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EP1247602B1 - Procédé pour la fabrication d'une aube de turbine - Google Patents

Procédé pour la fabrication d'une aube de turbine Download PDF

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Publication number
EP1247602B1
EP1247602B1 EP01108480A EP01108480A EP1247602B1 EP 1247602 B1 EP1247602 B1 EP 1247602B1 EP 01108480 A EP01108480 A EP 01108480A EP 01108480 A EP01108480 A EP 01108480A EP 1247602 B1 EP1247602 B1 EP 1247602B1
Authority
EP
European Patent Office
Prior art keywords
blade
spacers
core
turbine blade
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.)
Expired - Lifetime
Application number
EP01108480A
Other languages
German (de)
English (en)
Other versions
EP1247602A1 (fr
Inventor
Winfried Dr. Esser
Michael Haendler
Peter Tiemann
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 DE50113629T priority Critical patent/DE50113629D1/de
Priority to ES01108480T priority patent/ES2301504T3/es
Priority to EP01108480A priority patent/EP1247602B1/fr
Priority to JP2002098225A priority patent/JP2002349285A/ja
Priority to US10/117,633 priority patent/US6739381B2/en
Priority to CNB021054355A priority patent/CN1250361C/zh
Publication of EP1247602A1 publication Critical patent/EP1247602A1/fr
Application granted granted Critical
Publication of EP1247602B1 publication Critical patent/EP1247602B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C21/00—Flasks; Accessories therefor
    • B22C21/12—Accessories
    • B22C21/14—Accessories for reinforcing or securing moulding materials or cores, e.g. gaggers, chaplets, pins, bars
    • Y—GENERAL 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y10T29/49339—Hollow blade

