EP1201879A3 - Cooled component, casting core and method for the manufacture of the same - Google Patents

Cooled component, casting core and method for the manufacture of the same Download PDF

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Publication number
EP1201879A3
EP1201879A3 EP01123193A EP01123193A EP1201879A3 EP 1201879 A3 EP1201879 A3 EP 1201879A3 EP 01123193 A EP01123193 A EP 01123193A EP 01123193 A EP01123193 A EP 01123193A EP 1201879 A3 EP1201879 A3 EP 1201879A3
Authority
EP
European Patent Office
Prior art keywords
cooling channel
component
coolant
manufacture
same
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.)
Granted
Application number
EP01123193A
Other languages
German (de)
French (fr)
Other versions
EP1201879B1 (en
EP1201879A2 (en
Inventor
Hartmut Haehnle
Ibrahim Dr. El-Nashar
Rudolf Dr. Kellerer
Beat Von Arx
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 Schweiz 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 Schweiz AG filed Critical Alstom Schweiz AG
Publication of EP1201879A2 publication Critical patent/EP1201879A2/en
Publication of EP1201879A3 publication Critical patent/EP1201879A3/en
Application granted granted Critical
Publication of EP1201879B1 publication Critical patent/EP1201879B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/22—Moulds for peculiarly-shaped castings
    • B22C9/24—Moulds for peculiarly-shaped castings for hollow articles
    • 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
    • Y10T29/49341—Hollow blade with cooling passage

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)

Abstract

Ein gekühltes Bauteil, insbesondere Turbinenschaufel (10, 10'), für Gasturbinen, weist zur effizienten Innenkühlung einen innenliegenden Kühlkanal (16) mit rundem Kanalquerschnitt auf, in welchen Kühlkanal (16) zur Ausbildung eines Kühlmittelwirbels eine Reihe von in Richtung der Längsachse des Kühlkanals (16) übereinander angeordneten, von einem gemeinsamen Kühlmittelkanal (15) ausgehenden Anspeisebohrungen (17) für das Kühlmittel im wesentlichen tangential einmünden.A cooled component, in particular turbine blade (10, 10 '), for gas turbines, has an internal cooling channel (16) with round for efficient internal cooling Channel cross-section, in which cooling channel (16) for forming a coolant vortex a series of in the direction of the longitudinal axis of the cooling channel (16) arranged one above the other, starting from a common coolant channel (15) Feed bores (17) for the coolant substantially tangential open out.

Bei einem solchen Bauteil wird die Herstellbarkeit dadurch verbessert, dass die Anspeisebohrungen (17) überwiegend einen Bohrungsdurchmesser aufweisen, der kleiner ist als der halbe hydraulische Durchmesser des Kühlkanals (16), und dass zur Verbesserung der Ausbringungsrate beim Giessen des Bauteils (10') ausgewählte Anspeisebohrungen (25,..,27) einen Bohrungsdurchmesser aufweisen, der grösser ist als der halbe hydraulische Durchmesser des Kühlkanals (16).

Figure 00000001
In such a component, manufacturability is improved in that the feed bores (17) predominantly have a bore diameter smaller than half the hydraulic diameter of the cooling channel (16), and that for improving the rate of application during casting of the component (10 ') selected Anspeisebohrungen (25, .., 27) have a bore diameter which is greater than half the hydraulic diameter of the cooling channel (16).
Figure 00000001
EP01123193A 2000-10-27 2001-09-28 Cooled component, casting core and method for the manufacture of the same Expired - Lifetime EP1201879B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10053356A DE10053356A1 (en) 2000-10-27 2000-10-27 Cooled component, casting core for the production of such a component, and method for producing such a component
DE10053356 2000-10-27

Publications (3)

Publication Number Publication Date
EP1201879A2 EP1201879A2 (en) 2002-05-02
EP1201879A3 true EP1201879A3 (en) 2003-07-16
EP1201879B1 EP1201879B1 (en) 2004-11-10

Family

ID=7661311

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01123193A Expired - Lifetime EP1201879B1 (en) 2000-10-27 2001-09-28 Cooled component, casting core and method for the manufacture of the same

Country Status (3)

Country Link
US (1) US6547525B2 (en)
EP (1) EP1201879B1 (en)
DE (2) DE10053356A1 (en)

