EP2384392B1 - Élément structural refroidi pour turbine à gaz - Google Patents

Élément structural refroidi pour turbine à gaz Download PDF

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Publication number
EP2384392B1
EP2384392B1 EP10701375.7A EP10701375A EP2384392B1 EP 2384392 B1 EP2384392 B1 EP 2384392B1 EP 10701375 A EP10701375 A EP 10701375A EP 2384392 B1 EP2384392 B1 EP 2384392B1
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EP
European Patent Office
Prior art keywords
pins
wall
impingement cooling
density
holes
Prior art date
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Application number
EP10701375.7A
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German (de)
English (en)
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EP2384392A1 (fr
EP2384392B2 (fr
Inventor
Jörg KRÜCKELS
Milan Pathak
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Ansaldo Energia IP UK Ltd
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Ansaldo Energia IP UK Ltd
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Application filed by Ansaldo Energia IP UK Ltd filed Critical Ansaldo Energia IP UK Ltd
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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
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Definitions

  • the present invention relates to the field of gas turbines. It relates to a cooled component for a gas turbine according to the preamble of claim 1. It also relates to a method for operating such a device.
  • Gas turbines are designed to increase the efficiency for ever higher operating temperatures. Particularly exposed to thermal stresses are mainly the components or components in the combustion chamber and the running and vanes of the following turbine including the other, the hot gas channel limiting elements. In order to effectively counteract the thermal stresses occurring, on the one hand particularly resistant materials, such. As nickel-based alloys are used. On the other hand, additional measures for cooling the components must be taken, with different cooling methods, such as. the film cooling or the impingement cooling, find application.
  • the invention aims to remedy this situation. It is therefore an object of the invention to provide a cooled component of a gas turbine, in particular a platformed vane, the cooling of which is optimally adapted to the locally varying thermal load without causing unnecessary overconsumption of cooling air, i. it is achieved with the same cooling intensity minimizing the cooling air used.
  • the thermally stressed and cooled wall has a plurality of pins projecting from the wall on its rear side in a planar distribution, and that the distribution of the pins within the thermal critical zones of the component has a higher density than in the remaining areas.
  • the heat transfer between the wall and cooling air can locally be changed and adapted to the thermal load, without necessarily a larger amount of cooling air must be used.
  • An embodiment of the invention is characterized in that the means for generating the directed onto the back of the wall rays comprise a provided with distributed impingement cooling holes impingement cooling plate.
  • Cooling is particularly effective when, according to another embodiment of the invention, the impingement cooling plate is spaced substantially parallel to the back of the wall, and the distribution of the impingement cooling holes is matched to the distribution of the pins such that viewed in a direction perpendicular to the impingement cooling plate Impact cooling holes are each between the pins.
  • the variation of the cooling can be intensified by correlating the density of the impingement cooling holes with the density of the pins.
  • the density of the impingement cooling holes and the density of the pins may be locally equal.
  • the component is preferably a guide vane of a gas turbine which comprises a blade extending in a longitudinal direction and a platform extending transversely to the longitudinal direction, the bottom of which is the thermally loaded wall cooled by impingement cooling and a groove at the transition to the blade forms, with the distribution of the pins to the groove towards a higher density than in the other areas removed from the groove.
  • Fig. 1 is shown in longitudinal section of the upper part of a gas turbine guide vane with platform and locally varying impingement cooling according to an embodiment of the invention.
  • the vane 10 has a total of a similar configuration, as in the above-mentioned US B2-7,097,418 is described. It comprises an airfoil 11 extending in the blade longitudinal direction, at the upper end of which a platform 12 is formed, which extends substantially transversely to the longitudinal direction of the blade.
  • the platform 12 has a bottom wall 12a, the underside of which is acted upon by the hot gas flowing through the turbine, and which is cooled on the top by impingement cooling.
  • a cavity 13 is formed on the upper side of the platform 12, which cavity is covered by a baffle cooling plate 14 arranged parallel to the wall 12a.
  • impingement cooling holes 16 are provided in a predetermined distribution through which compressed cooling air in the form of individual cooling air jets (see the arrows in FIG Fig. 1 ) enters the cavity 13 and impinges on the opposite rear side of the wall 12a.
  • the cooling air absorbs heat from the wall 12a and is subsequently removed from the cavity 13 (in FIG Fig. 1 not shown paths) derived.
  • the area distribution of the impingement cooling holes 16 is in Fig. 2 to see.
  • the density of the impingement cooling holes 16 and the density of the pins 15 are locally different but correlated with each other, ie, in the areas where the density of the pins 15 is increased (compression area 18), the density of the impingement cooling holes 16 is also increased , and vice versa. In particular, locally the densities of the two are the same.
  • the impingement cooling holes 16 are preferably arranged "with gaps", that is, on intermediate spaces, with the pins 15: Between two parallel rows of pins 15, a row of impingement cooling holes 16 with the same periodicity is offset in each case.

