WO2010086402A2 - Procédé de production d'un élément de turbine à gaz - Google Patents

Procédé de production d'un élément de turbine à gaz Download PDF

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Publication number
WO2010086402A2
WO2010086402A2 PCT/EP2010/051074 EP2010051074W WO2010086402A2 WO 2010086402 A2 WO2010086402 A2 WO 2010086402A2 EP 2010051074 W EP2010051074 W EP 2010051074W WO 2010086402 A2 WO2010086402 A2 WO 2010086402A2
Authority
WO
WIPO (PCT)
Prior art keywords
cooling
platform
supply channels
component
gas turbine
Prior art date
Application number
PCT/EP2010/051074
Other languages
German (de)
English (en)
Other versions
WO2010086402A3 (fr
Inventor
Thomas Heinz-Schwarzmaier
Jörg KRÜCKELS
Brian Kenneth Wardle
Original Assignee
Alstom Technology Ltd.
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 Ltd. filed Critical Alstom Technology Ltd.
Publication of WO2010086402A2 publication Critical patent/WO2010086402A2/fr
Publication of WO2010086402A3 publication Critical patent/WO2010086402A3/fr

Links

Classifications

    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the present invention relates to the field of gas turbines. It relates to a method for producing a component of a gas turbine according to the preamble of claim 1.
  • Gas turbines are designed to increase the efficiency for ever higher operating temperatures. Particularly exposed to thermal stresses are mainly the components or components in the combustion chamber and the running and vanes of the following turbine including the other, the hot gas channel limiting elements. The occurring thermal loads can be effectively countered if, on the one hand, particularly resistant materials, such as Nickel-based alloys are used. On the other hand, additional measures must be taken to cool the components, wherein different cooling methods, such as. the film cooling or the impingement cooling, find application.
  • a plate-shaped, projecting component portion of a gas turbine is known, one side of which is acted upon by the hot gas of the gas turbine, and in the plate plane of cooling supply channels is interspersed (Fig. 1 and 2 of the document), which emanating a larger plenum inside the component and be supplied with cooling air, and of which depart from a plurality of cooling holes, which open at the surface of the component portion in the outer space and is blown off by the cooling air for film cooling of the surface to the outside.
  • the component is a guide vane of a gas turbine and the component portion is formed on the blade, the hot gas channel of the turbine limiting platform.
  • FIG. 1 of the present application A corresponding component configuration is shown in Fig. 1 of the present application:
  • the vane 10 of FIG. 1, which is only partially shown, comprises an airfoil 1 1, which at one end in a transverse to
  • Blade longitudinal direction oriented platform 12 passes. When installed, the top of this platform 12 is acted upon by the hot gas of the turbine, which flows in the direction of the arrow from a front edge 13 of the blade on the blade 1 1 along to a trailing edge 14.
  • the platform 12 is cooled in the example of FIG. 1 predominantly by a film cooling in which distributed over the loaded surface of the platform 12 cooling air is blown to the outside and forms a cooling film on the surface.
  • a film cooling in which distributed over the loaded surface of the platform 12 cooling air is blown to the outside and forms a cooling film on the surface.
  • a plurality of rows of obliquely extending cooling holes 17 are provided, the outlets 18 are arranged on the surface of the platform 12.
  • the cooling bores 17 are supplied in rows by means of cooling supply channels 15 extending transversely thereto (indicated by dashed lines in FIG. 1) with pressurized cooling air which is taken from a plenum, not shown in FIG. 1, located in the interior of the blade.
  • the cooling supply channels 15 are subsequently introduced by a spark erosion process (EDM or Electrical Discharge Machining) in the finished casting.
  • EDM Electrical Discharge Machining
  • the invention aims to remedy this situation. It is therefore an object of the invention to provide a method for producing a cooled component mentioned at the outset
  • Essential for the invention is that not only the component in its basic configuration, but also the cooling supply channels are produced by casting.
  • the cooling supply channels are produced directly in terms of casting technology in their final geometry.
  • the cooling supply channels are first manufactured by casting with a smaller cross-section and then brought by machining with a tool to its final cross-sectional geometry. In the latter case, corrections can be made and precise adjustments made to the cooling air flows.
  • the component manufactured according to this method is a gas turbine stator vane equipped with a platform.
  • the component may also be a heat shield of the gas turbine equipped with a platform.
  • FIG. 1 in perspective view a section of an exemplary
  • FIG. 2 is a plan view from above of the guide blade of FIG. 1, in which the cooling supply ducts according to the invention are produced by casting using corresponding core sections;
  • FIG. 2 is a plan view from above of the guide blade of FIG. 1, in which the cooling supply ducts according to the invention are produced by casting using corresponding core sections;
  • Fig. 3 shows schematically the subsequent mechanical post-processing of the casting technology produced cooling supply channels according to an embodiment of the invention
  • FIG 4 shows an illustration of an integral cooling of the guide blade with the integration of the cooling supply channels focused in the preceding figures.
  • the Guide vane 10 of a gas turbine are explained, as it has already been described.
  • Essential for the cooling of the platform 12 of the Guide vane 10 are extending in the platform 12 cooling supply channels 15 through which cooling air is led to the cooling holes necessary for the film cooling during operation.
  • the cooling supply channels 15 may be laterally open, as shown in Fig. 1. But they can also be closed at the ends later, if a cooling connection with adjacent components is not desirable.
  • cooling supply channels 15 are now produced by casting in accordance with the invention in their basic configuration, in which the core, which is in any case required to form the cavities in the interior of the blade, is widened by the core sections 16 indicated hatched in FIG.
  • cooling supply channels 15a are thereby produced whose diameter d1 or their cross-sectional areas already have the final dimension, and therefore do not have to be further processed. In this way, a considerable amount of time and work can be avoided, with a subsequent
  • cooling supply channels eg., By EDM
  • FIG. 4 shows an integral cooling of the vane, with the inclusion of the specially produced cooling supply ducts, as described in the preceding figures.
  • the platform 12 is subjected to a baffle cooling.
  • a gap 21 is provided, and formed by a plate 20, the holes 23 is penetrated, which are configured suitable for an impact cooling 22.
  • the impinging on the platform 12 cooling air jets are shown in the sense of an ongoing impact cooling. Thereafter, this cooling air flows (see arrow) through the already mentioned cooling supply channels 15, which are laterally formed with a closure 24.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un procédé de production d'un élément (10) de turbine à gaz. Cet élément (10) présente une plate-forme (12) exposée au gaz chaud de la turbine à gaz et fortement sollicitée thermiquement à travers laquelle s'étendent des conduits d'alimentation en air de refroidissement (15) qui se situent dans le plan de la plate-forme et qui servent à alimenter des orifices de refroidissement (17) débouchant dans une sortie (18) sur une surface de la plate-forme (12) et servant au refroidissement par film de la surface de la plate-forme. Selon le procédé de l'invention, l'élément (10) est produit par coulée. Le procédé selon l'invention simplifie significativement l'usinage grâce au fait que les conduits d'alimentation en air de refroidissement (15) sont également produits par coulée.
PCT/EP2010/051074 2009-01-30 2010-01-29 Procédé de production d'un élément de turbine à gaz WO2010086402A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH00141/09A CH700320A1 (de) 2009-01-30 2009-01-30 Verfahren zum herstellen eines bauteils einer gasturbine.
CH00141/09 2009-01-30

