WO2013011126A3 - Heat shield element for a gas turbine - Google Patents

Heat shield element for a gas turbine Download PDF

Info

Publication number
WO2013011126A3
WO2013011126A3 PCT/EP2012/064286 EP2012064286W WO2013011126A3 WO 2013011126 A3 WO2013011126 A3 WO 2013011126A3 EP 2012064286 W EP2012064286 W EP 2012064286W WO 2013011126 A3 WO2013011126 A3 WO 2013011126A3
Authority
WO
WIPO (PCT)
Prior art keywords
section
heat shield
shield element
gas turbine
hot gas
Prior art date
Application number
PCT/EP2012/064286
Other languages
French (fr)
Other versions
WO2013011126A2 (en
Inventor
Janos Szijarto
Per Granberg
Esa Utriainen
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2013011126A2 publication Critical patent/WO2013011126A2/en
Publication of WO2013011126A3 publication Critical patent/WO2013011126A3/en

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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2201/00—Metals
    • F05C2201/04—Heavy metals
    • F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
    • F05C2201/0463—Cobalt
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2201/00—Metals
    • F05C2201/04—Heavy metals
    • F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
    • F05C2201/0466—Nickel
    • 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
    • F05D2230/10—Manufacture by removing material
    • F05D2230/13—Manufacture by removing material using lasers
    • 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
    • F05D2230/22—Manufacture essentially without removing material by sintering
    • 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
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/185—Two-dimensional patterned serpentine-like
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/25—Three-dimensional helical
    • 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
    • F05D2260/221—Improvement of heat transfer

Abstract

Heat shield element (HS) for a gas turbine (GT) comprising an areal wall section (WS), said wall section (WS) being defined by limiting edges of the heat shield element (HS), and having a defined thickness (TH) extending radially from an inner surface (IS) to an outer surface (OS) said inner surface (IS) is exposed to a hot gas path (HGP) and said outer surface (OS) is exposed to a coolant (CO). To improve cooling efficiency, cooling channels (CC) are provided through the wall of said wall section (WS) said cooling channels (CC) comprising a first section (SI) starting at the inner surface (IS), further comprising a second section (S2) extending between the inner surface (IS) and the outer surface (OS) along a length of at least three times the thickness (TH) of the wall section (WS) at that specific area of the second section and comprising a third section (S3) joining the hot gas path so that said cooling channels (CC) connect said cavity (CV) with the hot gas path (HGP).
PCT/EP2012/064286 2011-07-21 2012-07-20 Heat shield element, gas turbine WO2013011126A2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP11174851.3 2011-07-21
EP11174851A EP2549063A1 (en) 2011-07-21 2011-07-21 Heat shield element for a gas turbine

Publications (2)

Publication Number Publication Date
WO2013011126A2 WO2013011126A2 (en) 2013-01-24
WO2013011126A3 true WO2013011126A3 (en) 2013-05-30

Family

ID=45002192

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2012/064286 WO2013011126A2 (en) 2011-07-21 2012-07-20 Heat shield element, gas turbine

Country Status (2)

Country Link
EP (1) EP2549063A1 (en)
WO (1) WO2013011126A2 (en)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3008392B1 (en) * 2013-06-14 2019-08-07 United Technologies Corporation Gas turbine engine wave geometry combustor liner panel
EP2894301A1 (en) 2014-01-14 2015-07-15 Alstom Technology Ltd Stator heat shield segment
DE102014221225A1 (en) * 2014-10-20 2016-04-21 Siemens Aktiengesellschaft Heat shield element and method for its production
US9896970B2 (en) 2014-11-14 2018-02-20 General Electric Company Method and system for sealing an annulus
US20170175576A1 (en) * 2015-12-16 2017-06-22 General Electric Company System and method for utilizing target features in forming inlet passages in micro-channel circuit
US10100667B2 (en) 2016-01-15 2018-10-16 United Technologies Corporation Axial flowing cooling passages for gas turbine engine components
RU2706210C2 (en) 2016-01-25 2019-11-14 Ансалдо Энерджиа Свитзерлэнд Аг Stator thermal shield for gas turbine, gas turbine with such stator thermal shield and stator thermal shield cooling method
US10550710B2 (en) * 2018-05-31 2020-02-04 General Electric Company Shroud for gas turbine engine