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

Claims (5)

  1. Elément (10) refroidi pour une turbine à gaz, lequel, pour le refroidissement d'une paroi (12a) exposée à des contraintes thermiques sur un côté avant, présentes sur le côté arrière de la paroi (12a), selon une répartition plane (17), une multiplicité de pointes (15) dépassant de la paroi, ainsi que des moyens (14, 16) pour la production de jets d'un agent de refroidissement dirigés dans la zone des pointes (15) vers le côté arrière de la paroi (12a) et servant au refroidissement par impact, les moyens pour la production des jets dirigés vers le côté arrière de la paroi comprenant une tôle de refroidissement par impact (14) avec des trous de refroidissement par impact (16) disposés de façon répartie, et la densité des trous de refroidissement par impact (16) étant corrélée avec la densité des pointes (15), la répartition des pointes (15) à l'intérieur des zones critiques (Ac) de l'élément (10) présentant une densité plus élevée que dans les autres zones de l'élément, caractérisé en ce que, dans les zones où la densité des pointes est accrue, la densité des trous de refroidissement par impact (16) est également accrue, et inversement.
  2. Elément refroidi selon la revendication 1, caractérisé en ce que la tôle de refroidissement par impact (14) est disposée de façon espacée, essentiellement parallèle au côté arrière de la paroi (12a), et en ce que la répartition des trous de refroidissement par impact (16) est harmonisée avec la répartition des pointes (15) de telle sorte que, vu dans une direction perpendiculaire à la tôle de refroidissement par impact (14), les trous de refroidissement par impact (16) sont situés respectivement entre les pointes (15).
  3. Elément refroidi selon la revendication 1, caractérisé en ce que la densité des trous de refroidissement par impact (16) et la densité des pointes (15) sont localement identiques.
  4. Elément refroidi selon l'une des revendications 1 à 3, caractérisé en ce que l'élément est une aube directrice (10) de la turbine à gaz qui comprend une ailette (11) s'étendant dans une direction longitudinale et une plate-forme (12), se raccordant à l'ailette (11) et s'étendant transversalement à la direction longitudinale, dont le fond est la paroi (12a) exposée à des contraintes thermiques et refroidie par refroidissement par impact, et forme une cannelure (Ac) au niveau de la transition vers l'ailette (11), et en ce que la répartition des pointes (15) présente une densité plus élevée en direction de la cannelure (Ac) que dans les zones restantes éloignées de la cannelure (Ac).
  5. Procédé de fonctionnement d'un élément refroidi pour une turbine à gaz selon l'une des revendications 1 - 4, caractérisé en ce que, pour améliorer le transfert thermique entre la paroi (12a) et l'air de refroidissement mis en oeuvre sous la forme de jets d'air de refroidissement individuels s'écoulant à travers des trous de refroidissement par impact (16), ces jets d'air de refroidissement s'écoulent sur le côté arrière de cette paroi équipée de pointes (15) de forme conique ou pyramidale dépassant perpendiculairement, en ce que les jets d'air de refroidissement réalisent un impact entre les espaces intermédiaires formés par les pointes de telle sorte que, lors de cet impact, il apparaît un écoulement turbulent agissant sur la paroi, qui provoque un refroidissement supplémentaire.
EP10701375.7A 2009-01-30 2010-01-28 Élément structural refroidi pour turbine à gaz Active EP2384392B2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH00140/09A CH700319A1 (de) 2009-01-30 2009-01-30 Gekühltes bauelement für eine gasturbine.
PCT/EP2010/051018 WO2010086381A1 (fr) 2009-01-30 2010-01-28 Élément structural refroidi pour turbine à gaz