Publications (2)

Publication Number Publication Date
WO2010086402A2 true WO2010086402A2 (fr) 2010-08-05
WO2010086402A3 WO2010086402A3 (fr) 2010-10-21

Family

ID=40637816

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2010/051074 WO2010086402A2 (fr) 2009-01-30 2010-01-29 Procédé de production d'un élément de turbine à gaz

Country Status (2)

Country Link
CH (1) CH700320A1 (fr)
WO (1) WO2010086402A2 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2698501A1 (fr) * 2011-04-14 2014-02-19 Mitsubishi Heavy Industries, Ltd. Aube de turbine à gaz, et turbine à gaz
EP2436882A3 (fr) * 2010-09-30 2014-02-26 Rolls-Royce plc Pale de rotor refroidie

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1138878A2 (fr) 2000-03-31 2001-10-04 ALSTOM Power N.V. Elément saillant, plat pour turbine à gaz

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5197852A (en) * 1990-05-31 1993-03-30 General Electric Company Nozzle band overhang cooling
US6210111B1 (en) * 1998-12-21 2001-04-03 United Technologies Corporation Turbine blade with platform cooling
US6254333B1 (en) * 1999-08-02 2001-07-03 United Technologies Corporation Method for forming a cooling passage and for cooling a turbine section of a rotary machine
JP2005513329A (ja) * 2001-12-13 2005-05-12 アルストム テクノロジー リミテッド タービンエンジンの構成部品用密閉構造体
US6668906B2 (en) * 2002-04-29 2003-12-30 United Technologies Corporation Shaped core for cast cooling passages and enhanced part definition
US6945749B2 (en) * 2003-09-12 2005-09-20 Siemens Westinghouse Power Corporation Turbine blade platform cooling system
DE50311059D1 (de) * 2003-10-29 2009-02-26 Siemens Ag Gussform
US6887033B1 (en) * 2003-11-10 2005-05-03 General Electric Company Cooling system for nozzle segment platform edges
US7255536B2 (en) * 2005-05-23 2007-08-14 United Technologies Corporation Turbine airfoil platform cooling circuit
US7309212B2 (en) * 2005-11-21 2007-12-18 General Electric Company Gas turbine bucket with cooled platform leading edge and method of cooling platform leading edge

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1138878A2 (fr) 2000-03-31 2001-10-04 ALSTOM Power N.V. Elément saillant, plat pour turbine à gaz

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2436882A3 (fr) * 2010-09-30 2014-02-26 Rolls-Royce plc Pale de rotor refroidie
US9074484B2 (en) 2010-09-30 2015-07-07 Rolls-Royce Plc Cooled rotor blade
EP2698501A1 (fr) * 2011-04-14 2014-02-19 Mitsubishi Heavy Industries, Ltd. Aube de turbine à gaz, et turbine à gaz
EP2698501A4 (fr) * 2011-04-14 2014-09-03 Mitsubishi Heavy Ind Ltd Aube de turbine à gaz, et turbine à gaz
US9085987B2 (en) 2011-04-14 2015-07-21 Mitsubishi Heavy Industries, Ltd. Turbine blade and gas turbine

Also Published As

Publication number Publication date
WO2010086402A3 (fr) 2010-10-21
CH700320A1 (de) 2010-07-30

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