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2125111A (en) * 1982-03-23 1984-02-29 Rolls Royce Shroud assembly for a gas turbine engine
EP0709550A1 (en) * 1994-10-31 1996-05-01 General Electric Company Cooled shroud
US5649806A (en) * 1993-11-22 1997-07-22 United Technologies Corporation Enhanced film cooling slot for turbine blade outer air seals
WO2000040838A1 (en) * 1999-01-07 2000-07-13 Siemens Westinghouse Power Corporation Method of cooling a combustion turbine
US6276142B1 (en) * 1997-08-18 2001-08-21 Siemens Aktiengesellschaft Cooled heat shield for gas turbine combustor
EP1517008A2 (en) * 2003-09-17 2005-03-23 General Electric Company Cooling of a coated wall by a network of cooling channels
US20090022583A1 (en) * 2005-04-21 2009-01-22 Albert Schrey Turbine blade with a cover plate and a protective layer applied to the cover plate
US20100139903A1 (en) * 2008-12-08 2010-06-10 General Electric Company Heat exchanging hollow passages
DE102009053247A1 (en) * 2009-11-13 2011-05-19 Mtu Aero Engines Gmbh Method for changing natural frequency of blade for flow machine, particularly for thermal gas turbine, involves applying material on upper surface area of blade by additive manufacturing process

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1507116A1 (en) 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Heat shield arrangement for a high temperature gas conveying component, in particular for a gas turbine combustion chamber

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2125111A (en) * 1982-03-23 1984-02-29 Rolls Royce Shroud assembly for a gas turbine engine
US5649806A (en) * 1993-11-22 1997-07-22 United Technologies Corporation Enhanced film cooling slot for turbine blade outer air seals
EP0709550A1 (en) * 1994-10-31 1996-05-01 General Electric Company Cooled shroud
US6276142B1 (en) * 1997-08-18 2001-08-21 Siemens Aktiengesellschaft Cooled heat shield for gas turbine combustor
WO2000040838A1 (en) * 1999-01-07 2000-07-13 Siemens Westinghouse Power Corporation Method of cooling a combustion turbine
EP1517008A2 (en) * 2003-09-17 2005-03-23 General Electric Company Cooling of a coated wall by a network of cooling channels
US20090022583A1 (en) * 2005-04-21 2009-01-22 Albert Schrey Turbine blade with a cover plate and a protective layer applied to the cover plate
US20100139903A1 (en) * 2008-12-08 2010-06-10 General Electric Company Heat exchanging hollow passages
DE102009053247A1 (en) * 2009-11-13 2011-05-19 Mtu Aero Engines Gmbh Method for changing natural frequency of blade for flow machine, particularly for thermal gas turbine, involves applying material on upper surface area of blade by additive manufacturing process

Also Published As

Publication number Publication date
EP2549063A1 (en) 2013-01-23
WO2013011126A2 (en) 2013-01-24

Similar Documents

Publication Publication Date Title
WO2013011126A3 (en) Heat shield element for a gas turbine
WO2014081492A3 (en) Cooling for combustor liners with accelerating channels
WO2015050592A3 (en) Gas turbine engine combustor liner panel
WO2015047472A3 (en) Conductive panel surface cooling augmentation for gas turbine engine combustor
WO2015023338A3 (en) Gas turbine engine component having trip strips
EP2381070A3 (en) Hot gas path component cooling system
WO2014028095A3 (en) Blade outer air seal with cored passages
WO2015147929A3 (en) Cooling an aperture body of a combustor wall
WO2013188645A3 (en) Gas turbine engine wall
WO2013135702A3 (en) Heat-shield element for a compressor-air bypass around the combustion chamber
WO2014028090A3 (en) Blade outer air seal for a gas turbine engine
EP3008312A4 (en) Heat shield assembly with double lap joint for a gas turbine engine
WO2008133758A3 (en) Airfoil for a gas turbine with impingement holes
WO2014116626A3 (en) Purge and cooling air for an exhaust section of a gas turbine assembly
EP2623726A3 (en) Turbofan engine fan case and corresponding turbofan engine
WO2014055887A3 (en) Gas turbine engine combustor liner
EP2946092A4 (en) Gas turbine engine combustor liner assembly with convergent hyperbolic profile
EP2549188A3 (en) Insert for a gas turbine engine combustor
WO2013044197A3 (en) A combustor resonator section with an internal thermal barrier coating and method of fabricating the same
WO2014123624A3 (en) Gas turbine engine combustor heat shield with increased film cooling effectiveness
EP2956634A4 (en) Compliant heat shield liner hanger assembly for gas turbine engines
EP2954261A4 (en) Gas turbine engine combustor liner assembly with convergent hyperbolic profile
WO2013184495A3 (en) Combustor liner with decreased liner cooling
WO2014042724A3 (en) Turbine compressor blade tip resistant to metal transfer
EP3039340A4 (en) Vena contracta swirling dilution passages for gas turbine engine combustor

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 12740934

Country of ref document: EP

Kind code of ref document: A2

DPE1 Request for preliminary examination filed after expiration of 19th month from priority date (pct application filed from 20040101)
122 Ep: pct application non-entry in european phase

Ref document number: 12740934

Country of ref document: EP

Kind code of ref document: A2