Publications (3)

Publication Number Publication Date
EP2384392A1 EP2384392A1 (fr) 2011-11-09
EP2384392B1 true EP2384392B1 (fr) 2017-05-31
EP2384392B2 EP2384392B2 (fr) 2024-09-04

Family

ID=40600054

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10701375.7A Active EP2384392B2 (fr) 2009-01-30 2010-01-28 Élément structural refroidi pour turbine à gaz

Country Status (5)

Country Link
US (1) US8444376B2 (fr)
EP (1) EP2384392B2 (fr)
CH (1) CH700319A1 (fr)
RU (1) RU2539950C2 (fr)
WO (1) WO2010086381A1 (fr)

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US11739935B1 (en) 2022-03-23 2023-08-29 General Electric Company Dome structure providing a dome-deflector cavity with counter-swirled airflow

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US9039350B2 (en) * 2012-01-09 2015-05-26 General Electric Company Impingement cooling system for use with contoured surfaces
US9500099B2 (en) * 2012-07-02 2016-11-22 United Techologies Corporation Cover plate for a component of a gas turbine engine
US9371735B2 (en) 2012-11-29 2016-06-21 Solar Turbines Incorporated Gas turbine engine turbine nozzle impingement cover
EP2927430B1 (fr) * 2014-04-04 2019-08-07 United Technologies Corporation Aube statorique ayant une plate-forme refroidie pour un moteur à turbine à gaz
EP2949871B1 (fr) * 2014-05-07 2017-03-01 United Technologies Corporation Segment d'aube variable
US10746403B2 (en) * 2014-12-12 2020-08-18 Raytheon Technologies Corporation Cooled wall assembly for a combustor and method of design
US9849510B2 (en) 2015-04-16 2017-12-26 General Electric Company Article and method of forming an article
US9976441B2 (en) 2015-05-29 2018-05-22 General Electric Company Article, component, and method of forming an article
US10739087B2 (en) 2015-09-08 2020-08-11 General Electric Company Article, component, and method of forming an article
US10253986B2 (en) 2015-09-08 2019-04-09 General Electric Company Article and method of forming an article
US10087776B2 (en) 2015-09-08 2018-10-02 General Electric Company Article and method of forming an article
US20170145834A1 (en) * 2015-11-23 2017-05-25 United Technologies Corporation Airfoil platform cooling core circuits with one-wall heat transfer pedestals for a gas turbine engine component and systems for cooling an airfoil platform
US10184343B2 (en) 2016-02-05 2019-01-22 General Electric Company System and method for turbine nozzle cooling
RU2641782C2 (ru) * 2016-05-30 2018-01-22 Общество с ограниченной ответственностью "Газпром трансгаз Казань" Способ охлаждения высокотемпературных шпилек паровых турбин и устройство для его осуществления
RU2641787C2 (ru) * 2016-05-30 2018-01-22 Общество с ограниченной ответственностью "Газпром трансгаз Казань" Способ охлаждения высокотемпературных шпилек газовых турбин и устройство для его осуществления
US10487660B2 (en) 2016-12-19 2019-11-26 General Electric Company Additively manufactured blade extension with internal features
US10641174B2 (en) 2017-01-18 2020-05-05 General Electric Company Rotor shaft cooling
US20180216474A1 (en) * 2017-02-01 2018-08-02 General Electric Company Turbomachine Blade Cooling Cavity
US10989068B2 (en) 2018-07-19 2021-04-27 General Electric Company Turbine shroud including plurality of cooling passages
CN108894832B (zh) * 2018-08-17 2024-01-23 西安热工研究院有限公司 超临界工质旋转机械本体侧面的外冷装置及方法
US10822962B2 (en) * 2018-09-27 2020-11-03 Raytheon Technologies Corporation Vane platform leading edge recessed pocket with cover
JP6508499B1 (ja) * 2018-10-18 2019-05-08 三菱日立パワーシステムズ株式会社 ガスタービン静翼、これを備えているガスタービン、及びガスタービン静翼の製造方法
US10837315B2 (en) * 2018-10-25 2020-11-17 General Electric Company Turbine shroud including cooling passages in communication with collection plenums
KR102126852B1 (ko) 2018-10-29 2020-06-25 두산중공업 주식회사 터빈 베인 및 링세그먼트와 이를 포함하는 가스 터빈
US11125434B2 (en) * 2018-12-10 2021-09-21 Raytheon Technologies Corporation Preferential flow distribution for gas turbine engine component
CN109737788A (zh) * 2018-12-21 2019-05-10 西北工业大学 一种减小流动损失、强化冲击换热的凸起靶板结构
US11891920B2 (en) * 2019-04-16 2024-02-06 Mitsubishi Heavy Industries, Ltd. Turbine stator vane and gas turbine
US11073036B2 (en) * 2019-06-03 2021-07-27 Raytheon Technologies Corporation Boas flow directing arrangement
KR102502652B1 (ko) * 2020-10-23 2023-02-21 두산에너빌리티 주식회사 물결 형태 유로를 구비한 배열 충돌제트 냉각구조

