CA2668750A1 - Film cooling structure - Google Patents

Film cooling structure Download PDF

Info

Publication number
CA2668750A1
CA2668750A1 CA002668750A CA2668750A CA2668750A1 CA 2668750 A1 CA2668750 A1 CA 2668750A1 CA 002668750 A CA002668750 A CA 002668750A CA 2668750 A CA2668750 A CA 2668750A CA 2668750 A1 CA2668750 A1 CA 2668750A1
Authority
CA
Canada
Prior art keywords
film cooling
combustion gas
hole
structural wall
cooling structure
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
CA002668750A
Other languages
French (fr)
Other versions
CA2668750C (en
Inventor
Yoji Ohkita
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.)
IHI Corp
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of CA2668750A1 publication Critical patent/CA2668750A1/en
Application granted granted Critical
Publication of CA2668750C publication Critical patent/CA2668750C/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F01D5/186—Film 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
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet
    • 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

Landscapes

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

Abstract

Film cooling structure (10) including structure wall (11) having outer surface (12) exposed to combustion gas and inner surface (13) positioned opposite to the outer surface (12), the film cooling structure (10) provided with film cooling hole (14) for, in the structure wall (11), leading of cooling air on the side of inner surface (13) to the side of outer surface (12) to thereby carry out film cooling of the outer surface (12), wherein the film cooling hole (14) has introduction portion (14a) extending from the inner surface (13) toward the outer surface (12) up to a mid position within the structure wall (11); enlarging portion (14b) having its cross section area gradually increasing from the end of the introduction portion (14a) on the side of outer surface (12) toward the outer surface (12) and opening on the outer surface (12); and partition portion (16) for partitioning of the interior of the enlarging portion (14b) into multiple units in the direction of hole width orthogonal to the direction of flow of combustion gas.

Claims (2)

1. A film cooling structure, comprising:

a structural wall that has an outer surface exposed to combustion gas and an inner surface positioned opposite to the outer surface, wherein film cooling holes being formed at the structural wall and introducing cooling air from the inner surface toward the outer surface in order to perform film cooling of the outer surface, the film cooling hole includes an introducing portion that extends to a middle position in the structural wall from the inner surface toward the outer surface, an enlarged portion of which the cross-sectional area is gradually increased toward the outer surface from an end of an outer surface side of the introducing portion and which is opened at the outer surface, and a partition portion that partitions the inside of the enlarged portion into a plurality of spaces in a width direction of the hole perpendicular to a flow direction of the combustion gas.
2. The film cooling structure according to claim 1, wherein the partition portion is formed at a middle position of the inside of the film cooling hole in the width direction of the hole perpendicular to the flow direction of the combustion gas, and the partition portion protrudes from one of the wall surfaces facing upstream and downstream sides in the flow direction of the combustion gas toward the other thereof, and extends over the entire inside of the hole from the inner surface of the structural wall toward the outer surface.
CA2668750A 2006-11-13 2007-03-13 Film cooling structure Expired - Fee Related CA2668750C (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
JP2006-306538 2006-11-13
JP2006306538A JP4941891B2 (en) 2006-11-13 2006-11-13 Film cooling structure
PCT/JP2007/054910 WO2008059620A1 (en) 2006-11-13 2007-03-13 Film cooling structure

Publications (2)

Publication Number Publication Date
CA2668750A1 true CA2668750A1 (en) 2008-05-22
CA2668750C CA2668750C (en) 2012-06-19

Family

ID=39401434

Family Applications (1)

Application Number Title Priority Date Filing Date
CA2668750A Expired - Fee Related CA2668750C (en) 2006-11-13 2007-03-13 Film cooling structure

Country Status (5)

Country Link
US (1) US20100040459A1 (en)
EP (1) EP2083147B1 (en)
JP (1) JP4941891B2 (en)
CA (1) CA2668750C (en)
WO (1) WO2008059620A1 (en)

