EP2299056A1 - Refroidissement d'un composant de turbine à gaz sous la forme d'un disque de rotor ou d'une aube - Google Patents

Refroidissement d'un composant de turbine à gaz sous la forme d'un disque de rotor ou d'une aube Download PDF

Info

Publication number
EP2299056A1
EP2299056A1 EP09011282A EP09011282A EP2299056A1 EP 2299056 A1 EP2299056 A1 EP 2299056A1 EP 09011282 A EP09011282 A EP 09011282A EP 09011282 A EP09011282 A EP 09011282A EP 2299056 A1 EP2299056 A1 EP 2299056A1
Authority
EP
European Patent Office
Prior art keywords
channel
groove
gas turbine
blade
recess
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Withdrawn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
EP09011282A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmed
Harald Hoell
Karsten Dr. Kolk
Harald Nimptsch
Werner Dr. Setz
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.)
Siemens AG
Original Assignee
Siemens AG
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 AG filed Critical Siemens AG
Priority to EP09011282A priority Critical patent/EP2299056A1/fr
Priority to PCT/EP2010/062880 priority patent/WO2011026903A1/fr
Priority to JP2012526086A priority patent/JP2013503289A/ja
Priority to EP10751650A priority patent/EP2473710A1/fr
Priority to US13/392,927 priority patent/US8956116B2/en
Priority to CN201080039240.2A priority patent/CN102482944B/zh
Priority to RU2012112591/06A priority patent/RU2547354C2/ru
Publication of EP2299056A1 publication Critical patent/EP2299056A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • 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
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • the invention relates to a gas turbine component with at least one opening in a surface channel.
  • gas turbine component mentioned at the outset can be understood as meaning, for example, a turbine blade with cooling air openings which open in the surface of the turbine blade around which hot gas flows, for example as film cooling openings.
  • a gas turbine component in the sense of the present patent application is understood to mean a rotor disk for a gas turbine, in which mostly radial bores for the passage of air are arranged.
  • Turbine guide vane carriers known from the prior art also have channels for the passage of cooling air used later for cooling, which open in its surface.
  • the object of the invention is therefore to provide a reliable gas turbine component with extended life.
  • the invention provides that in the surface next to the mouth, d. H. close to the action, at least one groove-like recess for lowering the concentration of stress is present.
  • grooves according to the invention which represent blindly ending recesses, the stress concentration in the immediate vicinity of the channel section opening into the surface is reduced.
  • material fatigue is reduced due to cyclic load changes and thus the risk of fatigue cracking. If cracks actually occur, their growth is slowed down accordingly. Consequently, the gas turbine component according to the invention has the desired service life extension.
  • the gas turbine component is designed as a rotor disk for a gas turbine.
  • the rotor disk is formed as a turbine disk and has a number of distributed along the circumference retaining grooves for blades whose walls have surface and wherein at least one of the in the respective Surface opening channels in each case the at least one groove-like recess is arranged.
  • the gas turbine component is designed as a turbine blade with a number of opening in a surface to be flowed by hot gas channels, of which at least one of the channels next to its orifice in the surface has the at least one groove-like recess for reducing the concentration of stress.
  • the arrangement according to the invention thus lends itself, on the one hand, to rotor disks in which bores are present for the passage of cooling air.
  • rotor disks in which bores are present for the passage of cooling air.
  • These may be turbine disks, on the outer circumference of which turbine rotor blades are inserted into corresponding retaining grooves, or they may also be compressor disks which are used to remove compressor air in the compressor-side section of the rotor.