Citations (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2343673A1 (de) 1972-09-05 1974-03-14 Gen Electric Stiftrippen-kuehlsystem
US4712979A (en) 1985-11-13 1987-12-15 The United States Of America As Represented By The Secretary Of The Air Force Self-retained platform cooling plate for turbine vane
RU2009331C1 (ru) 1990-09-27 1994-03-15 Научно-производственное предприятие "Завод им.В.Я.Климова" Устройство для конвективного охлаждения деталей турбины
WO1994012770A1 (fr) 1992-11-24 1994-06-09 United Technologies Corporation Aube de rotor a plate-forme d'un seul tenant avec ladite aube et passage de refroidissement du conge de raccordement
US5321951A (en) 1992-03-30 1994-06-21 General Electric Company Integral combustor splash plate and sleeve
EP0889201A1 (fr) 1997-07-03 1999-01-07 Abb Research Ltd. Refroidissement d'une partie de paroi d'aube de turbine par jets d'air
US20020062945A1 (en) 1997-09-30 2002-05-30 Rainer Hocker Wall part acted upon by an impingement flow
US6402464B1 (en) 2000-08-29 2002-06-11 General Electric Company Enhanced heat transfer surface for cast-in-bump-covered cooling surfaces and methods of enhancing heat transfer
US20030039537A1 (en) 2001-08-27 2003-02-27 Itzel Gary Michael Method for controlling coolant flow in airfoil, flow control structure and airfoil incorporating the same
US6779597B2 (en) 2002-01-16 2004-08-24 General Electric Company Multiple impingement cooled structure
US20050175444A1 (en) 2004-02-09 2005-08-11 Siemens Westinghouse Power Corporation Cooling system for an airfoil vane
WO2006045758A1 (fr) 2004-10-25 2006-05-04 Siemens Aktiengesellschaft Procede d'evacuation a regulation optimale, de refroidissement par impact et de scellage d'un ecran thermique et element d'ecran thermique associe
EP1813868A2 (fr) 2006-01-25 2007-08-01 Rolls-Royce plc Eléments de paroi de chambre de combustion de turbine à gaz
US20080166240A1 (en) 2007-01-04 2008-07-10 Siemens Power Generation, Inc. Advanced cooling method for combustion turbine airfoil fillets
US20080170946A1 (en) 2007-01-12 2008-07-17 General Electric Company Impingement cooled bucket shroud, turbine rotor incorporating the same, and cooling method
EP1983265A2 (fr) 2007-04-17 2008-10-22 Rolls-Royce Deutschland Ltd & Co KG Paroi de chambre de combustion de turbine à gaz
US7621718B1 (en) 2007-03-28 2009-11-24 Florida Turbine Technologies, Inc. Turbine vane with leading edge fillet region impingement cooling

