MX2009011266A - Proteccion termica para estator. - Google Patents

Proteccion termica para estator.

Info

Publication number
MX2009011266A
MX2009011266A MX2009011266A MX2009011266A MX2009011266A MX 2009011266 A MX2009011266 A MX 2009011266A MX 2009011266 A MX2009011266 A MX 2009011266A MX 2009011266 A MX2009011266 A MX 2009011266A MX 2009011266 A MX2009011266 A MX 2009011266A
Authority
MX
Mexico
Prior art keywords
heat shield
stator heat
distance
gas turbine
another
Prior art date
Application number
MX2009011266A
Other languages
English (en)
Inventor
Alexander Khanin
Edouard Sloutski
Anton Sumin
Sergey Vorontsov
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 MX2009011266A publication Critical patent/MX2009011266A/es

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00Components
    • F05D2240/10Stators
    • F05D2240/11Shroud seal segments
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00Components
    • F05D2240/55Seals
    • F05D2240/57Leaf seals
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/20Heat transfer, e.g. cooling
    • F05D2260/201Heat transfer, e.g. cooling by impingement of a fluid
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00Function
    • F05D2260/20Heat transfer, e.g. cooling
    • F05D2260/221Improvement of heat transfer
    • F05D2260/2214Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Abstract

La presente invención se refiere a una protección térmica para estator (6) para una turbina de gas (1), que en estado montado presenta una trayectoria de gas caliente (9) del lado exterior adyacente a la turbina de gas (1), un lado interior (12) opuesto al lado exterior (11), varias nervaduras (13) formada en el interior (12), que en estado montado se extienden axialmente en relación a un eje de rotación (8) de un rotor (3) de la turbina de gas (1) y en la dirección periférica están separados, cuando menos una placa deflectora (14) montada en el lado interior (12), la cual se apoya sobre las nervaduras (13), cuando menos una ranura (16), que está formada en el lado frontal (15) que colinda en la dirección periférica con una protección térmica para estator (6), y en la cual puede introducirse cuando menos un elemento hermético (18), y varias perforaciones (19) que con un extremo desembocan en el lado interior (12) y con el otro extremo desembocan en el lado frontal (15) de la ranura (16) en dirección hacia el lado exterior (11) y están separadas entre si en dirección axial.
MX2009011266A 2007-04-19 2008-04-07 Proteccion termica para estator. MX2009011266A (es)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH6452007 2007-04-19
PCT/EP2008/054140 WO2008128876A1 (de) 2007-04-19 2008-04-07 Statorhitzeschild

Publications (1)

Publication Number Publication Date
MX2009011266A true MX2009011266A (es) 2009-11-02

Family

ID=38349602

Family Applications (1)

Application Number Title Priority Date Filing Date
MX2009011266A MX2009011266A (es) 2007-04-19 2008-04-07 Proteccion termica para estator.

Country Status (6)