Definitions

  • the invention relates to a method for producing a turbine blade in a hollow profile.
  • Gas turbines are used in many areas to drive generators or work machines.
  • the energy content of a fuel is used to generate a rotational movement of a turbine shaft.
  • the fuel is burned in a combustion chamber, compressed air being supplied by an air compressor.
  • the working medium produced in the combustion chamber by the combustion of the fuel, under high pressure and at high temperature, is guided via a turbine unit arranged downstream of the combustion chambers, where it relaxes to perform its work.
  • the momentum transfer from the working medium required for generating the rotational movement of the turbine shaft is achieved via turbine blades.
  • a number of profiled blades are arranged on the turbine shaft, which are supplemented for guiding the flow medium in the turbine unit by associated with the turbine housing vanes.
  • the turbine blades usually have a profiled airfoil extending along a blade axis.
  • such gas turbines are usually thermodynamic reasons for particularly high outlet temperatures of the off of the combustion chamber and designed in the inflowing into the turbine unit working fluid of about 1200 ° C to about 1300 ° C.
  • the components of the gas turbine in particular the turbine blades, are exposed to comparatively high thermal loads.
  • a high reliability and a long life of the respective components To ensure the affected components are usually designed cooled.
  • the turbine blades are usually formed as a so-called hollow profile.
  • the profiled airfoil has for this purpose in its inner region also referred to as a vane core cavities in which a cooling medium can be performed.
  • a cooling medium can be performed.
  • the coolant channels thus formed, it is thus possible to apply the coolant to the areas of the respective airfoil that are subject to particular thermal stress.
  • a particularly favorable cooling effect and thus a particularly high level of operational reliability can be achieved in that the coolant channels occupy a comparatively large spatial area in the interior of the respective airfoil, and in that the coolant is guided as close as possible to the respective surface exposed to the hot gas.
  • the respective turbine blade can be flowed through in multiple channels, with a plurality of coolant channels, which can be acted upon by coolant and are separated from one another by comparatively thin partitions, being provided in the interior of the blade profile.
  • Such turbine blades are usually made by casting.
  • a mold adapted in its contour to the desired blade profile is poured out with blade material.
  • core elements are arranged during casting in the casting mold, which are removed after the casting process from the blade body, so that the desired for the coolant channels cavities arise.
  • a plurality of in each case form-specific adapted core elements is arranged in the casting mold.
  • core openings remain in the top and bottom of the turbine blade, which can be closed by appropriate measures. This is for example from the EP 1 027 943 A1 It is known to provide a further recess in the turbine blade which completely crosses the core opening originating from the core support. By inserting a closure piece in the recess then the inner opening of the core opening can be completely covered and thus closed. The core opening itself remains free.
  • spacers can additionally be used to position the core elements in the casting mold in order to achieve defined distances between core elements and casting molds for defined wall thicknesses of the turbine blade.
  • These spacers leave when removing the core elements undesirable additional cavities that hinder the actually intended fluidic decoupling of the respective core areas from each other and in particular from the outside of the turbine blade. Therefore, the spacers are usually designed tapered, so as to safely preclude the formation of unacceptably large openings.
  • the spacers are designed such that when casting the turbine blade as possible a continuous, not completely penetrated by the respective spacer surface or partition at the respective location results. Nevertheless, the cast turbine blade usually has weak points at the locations of the spacers which are at least one local one Promote cracking in the area in question. The error or reject rate in the manufacture of the turbine blades is thus comparatively high.
  • the invention is therefore based on the object to provide a method for producing a turbine blade in a hollow profile, with a particularly low error or reject rate is achievable.
  • This object is achieved according to the invention by connecting a first core element via a number of approximately cylindrical spacers to a further core element and / or to a casting mold, wherein the cavities left by the core elements in the casting mold are poured out by blade material, and wherein the after removal the core elements and the spacer in the turbine blade remaining, openings produced by the spacers are closed by plug elements.
  • the invention is based on the consideration that a possible cause of error in the manufacture of the turbine blades just to be seen in those vulnerabilities that arise as a result of the use of tapered spacers in the connection of the core elements.
  • cylindrical spacers are now used instead of conical or tapered spacers. Although these also leave weak points in the material of the cast turbine blade, which can be found without further ado. Contrary to the principle of keeping the weaknesses in the manufacture of the turbine blades particularly small, it is thus provided to make this particularly easy to find at the cost of comparatively larger vulnerabilities. The thus reliably detectable weak points can then be effectively closed by attaching a closure element and in a manner not affecting the subsequent operation of the turbine blade way.
  • the spacers are preferably dimensioned in their longitudinal extent such that their ends protrude beyond the resulting blade profile, so that arise during the casting of the turbine blade in any case through the respective structure completely continuous holes.
  • the plug elements are compressed in an advantageous development after their introduction into the respective opening. By such compression is ensured that the respective Plug element expands in width so that it receives a particularly intimate positive and non-positive connection with the edge of the respective opening. The opening is thus closed particularly effectively.
  • a suitable pin-shaped element can be used in each case.
  • blind rivets or impact pins are used as plug elements.
  • the advantages achieved by the invention are in particular that by the deliberate acceptance of comparatively large openings in the initially cast blade body each caused by the spacers vulnerability in the blade body is clearly identifiable. Hidden vulnerabilities are thus safely avoided.
  • the spacers can also be comparatively large dimensions, so that only a comparatively small number of spacers is required for reliable positioning of the core elements during the casting process. This also reduces the number of total resulting openings or weak points, so that the cost of resealing these vulnerabilities is kept particularly low.
  • the turbine blade 1 comprises an airfoil blade 2 which extends along a blade axis and is also referred to as a blade profile.
  • the airfoil 2 is, as in FIG FIG. 1 can be seen, profiled or curved on its surface, so that a particularly favorable guidance of the gas turbine flowing through the working medium is ensured.
  • the gas turbine is designed for thermodynamic reasons for an outlet temperature of their working medium from the combustion chamber of comparatively high temperatures of for example 1200 ° C to 1300 ° C.
  • the turbine blade 1 is designed to be coolable in addition to other components.
  • the blade 2 includes a number of integrated cavities 4, 6, each serving as a flow channel for a coolant.
  • the cavities 4 have a comparatively large cross-section and serve as the main flow path for the coolant.
  • a comparatively large wall thickness of the remaining structural parts of the turbine blade 1 is required for mechanical stabilization.
  • a casting mold which has a cavity adapted to the desired outer contour of the turbine blade 1.
  • 6 are in this mold in its outer contour to the desired cavities 4 and 6 adapted so-called core elements positioned.
  • the casting mold is poured out with blade material, wherein the intended cavities 4 and 6 are kept free of blade material by the core elements.
  • the core elements are removed again, so that the desired cavities 4 and 6 remain in the cast turbine blade 1.
  • the core element 10 comprises a base plate 12 which is adapted in shape to the contour desired for the respective cavity 6.
  • a number of spacers 14 are also arranged on the base plate 12.
  • Each spacer 14 is designed substantially cylindrical and formed in its length such that it completely penetrates the provided in its space area blade profile. In the embodiment, the spacers 14 are thus formed in their length so that it exceeds the thickness of the respective cavity 6 surrounding material walls. With their free ends, the spacers 14 are each in the mold or in an adjacent Core element anchored, so that there is a substantially stable structure during the casting process.
  • the thus cast blade body at those locations where the spacers 14 were located through openings. These are thus easily recognizable and can thus be subjected to further treatment.
  • the openings remaining after the removal of the core elements and the spacers in the turbine blade 1, generated by the spacers 14 are thereby closed by suitable plug elements, as for some different types of plug elements in FIG. 3 is shown.
  • FIG. 3 shows in the manner of several alternative embodiments, a number of different types of plug elements, with which the openings left by the spacers 14 may be closed.
  • a Einschlagpin 20 may be provided as a plug element for the respective opening, which includes a conically shaped fitting 22 in its center region in the manner of a barb.
  • a one-sided compressed impact pin 24 which is particularly suitable in the event that the opening to be closed on one side still the actual opening channel limiting projections 26 has.
  • a continuous pin 28 may be provided, which has been compressed on both sides after its penetration into the respective opening. Just by the compression occurs here as a result of the self-adjusting thickening in the central region of the pin 28 a particularly good sealing effect.
  • a pin 30 inserted in a continuous opening, the respective opening having bevels in its end regions. In a compression of the pin 30, this is deformed in its end regions, with its pin material in the corresponding Bevels of the respective openings inserts. Furthermore, the use of a pin 32 is possible, which is sealed in its end by attaching a soldering cap 34 and then soldering.