  • the invention is particularly advantageously applied in turbine blades, in which mostly cylindrical cooling air outlet openings open in a surface which can be flowed around by hot gas. Since, in particular, the cooling channel outlets arranged in an inflow edge of the blade of a turbine blade are exposed to the highest thermal stresses, it is advisable to protect them from crack formation using the groove-like recess according to the invention and to slow down the growth of cracks that have developed.
  • the at least one channel for guiding coolant is formed as a bore.
  • An advantageous embodiment of the rotor disk has two recesses which are arranged on both sides of the channel opening in the case of a cross-sectional view made perpendicular to the axis of rotation of the rotor disk.
  • the retaining grooves in which the blades of the gas turbine are used are, have walls, on the one hand a groove base and on the other two opposite, at least partially corrugated to the outer edge of the rotor disc extending flank surfaces, wherein in the transition from the groove base to the respective flank surface each one of the recesses is arranged.
  • the recesses can be arbitrary in their contour.
  • the contour is mainly rectangular, but with rounded corners between the side walls.
  • the transition of the side walls of the recess to the bottom surface is rounded. Both serve to reduce and avoid notch stresses.
  • the groove-like recess may be formed as an endless groove which engages around the mouth of the respective channel. More preferably, the endless groove is arranged circular and concentric with the mouth portion of the respective channel. In particular, two, possibly more grooves are arranged concentrically around the mouth portion of the respective channel, which may also have different groove depths. If the groove-like recess is designed as an endless groove, it can be used particularly preferably in the rotor disk and in the turbine blade. Of course, instead of a circular endless groove, this can also be elliptical.
  • the invention specifies a gas turbine component with an extended service life.
  • the service life extension is achieved by means of a voltage reduction in those areas of the gas turbine component which, due to a channel arranged there, could have an unacceptably high stress concentration for this area.
  • the operating risk of a gas turbine equipped with the component is also minimized since cracks rarely occur in the component.
  • a turbine blade 2 after FIG. 1 is designed as a guide vane for a gas turbine not shown here. It comprises a foot section 4 and a tip section 6 with associated platforms 8, 10 and an intermediate airfoil 12 extending in the longitudinal direction L.
  • the aerodynamically curved airfoil 12 has a leading edge 14 which also extends substantially in the longitudinal direction L and a trailing edge 16 intermediate side walls 18.
  • the turbine blade 2 is fixed via the foot section 4 to the inner casing of the turbine, wherein the associated platform 8 forms a wall element bounding the flow path of the hot gas in the gas turbine.
  • the turbine-shaft-facing tip-side platform 10 forms another boundary for the flowing hot gas.
  • the turbine blade 2 could also be designed as a rotor blade, which is fastened in an analogous manner to a rotor disk of the turbine shaft via a foot-side platform 8, also referred to as a blade root.
  • a coolant K is introduced into the blade interior via a number of inlet openings 20 arranged at the lower end of the foot section 4.
  • the coolant K is cooling air.
  • the coolant K After the coolant K has flowed through one or more coolant channels 22 adjoining the inlet openings 20 in the interior of the turbine blade 2, it exits at a number of exit openings 24, also referred to as film cooling holes, corresponding to the coolant channels 22 in the area of the blade 12.
  • film cooling holes also referred to as film cooling holes
  • FIG. 2 shows the front portion of the profiled airfoil 12 in cross-section along the section line II-II FIG. 1 in which the front edge region 28 comprising the front edge 14 adjoins the pressure side 30 and the suction side 32.
  • coolant channel 22 From a substantially in the longitudinal direction L of the turbine blade 2 extending, spaced from the front edge 14 coolant channel 22 branch off outlet channels 34 of smaller cross section, which penetrate the blade wall 36 and open in the leading edge region 28 in outlet openings 24 or film cooling holes.
  • coolant K By the flow through the outlet channels 34 with coolant K, a convective cooling of the adjacent areas of the blade wall is achieved.