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU1238465A2 (ru) * 1983-08-05 1996-02-27 Уфимский авиационный институт им.Серго Орджоникидзе Охлаждаемая лопатка турбины
US4719748A (en) 1985-05-14 1988-01-19 General Electric Company Impingement cooled transition duct
DE59912578D1 (de) * 1999-02-10 2005-10-27 Alstom Technology Ltd Baden Turbomaschinenschaufel
US7097418B2 (en) 2004-06-18 2006-08-29 Pratt & Whitney Canada Corp. Double impingement vane platform cooling
US7862291B2 (en) * 2007-02-08 2011-01-04 United Technologies Corporation Gas turbine engine component cooling scheme

Patent Citations (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2343673A1 (de) 1972-09-05 1974-03-14 Gen Electric Stiftrippen-kuehlsystem
US4712979A (en) 1985-11-13 1987-12-15 The United States Of America As Represented By The Secretary Of The Air Force Self-retained platform cooling plate for turbine vane
RU2009331C1 (ru) 1990-09-27 1994-03-15 Научно-производственное предприятие "Завод им.В.Я.Климова" Устройство для конвективного охлаждения деталей турбины
US5321951A (en) 1992-03-30 1994-06-21 General Electric Company Integral combustor splash plate and sleeve
WO1994012770A1 (fr) 1992-11-24 1994-06-09 United Technologies Corporation Aube de rotor a plate-forme d'un seul tenant avec ladite aube et passage de refroidissement du conge de raccordement
EP0889201A1 (fr) 1997-07-03 1999-01-07 Abb Research Ltd. Refroidissement d'une partie de paroi d'aube de turbine par jets d'air
US20020062945A1 (en) 1997-09-30 2002-05-30 Rainer Hocker Wall part acted upon by an impingement flow
US6402464B1 (en) 2000-08-29 2002-06-11 General Electric Company Enhanced heat transfer surface for cast-in-bump-covered cooling surfaces and methods of enhancing heat transfer
US20030039537A1 (en) 2001-08-27 2003-02-27 Itzel Gary Michael Method for controlling coolant flow in airfoil, flow control structure and airfoil incorporating the same
US6779597B2 (en) 2002-01-16 2004-08-24 General Electric Company Multiple impingement cooled structure
US20050175444A1 (en) 2004-02-09 2005-08-11 Siemens Westinghouse Power Corporation Cooling system for an airfoil vane
WO2006045758A1 (fr) 2004-10-25 2006-05-04 Siemens Aktiengesellschaft Procede d'evacuation a regulation optimale, de refroidissement par impact et de scellage d'un ecran thermique et element d'ecran thermique associe
EP1813868A2 (fr) 2006-01-25 2007-08-01 Rolls-Royce plc Eléments de paroi de chambre de combustion de turbine à gaz
US20080166240A1 (en) 2007-01-04 2008-07-10 Siemens Power Generation, Inc. Advanced cooling method for combustion turbine airfoil fillets
US20080170946A1 (en) 2007-01-12 2008-07-17 General Electric Company Impingement cooled bucket shroud, turbine rotor incorporating the same, and cooling method
US7621718B1 (en) 2007-03-28 2009-11-24 Florida Turbine Technologies, Inc. Turbine vane with leading edge fillet region impingement cooling
EP1983265A2 (fr) 2007-04-17 2008-10-22 Rolls-Royce Deutschland Ltd & Co KG Paroi de chambre de combustion de turbine à gaz

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
G.E. ANDREWS ET AL.: "Proceedings of ASME Turbo Expo 2004 GT2004-54184", ENHANCED IMPINGEMENT HEAT TRANSFER: THE INFLUENCE OF IMPINGEMENT X/D FOR INTERRUPTED RIB OBSTACLES (RECTANGULAR PIN FINS), 14 June 2004 (2004-06-14), Vienna , Austria, pages 1 - 13, XP055476624

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11739935B1 (en) 2022-03-23 2023-08-29 General Electric Company Dome structure providing a dome-deflector cavity with counter-swirled airflow

Also Published As

Publication number Publication date
US20120020768A1 (en) 2012-01-26
US8444376B2 (en) 2013-05-21
RU2011135942A (ru) 2013-03-10
CH700319A1 (de) 2010-07-30
RU2539950C2 (ru) 2015-01-27
WO2010086381A1 (fr) 2010-08-05
EP2384392A1 (fr) 2011-11-09
EP2384392B2 (fr) 2024-09-04

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