Landscapes

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

Claims (5)

  1. Procédé de fabrication d'une aube (1) de turbine en profil creux, dans lequel on assemble un premier élément (10) de noyau par un certain nombre d'entretoises (14) à peu près cylindriques à un autre élément de noyau et/ou à une lingotière de coulée, les cavités (4, 6) laissées par les éléments (10) de noyau dans la lingotière de coulée étant remplies par coulée de matériau d'aube et dans lequel on ferme par des éléments de bouchage les ouvertures restant dans l'aube (1) de turbine, après l'enlèvement des éléments (10) de noyau et des entretoises (14), et produites par les entretoises (14).
  2. Procédé suivant la revendication 1, dans lequel on refoule les éléments de bouchage après leur introduction dans l'ouverture respective.
  3. Procédé suivant la revendication 1 ou 2, dans lequel on brase les éléments de bouchage après leur introduction dans l'ouverture respective.
  4. Procédé suivant l'une des revendications 1 à 3, dans lequel on utilise comme élément de bouchage des rivets aveugles.
  5. Procédé suivant l'une des revendications 1 à 3, dans lequel on utilise comme élément de bouchage des chevilles (24) à enfoncer.
EP01108480A 2001-04-04 2001-04-04 Procédé pour la fabrication d'une aube de turbine Expired - Lifetime EP1247602B1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
DE50113629T DE50113629D1 (de) 2001-04-04 2001-04-04 Verfahren zur Herstellung einer Turbinenschaufel
ES01108480T ES2301504T3 (es) 2001-04-04 2001-04-04 Procedimiento para producir un alabe de turbina.
EP01108480A EP1247602B1 (fr) 2001-04-04 2001-04-04 Procédé pour la fabrication d'une aube de turbine
JP2002098225A JP2002349285A (ja) 2001-04-04 2002-04-01 タービン翼の製造方法
US10/117,633 US6739381B2 (en) 2001-04-04 2002-04-04 Method of producing a turbine blade
CNB021054355A CN1250361C (zh) 2001-04-04 2002-04-04 制造涡轮机叶片的方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01108480A EP1247602B1 (fr) 2001-04-04 2001-04-04 Procédé pour la fabrication d'une aube de turbine

Publications (2)

Publication Number Publication Date
EP1247602A1 EP1247602A1 (fr) 2002-10-09
EP1247602B1 true EP1247602B1 (fr) 2008-02-20

Family

ID=8177048

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01108480A Expired - Lifetime EP1247602B1 (fr) 2001-04-04 2001-04-04 Procédé pour la fabrication d'une aube de turbine

Country Status (6)