  • the film cooling effect caused by the cooling air flowing out of the outlet openings 24 impinges on the surface 37 of the blade 12.
  • an air cushion or a protective film which prevents direct contact with the blade surface 37 with the high flow velocity having hot gas.
  • the groove-shaped recesses 40 are formed as endless grooves which are arranged concentrically to the outlet channel 34 opening into the surface 37.
  • two concentric endless grooves may each be arranged around an outlet channel 34, which is exemplified, for example, at the channel designated 42.
  • FIG. 3 shows as a further gas turbine component a section of a perspective view of a rotor disk 50.
  • the rotor disk 50 is provided as a turbine disk in a known manner with a number of retaining grooves 52 which are distributed on the lateral surface 54 of the rotor disk 50 along the circumference at regular intervals.
  • the retaining groove 52 is open radially outward and additionally has in each case lateral openings which are provided in the end faces of the rotor disk 50.
  • the end-side, contemplated in cross-section contour of the retaining groove 52 corresponds substantially to a Christmas tree shape, with other forms are known and can be used.
  • In the Holding grooves 52 are blades of the turbine of a gas turbine can be used, wherein the corresponding blades to the contour of the retaining groove 52 have correspondingly shaped blade roots.
  • Each retaining groove 52 thus has walls with surfaces.
  • the surface can be subdivided into a base side surface 58 and in two arranged on the flanks of the retaining side surfaces 60, 62, the transition laterally join the groove base 58. Since, as a rule, the turbine blades used in the retaining grooves 52 must be cooled during operation in the gas turbine, these are supplied via the blade root cooling air.
  • a channel 64 is provided in the rotor disk 50, which opens into the groove base 58 of the retaining groove 52.
  • the blades inserted in the retaining grooves 52 have inlet openings for cooling air on their surface opposite the groove base 58 in order to allow the cooling air supplied via the channel 64 to enter the rotor blades. In the blade takes place in a known, for the invention but in an unimportant manner, the cooling of the blade and / or belonging to the blade platform.
  • a groove-like recess 66 are respectively arranged in the two passages between groove bottom 58 and side surfaces 60, 62.
  • the recesses 66 are placed in such a way that, in the case of a cross-sectional view made perpendicular to the axis of rotation of the rotor disk 50, they are arranged on both sides of the channel opening.
  • the two recesses 66 are thus viewed in the circumferential direction of the rotor disc on both sides of the channel mouth.
  • a gas turbine component 2, 50 for example, a turbine blade 2 or a rotor disk 50 indicated for a gas turbine, in extending the life of the corresponding component 2, 50 by reducing the thermally or mechanically induced stress concentration in the immediate vicinity of a in a Surface 37, 58 opening channel 34, 64 at least one groove-like recess 40, 66 is present in the vicinity of the impact point.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP09011282A 2009-09-02 2009-09-02 Refroidissement d'un composant de turbine à gaz sous la forme d'un disque de rotor ou d'une aube Withdrawn EP2299056A1 (fr)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP09011282A EP2299056A1 (fr) 2009-09-02 2009-09-02 Refroidissement d'un composant de turbine à gaz sous la forme d'un disque de rotor ou d'une aube
PCT/EP2010/062880 WO2011026903A1 (fr) 2009-09-02 2010-09-02 Refroidissement d'un composant de turbine à gaz conçu comme disque rotor ou aube de turbine
JP2012526086A JP2013503289A (ja) 2009-09-02 2010-09-02 ロータディスクまたはタービンブレードとして設計されたガスタービン要素の冷却
EP10751650A EP2473710A1 (fr) 2009-09-02 2010-09-02 Refroidissement d'un composant de turbine à gaz conçu comme disque rotor ou aube de turbine
US13/392,927 US8956116B2 (en) 2009-09-02 2010-09-02 Cooling of a gas turbine component designed as a rotor disk or turbine blade
CN201080039240.2A CN102482944B (zh) 2009-09-02 2010-09-02 构成为转子盘或者涡轮叶片的燃气轮机构件的冷却
RU2012112591/06A RU2547354C2 (ru) 2009-09-02 2010-09-02 Охлаждение конструктивного элемента газовой турбины, выполненного в виде диска ротора или лопатки турбины

