EP2031185A3 - Multi-part cast turbine engine component having an internal cooling channel and method of forming a multi-part cast turbine engine component - Google Patents

Multi-part cast turbine engine component having an internal cooling channel and method of forming a multi-part cast turbine engine component Download PDF

Info

Publication number
EP2031185A3
EP2031185A3 EP08162441A EP08162441A EP2031185A3 EP 2031185 A3 EP2031185 A3 EP 2031185A3 EP 08162441 A EP08162441 A EP 08162441A EP 08162441 A EP08162441 A EP 08162441A EP 2031185 A3 EP2031185 A3 EP 2031185A3
Authority
EP
European Patent Office
Prior art keywords
turbine engine
engine component
part cast
cast turbine
component
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Withdrawn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
EP08162441A
Other languages
German (de)
French (fr)
Other versions
EP2031185A2 (en
Inventor
Thomas Moors
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 Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP2031185A2 publication Critical patent/EP2031185A2/en
Publication of EP2031185A3 publication Critical patent/EP2031185A3/en
Withdrawn legal-status Critical Current

Links

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
    • 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
    • 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
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • 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)

Abstract

A multi-part cast component for a turbine engine includes a first component section having a main body portion including at least one cooling flow passage section, and a second component section having a main body including at least one cooling flow passage section. The first and second component sections are joined along a parting line to form a turbine engine component with the at least one cooling flow passage section of the first component section aligning with the at least one cooling flow passage of the second component section to form a cooling flow channel.
EP08162441A 2007-08-30 2008-08-14 Multi-part cast turbine engine component having an internal cooling channel and method of forming a multi-part cast turbine engine component Withdrawn EP2031185A3 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/896,157 US20090060714A1 (en) 2007-08-30 2007-08-30 Multi-part cast turbine engine component having an internal cooling channel and method of forming a multi-part cast turbine engine component

Publications (2)

Publication Number Publication Date
EP2031185A2 EP2031185A2 (en) 2009-03-04
EP2031185A3 true EP2031185A3 (en) 2012-06-27

Family

ID=39717719

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08162441A Withdrawn EP2031185A3 (en) 2007-08-30 2008-08-14 Multi-part cast turbine engine component having an internal cooling channel and method of forming a multi-part cast turbine engine component

Country Status (4)

Country Link
US (1) US20090060714A1 (en)
EP (1) EP2031185A3 (en)
JP (1) JP2009057968A (en)
CN (1) CN101377132A (en)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8007245B2 (en) * 2007-11-29 2011-08-30 General Electric Company Shank shape for a turbine blade and turbine incorporating the same
CN101607300B (en) * 2009-07-18 2013-07-10 大同北方天力增压技术有限公司 Water-cooling and linked opening and starting type turbine wax injection die
US8899303B2 (en) 2011-05-10 2014-12-02 Howmet Corporation Ceramic core with composite insert for casting airfoils
US8915289B2 (en) 2011-05-10 2014-12-23 Howmet Corporation Ceramic core with composite insert for casting airfoils
JP6245757B2 (en) * 2014-05-22 2017-12-13 三菱日立パワーシステムズ株式会社 COOLING DEVICE, GAS TURBINE EQUIPMENT HAVING THE SAME, AND COOLING DEVICE OPERATION METHOD
US20170074116A1 (en) * 2014-07-17 2017-03-16 United Technologies Corporation Method of creating heat transfer features in high temperature alloys
US10252380B2 (en) 2014-09-10 2019-04-09 Mechanical Dynamics & Analysis Llc Repair or remanufacture of blade platform for a gas turbine engine
US9828857B2 (en) 2014-09-10 2017-11-28 Pw Power Systems, Inc. Repaired or remanufactured blade platform for a gas turbine engine
JP6810694B2 (en) * 2015-09-14 2021-01-06 三菱パワー株式会社 How to manufacture turbine blades
US10472973B2 (en) 2016-06-06 2019-11-12 General Electric Company Turbine component and methods of making and cooling a turbine component
CN113122789B (en) 2016-11-16 2022-07-08 三菱重工业株式会社 Nickel-based alloy mold and repair method thereof
US11813669B2 (en) 2016-12-13 2023-11-14 General Electric Company Method for making an integrated core-shell structure
US20180161866A1 (en) 2016-12-13 2018-06-14 General Electric Company Multi-piece integrated core-shell structure for making cast component
US11021968B2 (en) * 2018-11-19 2021-06-01 General Electric Company Reduced cross flow linking cavities and method of casting

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB926084A (en) * 1962-01-11 1963-05-15 Rolls Royce Bladed member adapted for use on a fluid flow machine
GB2095589A (en) * 1981-04-01 1982-10-06 Rolls Royce Method of making a blade for a gas turbine engine
JPH11114662A (en) * 1997-10-09 1999-04-27 Ishikawajima Harima Heavy Ind Co Ltd Joining method for casting material and manufacture of turbine blade
US5993156A (en) * 1997-06-26 1999-11-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Snecma Turbine vane cooling system

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1776015A1 (en) * 1968-09-04 1971-09-16 Daimler Benz Ag Turbine blade
US4073599A (en) * 1976-08-26 1978-02-14 Westinghouse Electric Corporation Hollow turbine blade tip closure
US4257737A (en) * 1978-07-10 1981-03-24 United Technologies Corporation Cooled rotor blade
FR2516165B1 (en) * 1981-11-10 1986-07-04 Snecma GAS TURBINE BLADE WITH FLUID CIRCULATION COOLING CHAMBER AND METHOD FOR PRODUCING THE SAME
US4815939A (en) * 1986-11-03 1989-03-28 Airfoil Textron Inc. Twisted hollow airfoil with non-twisted internal support ribs
US5246340A (en) * 1991-11-19 1993-09-21 Allied-Signal Inc. Internally cooled airfoil
DE10064267A1 (en) * 2000-12-22 2002-07-04 Alstom Switzerland Ltd Process for quickly manufacturing hollow turbine blades for manufacturing development and component testing
US6491496B2 (en) * 2001-02-23 2002-12-10 General Electric Company Turbine airfoil with metering plates for refresher holes
US6672836B2 (en) * 2001-12-11 2004-01-06 United Technologies Corporation Coolable rotor blade for an industrial gas turbine engine
US6966756B2 (en) * 2004-01-09 2005-11-22 General Electric Company Turbine bucket cooling passages and internal core for producing the passages
US7137780B2 (en) * 2004-06-17 2006-11-21 Siemens Power Generation, Inc. Internal cooling system for a turbine blade
US7168921B2 (en) * 2004-11-18 2007-01-30 General Electric Company Cooling system for an airfoil
US7311497B2 (en) * 2005-08-31 2007-12-25 United Technologies Corporation Manufacturable and inspectable microcircuits
US8591189B2 (en) * 2006-11-20 2013-11-26 General Electric Company Bifeed serpentine cooled blade

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB926084A (en) * 1962-01-11 1963-05-15 Rolls Royce Bladed member adapted for use on a fluid flow machine
GB2095589A (en) * 1981-04-01 1982-10-06 Rolls Royce Method of making a blade for a gas turbine engine
US5993156A (en) * 1997-06-26 1999-11-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Snecma Turbine vane cooling system
JPH11114662A (en) * 1997-10-09 1999-04-27 Ishikawajima Harima Heavy Ind Co Ltd Joining method for casting material and manufacture of turbine blade

Also Published As

Publication number Publication date
US20090060714A1 (en) 2009-03-05
EP2031185A2 (en) 2009-03-04
CN101377132A (en) 2009-03-04
JP2009057968A (en) 2009-03-19

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