Country Link
US (1) US7997856B2 (es)
EP (1) EP2137382B1 (es)
CA (1) CA2684371C (es)
MX (1) MX2009011266A (es)
SI (1) SI2137382T1 (es)
WO (1) WO2008128876A1 (es)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008128876A1 (de) 2007-04-19 2008-10-30 Alstom Technology Ltd Statorhitzeschild
IT1395732B1 (it) * 2009-08-03 2012-10-19 Ansaldo Energia Spa Apparecchiatura per l'investigazione sperimentale di sistemi di tenuta assiale di turbine a gas
FR2968350B1 (fr) * 2010-12-06 2016-01-29 Snecma Anneau sectorise de turbine pour turbomachine, et turbomachine equipee d'un tel anneau
US8876458B2 (en) * 2011-01-25 2014-11-04 United Technologies Corporation Blade outer air seal assembly and support
EP2508713A1 (en) * 2011-04-04 2012-10-10 Siemens Aktiengesellschaft Gas turbine comprising a heat shield and method of operation
WO2014150182A1 (en) * 2013-03-15 2014-09-25 United Technologies Corporation Interlocking rotor assembly with thermal shield
US8814507B1 (en) 2013-05-28 2014-08-26 Siemens Energy, Inc. Cooling system for three hook ring segment
ES2581511T3 (es) * 2013-07-15 2016-09-06 Mtu Aero Engines Gmbh Turbomáquina, segmento de sellado y segmento de álabe de guía
EP2835500A1 (de) 2013-08-09 2015-02-11 Siemens Aktiengesellschaft Einsatzelement und Gasturbine
WO2015084550A1 (en) * 2013-12-03 2015-06-11 United Technologies Corporation Heat shields for air seals
EP2949873A1 (en) * 2014-05-27 2015-12-02 Siemens Aktiengesellschaft Turbomachine with an ingestion shield and use of the turbomachine
WO2016028310A1 (en) 2014-08-22 2016-02-25 Siemens Aktiengesellschaft Shroud cooling system for shrouds adjacent to airfoils within gas turbine engines
EP3118420A1 (en) * 2015-07-15 2017-01-18 Siemens Aktiengesellschaft Coolable wall element with impingement plate
EP3179053B1 (de) 2015-12-07 2019-04-03 MTU Aero Engines GmbH Gehäusestruktur einer strömungsmaschine mit hitzeschutzschild
US10513943B2 (en) 2016-03-16 2019-12-24 United Technologies Corporation Boas enhanced heat transfer surface
GB2559804A (en) * 2017-02-21 2018-08-22 Siemens Ag Heatshield for a gas turbine
US10428689B2 (en) * 2017-05-17 2019-10-01 Rolls-Royce Deutschland Ltd & Co Kg Heat shield for a gas turbine engine
US20180347399A1 (en) * 2017-06-01 2018-12-06 Pratt & Whitney Canada Corp. Turbine shroud with integrated heat shield
US11168702B2 (en) 2017-08-10 2021-11-09 Raytheon Technologies Corporation Rotating airfoil with tip pocket

Family Cites Families (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3728039A (en) * 1966-11-02 1973-04-17 Gen Electric Fluid cooled porous stator structure
US4573865A (en) * 1981-08-31 1986-03-04 General Electric Company Multiple-impingement cooled structure
GB2125111B (en) * 1982-03-23 1985-06-05 Rolls Royce Shroud assembly for a gas turbine engine
DE19919654A1 (de) * 1999-04-29 2000-11-02 Abb Alstom Power Ch Ag Hitzeschild für eine Gasturbine
DE19963371A1 (de) * 1999-12-28 2001-07-12 Alstom Power Schweiz Ag Baden Gekühltes Hitzeschild
CA2372984C (en) * 2000-03-07 2005-05-10 Mitsubishi Heavy Industries, Ltd. Gas turbine segmental ring
US6340285B1 (en) * 2000-06-08 2002-01-22 General Electric Company End rail cooling for combined high and low pressure turbine shroud
US6354795B1 (en) * 2000-07-27 2002-03-12 General Electric Company Shroud cooling segment and assembly
JP4698847B2 (ja) * 2001-01-19 2011-06-08 三菱重工業株式会社 ガスタービン分割環
GB0117110D0 (en) * 2001-07-13 2001-09-05 Siemens Ag Coolable segment for a turbomachinery and combustion turbine
US7033138B2 (en) * 2002-09-06 2006-04-25 Mitsubishi Heavy Industries, Ltd. Ring segment of gas turbine
US6905302B2 (en) * 2003-09-17 2005-06-14 General Electric Company Network cooled coated wall
US7387488B2 (en) * 2005-08-05 2008-06-17 General Electric Company Cooled turbine shroud
US7377742B2 (en) * 2005-10-14 2008-05-27 General Electric Company Turbine shroud assembly and method for assembling a gas turbine engine
WO2008128876A1 (de) 2007-04-19 2008-10-30 Alstom Technology Ltd Statorhitzeschild

Also Published As

Publication number Publication date
US7997856B2 (en) 2011-08-16
SI2137382T1 (sl) 2012-10-30
EP2137382B1 (de) 2012-05-30
EP2137382A1 (de) 2009-12-30
CA2684371C (en) 2014-10-21
CA2684371A1 (en) 2008-10-30
WO2008128876A1 (de) 2008-10-30
US20100047062A1 (en) 2010-02-25

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