranged in the uppermost part of the cavity 14, which defines the negative shape of the blade root.
  • the shape, contour and type of the casting cores 18 in the platform-side region or in the blade-side region is not of further interest to the invention and can therefore be arbitrarily, for example meander-shaped, rectilinear or even slightly curved.
  • the respective cooling channels can also be partially recombined.
  • Each casting pair of cores 18 are spaced from one another.
  • the existing between them distance A is so large that hot, liquid cast material does not hit directly on the casting cores 18 when filling the cavity 14.
  • the hot casting material fed into the cavity 14 flows between two immediately adjacent casting cores 18. So it should be the contact between inflowing liquid casting material and Gusskernober Design in the foot as possible avoided.
  • casting core areas are avoided with locally elevated temperature.
  • the locally increased core temperature was the cause of prior art cracking phenomena on the walls of cooling passages of turbine blades.
  • the imaginary extension of the longitudinal extent of the inlet channel 20 thus extends into the free area between the two casting cores 18 of a casting core pair.
  • FIG. 1 is the imaginary extension of the inlet channel completely free of casting cores 18.
  • the casting core pair shown in the middle or the casting core pair shown on the left can each also be replaced by a single casting core whose sections arranged in the blade root are positioned in the imaginary extension of the inlet channel 20.
  • FIG. 2 is a perspective view of a turbine blade 30 shown with the casting apparatus according to FIG. 1 was produced.
  • the turbine blade 30 has a blade root 32 contoured in the manner of a fir tree in longitudinal section, on which a platform 34 is arranged.
  • the platform 34 is adjoined by an aerodynamically curved airfoil 36 which terminates at a freestanding airfoil tip 38.
  • the turbine blade 30 thus extends along a longitudinal axis 40 from the blade root 32 to the blade tip 38.
  • the longitudinal axis 40 is arranged such that it extends centrally or symmetrically to the contour of the fir-tree-shaped blade root 32.
  • the blade root 32 has on its side facing away from the blade 36, transversely to the longitudinal axis 40 extending surface 42, also called underside, a plurality of openings 44, which remain when the casting cores 18 have been removed from the cast turbine blade 30.
  • the openings 44 are arranged on both sides of the center of symmetry, which is defined in cross-section by the longitudinal axis 40. They are located in two rows, each with three openings 44.
  • the openings 44 serve to introduce a coolant into the interior of the turbine blade 30.
  • Each opening 44 forms one end of a cooling channel of the turbine blade 30 from. Its course in the interior of the turbine blade 30 is of no importance to the invention.
  • the invention prevents uneven local overheating of the casting cores 18 in the vicinity of the inlet during filling of the cavity 14. At the same time, a better filling can take place since casting cores 18 no longer block the inlet opening 22. A collision of inflowing hot casting material with casting cores 18 is prevented by the use of the invention. In addition, the solidification can be further improved by the unobstructed flow of hot cast material (food) from the feeds, which reduces remaining residual stress or residual stress and avoids the formation of cracks.
  • the invention relates to a casting apparatus 10 for producing a turbine blade 30 of a gas turbine, in which the mold shell 12, its inlet and the casting cores 18 disposed therein are aligned with each other such that a casting material flowing into the cavity 14 of the shell mold 12 does not impinge on casting cores 18 directly.
  • This avoids so-called hotter areas (hot spots) on casting cores 18, which have hitherto been detrimental to the solidification of the casting material.
  • improved solidification of the cast material can thus be achieved, which reduces interference in the structure of the solidified cast material. Due to the reduction or avoidance of the disturbances cracking and crack growth is avoided in the area of the blade root side cooling channel sections, which increases the life of the turbine blade 30.

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)
EP09005533A 2009-04-20 2009-04-20 Giessvorrichtung zum Herstellen einer Turbinenlaufschaufel einer Gasturbine und Turbinenlaufschaufel Withdrawn EP2243574A1 (de)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP09005533A EP2243574A1 (de) 2009-04-20 2009-04-20 Giessvorrichtung zum Herstellen einer Turbinenlaufschaufel einer Gasturbine und Turbinenlaufschaufel
CN2010800275199A CN102458715A (zh) 2009-04-20 2010-04-15 用于制造燃气轮机的涡轮动叶片的浇铸装置和涡轮动叶片
EP10713950A EP2421666A1 (de) 2009-04-20 2010-04-15 Giessvorrichtung zum herstellen einer turbinenlaufschaufel einer gasturbine und turbinenlaufschaufel
PCT/EP2010/054930 WO2010121939A1 (de) 2009-04-20 2010-04-15 Giessvorrichtung zum herstellen einer turbinenlaufschaufel einer gasturbine und turbinenlaufschaufel
US13/265,185 US20120039718A1 (en) 2009-04-20 2010-04-15 Casting apparatus for producing a turbine rotor blade of a gas turbine and turbine rotor blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09005533A EP2243574A1 (de) 2009-04-20 2009-04-20 Giessvorrichtung zum Herstellen einer Turbinenlaufschaufel einer Gasturbine und Turbinenlaufschaufel