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US8371814B2 (en) * 2009-06-24 2013-02-12 Honeywell International Inc. Turbine engine components
US8529193B2 (en) * 2009-11-25 2013-09-10 Honeywell International Inc. Gas turbine engine components with improved film cooling
US8628293B2 (en) 2010-06-17 2014-01-14 Honeywell International Inc. Gas turbine engine components with cooling hole trenches
US8672613B2 (en) * 2010-08-31 2014-03-18 General Electric Company Components with conformal curved film holes and methods of manufacture
US8858175B2 (en) * 2011-11-09 2014-10-14 General Electric Company Film hole trench
JP5982807B2 (en) * 2011-12-15 2016-08-31 株式会社Ihi Turbine blade
US8850828B2 (en) 2012-02-15 2014-10-07 United Technologies Corporation Cooling hole with curved metering section
US8683813B2 (en) * 2012-02-15 2014-04-01 United Technologies Corporation Multi-lobed cooling hole and method of manufacture
US9284844B2 (en) 2012-02-15 2016-03-15 United Technologies Corporation Gas turbine engine component with cusped cooling hole
US10422230B2 (en) 2012-02-15 2019-09-24 United Technologies Corporation Cooling hole with curved metering section
US8683814B2 (en) * 2012-02-15 2014-04-01 United Technologies Corporation Gas turbine engine component with impingement and lobed cooling hole
US9422815B2 (en) 2012-02-15 2016-08-23 United Technologies Corporation Gas turbine engine component with compound cusp cooling configuration
US8584470B2 (en) * 2012-02-15 2013-11-19 United Technologies Corporation Tri-lobed cooling hole and method of manufacture
US9273560B2 (en) * 2012-02-15 2016-03-01 United Technologies Corporation Gas turbine engine component with multi-lobed cooling hole
US8689568B2 (en) 2012-02-15 2014-04-08 United Technologies Corporation Cooling hole with thermo-mechanical fatigue resistance
US20130209235A1 (en) * 2012-02-15 2013-08-15 United Technologies Corporation Gas turbine engine component with cusped, lobed cooling hole
US9024226B2 (en) * 2012-02-15 2015-05-05 United Technologies Corporation EDM method for multi-lobed cooling hole
US8763402B2 (en) * 2012-02-15 2014-07-01 United Technologies Corporation Multi-lobed cooling hole and method of manufacture
US9650900B2 (en) 2012-05-07 2017-05-16 Honeywell International Inc. Gas turbine engine components with film cooling holes having cylindrical to multi-lobe configurations
CN104364581B (en) * 2012-06-13 2016-05-18 通用电气公司 Gas-turbine unit wall
US10113433B2 (en) * 2012-10-04 2018-10-30 Honeywell International Inc. Gas turbine engine components with lateral and forward sweep film cooling holes
US10464135B2 (en) 2013-03-15 2019-11-05 United Technologies Corporation Additive manufacturing method for the addition of features within cooling holes
EP2886798B1 (en) * 2013-12-20 2018-10-24 Rolls-Royce Corporation mechanically machined film cooling holes
US10370987B2 (en) 2014-04-03 2019-08-06 Mitsubishi Hitachi Power Systems, Ltd. Blade or vane row and gas turbine
US11313235B2 (en) * 2015-03-17 2022-04-26 General Electric Company Engine component with film hole
US10208602B2 (en) * 2015-04-27 2019-02-19 United Technologies Corporation Asymmetric diffuser opening for film cooling holes
US11021965B2 (en) 2016-05-19 2021-06-01 Honeywell International Inc. Engine components with cooling holes having tailored metering and diffuser portions
US10605092B2 (en) * 2016-07-11 2020-03-31 United Technologies Corporation Cooling hole with shaped meter
KR101853550B1 (en) * 2016-08-22 2018-04-30 두산중공업 주식회사 Gas Turbine Blade
US20180058770A1 (en) * 2016-09-01 2018-03-01 Additive Rocket Corporation Structural heat exchanger
EP3354849A1 (en) * 2017-01-31 2018-08-01 Siemens Aktiengesellschaft Wall of a hot gas part and corresponding hot gas part for a gas turbine
KR20200040278A (en) 2017-08-11 2020-04-17 아르크로마 아이피 게엠베하 Purified concentrated leucoindigo salt aqueous solution
US10933481B2 (en) * 2018-01-05 2021-03-02 General Electric Company Method of forming cooling passage for turbine component with cap element
US11286792B2 (en) * 2019-07-30 2022-03-29 Rolls-Royce Plc Ceramic matrix composite vane with cooling holes and methods of making the same

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US3936223A (en) * 1974-09-23 1976-02-03 General Motors Corporation Compressor diffuser
US4529358A (en) * 1984-02-15 1985-07-16 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Vortex generating flow passage design for increased film cooling effectiveness
JPH0693802A (en) * 1992-09-14 1994-04-05 Hitachi Ltd Gas turbine stator vane
JP2810023B2 (en) * 1996-09-18 1998-10-15 株式会社東芝 High temperature member cooling device
JP2001012204A (en) * 1999-06-30 2001-01-16 Toshiba Corp Gas turbine blade
US6234755B1 (en) 1999-10-04 2001-05-22 General Electric Company Method for improving the cooling effectiveness of a gaseous coolant stream, and related articles of manufacture
JP2002221005A (en) * 2001-01-26 2002-08-09 Ishikawajima Harima Heavy Ind Co Ltd Cooling turbine blade
US6629817B2 (en) 2001-07-05 2003-10-07 General Electric Company System and method for airfoil film cooling
US7008186B2 (en) 2003-09-17 2006-03-07 General Electric Company Teardrop film cooled blade
JP3997986B2 (en) * 2003-12-19 2007-10-24 株式会社Ｉｈｉ Cooling turbine component and cooling turbine blade
US7328580B2 (en) 2004-06-23 2008-02-12 General Electric Company Chevron film cooled wall
JP4898253B2 (en) * 2005-03-30 2012-03-14 三菱重工業株式会社 High temperature components for gas turbines

Also Published As

Publication number Publication date
EP2083147B1 (en) 2015-10-07
JP4941891B2 (en) 2012-05-30
EP2083147A4 (en) 2014-05-14
EP2083147A1 (en) 2009-07-29
US20100040459A1 (en) 2010-02-18
WO2008059620A1 (en) 2008-05-22
CA2668750C (en) 2012-06-19
JP2008121561A (en) 2008-05-29

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EEER Examination request
MKLA Lapsed

Effective date: 20170313