Country Link
US (1) US6739381B2 (fr)
EP (1) EP1247602B1 (fr)
JP (1) JP2002349285A (fr)
CN (1) CN1250361C (fr)
DE (1) DE50113629D1 (fr)
ES (1) ES2301504T3 (fr)

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Publication number Priority date Publication date Assignee Title
KR100406630B1 (ko) * 2001-03-13 2003-11-20 엘지전자 주식회사 데모용 데이터의 기록 및 재생방법과, 그에 따른 기록매체
DE10255346A1 (de) * 2002-11-28 2004-06-09 Alstom Technology Ltd Verfahren zum Herstellen einer Turbinenschaufel
US8137611B2 (en) * 2005-03-17 2012-03-20 Siemens Energy, Inc. Processing method for solid core ceramic matrix composite airfoil
US7306026B2 (en) * 2005-09-01 2007-12-11 United Technologies Corporation Cooled turbine airfoils and methods of manufacture
GB2430170B (en) * 2005-09-15 2008-05-07 Rolls Royce Plc Method of forming a cast component
CN100398232C (zh) * 2005-11-01 2008-07-02 中国科学院金属研究所 一种具有双晶组织结构的整体涡轮的制备工艺
US20080005903A1 (en) * 2006-07-05 2008-01-10 United Technologies Corporation External datum system and film hole positioning using core locating holes
US7967555B2 (en) * 2006-12-14 2011-06-28 United Technologies Corporation Process to cast seal slots in turbine vane shrouds
US7674093B2 (en) * 2006-12-19 2010-03-09 General Electric Company Cluster bridged casting core
US8366383B2 (en) * 2007-11-13 2013-02-05 United Technologies Corporation Air sealing element
US8083489B2 (en) * 2009-04-16 2011-12-27 United Technologies Corporation Hybrid structure fan blade
US8727714B2 (en) * 2011-04-27 2014-05-20 Siemens Energy, Inc. Method of forming a multi-panel outer wall of a component for use in a gas turbine engine
US10300526B2 (en) 2014-02-28 2019-05-28 United Technologies Corporation Core assembly including studded spacer
US10099275B2 (en) 2014-04-07 2018-10-16 United Technologies Corporation Rib bumper system
US10053989B2 (en) * 2015-12-21 2018-08-21 General Electric Company Cooling circuit for a multi-wall blade
US10119405B2 (en) * 2015-12-21 2018-11-06 General Electric Company Cooling circuit for a multi-wall blade
US20180238175A1 (en) * 2017-02-21 2018-08-23 General Electric Company Method and Device for Retaining Position of a Consumable Core
US11572796B2 (en) 2020-04-17 2023-02-07 Raytheon Technologies Corporation Multi-material vane for a gas turbine engine
US11795831B2 (en) 2020-04-17 2023-10-24 Rtx Corporation Multi-material vane for a gas turbine engine
US11945025B1 (en) 2023-04-06 2024-04-02 Rtx Corporation Method of wall control in multi-wall investment casting

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US2821323A (en) * 1955-12-07 1958-01-28 Lee Co Pin plug
US3761201A (en) * 1969-04-23 1973-09-25 Avco Corp Hollow turbine blade having diffusion bonded therein
US5111570A (en) * 1990-08-10 1992-05-12 United Technologies Corporation Forge joining repair technique
FR2695163B1 (fr) * 1992-09-02 1994-10-28 Snecma Aube creuse pour turbomachine et son procédé de fabrication.
DE4434139C1 (de) * 1994-09-24 1995-08-31 Ford Werke Ag Gußteilform mit Gießkernabstützung und Gußteil mit Kernöffnungsverschluß
DE19821770C1 (de) * 1998-05-14 1999-04-15 Siemens Ag Verfahren und Vorrichtung zur Herstellung eines metallischen Hohlkörpers
JP2000265802A (ja) * 1999-01-25 2000-09-26 General Electric Co <Ge> ガスタービン動翼冷却通路連絡路
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US6370752B1 (en) * 2000-04-21 2002-04-16 General Electric Company Method for repositioning or repairing holes

Also Published As

Publication number Publication date
CN1378890A (zh) 2002-11-13
ES2301504T3 (es) 2008-07-01
US20020157251A1 (en) 2002-10-31
DE50113629D1 (de) 2008-04-03
JP2002349285A (ja) 2002-12-04
CN1250361C (zh) 2006-04-12
US6739381B2 (en) 2004-05-25
EP1247602A1 (fr) 2002-10-09

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