Publications (1)

Publication Number Publication Date
EP2243574A1 true EP2243574A1 (de) 2010-10-27

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Family Applications (2)

Application Number Title Priority Date Filing Date
EP09005533A Withdrawn EP2243574A1 (de) 2009-04-20 2009-04-20 Giessvorrichtung zum Herstellen einer Turbinenlaufschaufel einer Gasturbine und Turbinenlaufschaufel
EP10713950A Withdrawn EP2421666A1 (de) 2009-04-20 2010-04-15 Giessvorrichtung zum herstellen einer turbinenlaufschaufel einer gasturbine und turbinenlaufschaufel

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP10713950A Withdrawn EP2421666A1 (de) 2009-04-20 2010-04-15 Giessvorrichtung zum herstellen einer turbinenlaufschaufel einer gasturbine und turbinenlaufschaufel

Country Status (4)

Country Link
US (1) US20120039718A1 (zh)
EP (2) EP2243574A1 (zh)
CN (1) CN102458715A (zh)
WO (1) WO2010121939A1 (zh)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103567450A (zh) * 2013-10-29 2014-02-12 浙江大学 功能梯度材料半固态粉末成形装置
CN113719323A (zh) * 2021-07-09 2021-11-30 北京航空航天大学 一种燃气轮机涡轮叶片复合冷却结构

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010054513A1 (de) * 2010-12-15 2012-06-21 Claas Guss Gmbh Gusskern und Verfahren zur Beeinflussung des Erstarrungsverhaltens eines Gussteils
EP2735387A1 (de) * 2012-11-22 2014-05-28 Siemens Aktiengesellschaft Gussform mit angeschrägten Stirnseiten bei inneren Wänden
CN106890945A (zh) * 2015-12-17 2017-06-27 通用电气公司 模芯组件及熔模铸造方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5465780A (en) * 1993-11-23 1995-11-14 Alliedsignal Inc. Laser machining of ceramic cores
EP1041246A1 (de) * 1999-03-29 2000-10-04 Siemens Aktiengesellschaft Kühlmitteldurchströmte, gegossene Gasturbinenschaufel sowie Vorrichtung und Verfahren zur Herstellung eines Verteilerraums der Gasturbinenschaufel
EP1621725A1 (en) * 2004-07-30 2006-02-01 General Electric Company Turbine rotor blade and gas turbine engine rotor assembly comprising such blades
WO2007012590A1 (de) * 2005-07-25 2007-02-01 Siemens Aktiengesellschaft Gekühlte turbinenschaufel für eine gasturbine und verwendung einer solchen turbinenschaufel

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3204303A (en) * 1963-06-20 1965-09-07 Thompson Ramo Wooldridge Inc Precision investment casting
US5820774A (en) * 1996-10-28 1998-10-13 United Technologies Corporation Ceramic core for casting a turbine blade
US7413403B2 (en) * 2005-12-22 2008-08-19 United Technologies Corporation Turbine blade tip cooling
US7695246B2 (en) * 2006-01-31 2010-04-13 United Technologies Corporation Microcircuits for small engines

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5465780A (en) * 1993-11-23 1995-11-14 Alliedsignal Inc. Laser machining of ceramic cores
EP1041246A1 (de) * 1999-03-29 2000-10-04 Siemens Aktiengesellschaft Kühlmitteldurchströmte, gegossene Gasturbinenschaufel sowie Vorrichtung und Verfahren zur Herstellung eines Verteilerraums der Gasturbinenschaufel
EP1621725A1 (en) * 2004-07-30 2006-02-01 General Electric Company Turbine rotor blade and gas turbine engine rotor assembly comprising such blades
WO2007012590A1 (de) * 2005-07-25 2007-02-01 Siemens Aktiengesellschaft Gekühlte turbinenschaufel für eine gasturbine und verwendung einer solchen turbinenschaufel

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103567450A (zh) * 2013-10-29 2014-02-12 浙江大学 功能梯度材料半固态粉末成形装置
CN103567450B (zh) * 2013-10-29 2015-05-20 浙江大学 功能梯度材料半固态粉末成形装置
CN113719323A (zh) * 2021-07-09 2021-11-30 北京航空航天大学 一种燃气轮机涡轮叶片复合冷却结构
CN113719323B (zh) * 2021-07-09 2022-05-17 北京航空航天大学 一种燃气轮机涡轮叶片复合冷却结构

Also Published As

Publication number Publication date
WO2010121939A1 (de) 2010-10-28
CN102458715A (zh) 2012-05-16
EP2421666A1 (de) 2012-02-29
US20120039718A1 (en) 2012-02-16

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