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1529580B1 (en) 2003-10-29 2009-01-07 Siemens Aktiengesellschaft Casting mould
US7128533B2 (en) * 2004-09-10 2006-10-31 Siemens Power Generation, Inc. Vortex cooling system for a turbine blade
US7690894B1 (en) 2006-09-25 2010-04-06 Florida Turbine Technologies, Inc. Ceramic core assembly for serpentine flow circuit in a turbine blade
WO2011019672A2 (en) * 2009-08-09 2011-02-17 Rolls-Royce Corporation Support for a fired article
GB0921818D0 (en) * 2009-12-15 2010-01-27 Rolls Royce Plc Casting of internal features within a product (
DE102010046331A1 (en) 2010-09-23 2012-03-29 Rolls-Royce Deutschland Ltd & Co Kg Cooled turbine blades for a gas turbine engine
DE102012017491A1 (en) 2012-09-04 2014-03-06 Rolls-Royce Deutschland Ltd & Co Kg Turbine blade of a gas turbine with swirl-generating element
WO2014137470A1 (en) 2013-03-05 2014-09-12 Vandervaart Peter L Gas turbine engine component arrangement
WO2014163698A1 (en) 2013-03-07 2014-10-09 Vandervaart Peter L Cooled gas turbine engine component
US10012090B2 (en) * 2014-07-25 2018-07-03 United Technologies Corporation Airfoil cooling apparatus
FR3025444B1 (en) 2014-09-04 2016-09-23 Snecma PROCESS FOR PRODUCING A CERAMIC CORE
US9988912B2 (en) * 2015-05-08 2018-06-05 United Technologies Corporation Thermal regulation channels for turbomachine components
US10301946B2 (en) 2016-10-26 2019-05-28 General Electric Company Partially wrapped trailing edge cooling circuits with pressure side impingements
US10450950B2 (en) 2016-10-26 2019-10-22 General Electric Company Turbomachine blade with trailing edge cooling circuit
US10352176B2 (en) 2016-10-26 2019-07-16 General Electric Company Cooling circuits for a multi-wall blade
US10450875B2 (en) 2016-10-26 2019-10-22 General Electric Company Varying geometries for cooling circuits of turbine blades
US10273810B2 (en) 2016-10-26 2019-04-30 General Electric Company Partially wrapped trailing edge cooling circuit with pressure side serpentine cavities
US10309227B2 (en) 2016-10-26 2019-06-04 General Electric Company Multi-turn cooling circuits for turbine blades
US10465521B2 (en) 2016-10-26 2019-11-05 General Electric Company Turbine airfoil coolant passage created in cover
US10598028B2 (en) 2016-10-26 2020-03-24 General Electric Company Edge coupon including cooling circuit for airfoil
US10240465B2 (en) * 2016-10-26 2019-03-26 General Electric Company Cooling circuits for a multi-wall blade
EP3832069A1 (en) 2019-12-06 2021-06-09 Siemens Aktiengesellschaft Turbine blade for a stationary gas turbine
US11814965B2 (en) 2021-11-10 2023-11-14 General Electric Company Turbomachine blade trailing edge cooling circuit with turn passage having set of obstructions
CN114109518A (en) * 2021-11-29 2022-03-01 西安交通大学 Turbine blade leading edge ribbed rotational flow-air film composite cooling structure
CN114215607A (en) * 2021-11-29 2022-03-22 西安交通大学 Turbine blade leading edge rotational flow cooling structure
CN114412577B (en) * 2022-01-24 2024-03-15 杭州汽轮动力集团股份有限公司 Turbine moving blade

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4669957A (en) * 1985-12-23 1987-06-02 United Technologies Corporation Film coolant passage with swirl diffuser
US5603606A (en) * 1994-11-14 1997-02-18 Solar Turbines Incorporated Turbine cooling system
EP0892151A1 (en) * 1997-07-15 1999-01-20 Asea Brown Boveri AG Cooling system for the leading edge of a hollow blade for gas turbine
US6033181A (en) * 1997-09-01 2000-03-07 Asea Brown Boveri Ag Turbine blade of a gas turbine

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB893706A (en) * 1960-01-05 1962-04-11 Rolls Royce Blades for fluid flow machines
US3542486A (en) * 1968-09-27 1970-11-24 Gen Electric Film cooling of structural members in gas turbine engines
JPS5540221A (en) 1978-09-14 1980-03-21 Hitachi Ltd Cooling structure of gas turbin blade
FR2516165B1 (en) * 1981-11-10 1986-07-04 Snecma GAS TURBINE BLADE WITH FLUID CIRCULATION COOLING CHAMBER AND METHOD FOR PRODUCING THE SAME
GB2202907A (en) 1987-03-26 1988-10-05 Secr Defence Cooled aerofoil components
US5002460A (en) 1989-10-02 1991-03-26 General Electric Company Internally cooled airfoil blade
US5498133A (en) * 1995-06-06 1996-03-12 General Electric Company Pressure regulated film cooling

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4669957A (en) * 1985-12-23 1987-06-02 United Technologies Corporation Film coolant passage with swirl diffuser
US5603606A (en) * 1994-11-14 1997-02-18 Solar Turbines Incorporated Turbine cooling system
EP0892151A1 (en) * 1997-07-15 1999-01-20 Asea Brown Boveri AG Cooling system for the leading edge of a hollow blade for gas turbine
US6033181A (en) * 1997-09-01 2000-03-07 Asea Brown Boveri Ag Turbine blade of a gas turbine

Also Published As

Publication number Publication date
US20020051706A1 (en) 2002-05-02
EP1201879B1 (en) 2004-11-10
EP1201879A2 (en) 2002-05-02
DE50104476D1 (en) 2004-12-16
DE10053356A1 (en) 2002-05-08
US6547525B2 (en) 2003-04-15

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