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09011282A EP2299056A1 (fr) 2009-09-02 2009-09-02 Refroidissement d'un composant de turbine à gaz sous la forme d'un disque de rotor ou d'une aube

Publications (1)

Publication Number Publication Date
EP2299056A1 true EP2299056A1 (fr) 2011-03-23

Family

ID=41580998

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09011282A Withdrawn EP2299056A1 (fr) 2009-09-02 2009-09-02 Refroidissement d'un composant de turbine à gaz sous la forme d'un disque de rotor ou d'une aube
EP10751650A Withdrawn EP2473710A1 (fr) 2009-09-02 2010-09-02 Refroidissement d'un composant de turbine à gaz conçu comme disque rotor ou aube de turbine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP10751650A Withdrawn EP2473710A1 (fr) 2009-09-02 2010-09-02 Refroidissement d'un composant de turbine à gaz conçu comme disque rotor ou aube de turbine

Country Status (6)

Country Link
US (1) US8956116B2 (fr)
EP (2) EP2299056A1 (fr)
JP (1) JP2013503289A (fr)
CN (1) CN102482944B (fr)
RU (1) RU2547354C2 (fr)
WO (1) WO2011026903A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3054855A1 (fr) * 2016-08-08 2018-02-09 Safran Aircraft Engines Disque de rotor de turbomachine

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2949871B1 (fr) * 2014-05-07 2017-03-01 United Technologies Corporation Segment d'aube variable
US20160298464A1 (en) * 2015-04-13 2016-10-13 United Technologies Corporation Cooling hole patterned airfoil
KR102028804B1 (ko) * 2017-10-19 2019-10-04 두산중공업 주식회사 가스 터빈 디스크
CN109030012B (zh) * 2018-08-24 2024-01-23 哈尔滨电气股份有限公司 一种带有冷却通道的透平叶根疲劳试验模拟件及试验方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2010022A (en) * 1931-06-27 1935-08-06 Holzwarth Gas Turbine Co Cooling of gas turbine blades
US5653110A (en) * 1991-07-22 1997-08-05 General Electric Company Film cooling of jet engine components
WO2003062607A1 (fr) * 2002-01-25 2003-07-31 Alstom (Switzerland) Ltd Élément refroidi pour turbine à gaz
GB2438861A (en) * 2006-06-07 2007-12-12 Rolls Royce Plc Film-cooled component, eg gas turbine engine blade or vane

Family Cites Families (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2085788A (en) 1936-03-14 1937-07-06 Robert S Briggs Clothes drying apparatus
JPS5349609A (en) 1976-10-19 1978-05-06 Nissan Diesel Motor Co Ltd Turbulent type combustion chamber
US4344738A (en) * 1979-12-17 1982-08-17 United Technologies Corporation Rotor disk structure
JPS56168327A (en) 1980-05-30 1981-12-24 Hitachi Ltd Hollow cathode for secondary ion mass spectroscope
JPS5870439U (ja) * 1981-11-06 1983-05-13 マツダ株式会社 エンジンのシリンダブロツク
JPS6025740U (ja) * 1983-07-22 1985-02-21 後藤合金株式会社 製鋼用ランスノズル
JPS6025740A (ja) 1983-07-22 1985-02-08 東京シ−ト株式会社 クッションフォームに対するシート表皮の組付方法
US4676719A (en) 1985-12-23 1987-06-30 United Technologies Corporation Film coolant passages for cast hollow airfoils
JP2753234B2 (ja) * 1987-10-23 1998-05-18 財団法人電力中央研究所 セラミック静翼
JPH02154919A (ja) 1988-12-07 1990-06-14 Hitachi Ltd 遮熱圧力隔壁
JP3269817B2 (ja) 1990-09-20 2002-04-02 富士通株式会社 入出力制御装置
US5152657A (en) 1991-04-08 1992-10-06 Kehne Lewis F Boat trailer attachment
US5152667A (en) * 1991-07-16 1992-10-06 General Motors Corporation Cooled wall structure especially for gas turbine engines
US5779437A (en) * 1996-10-31 1998-07-14 Pratt & Whitney Canada Inc. Cooling passages for airfoil leading edge
JPH10299408A (ja) 1997-04-22 1998-11-10 Hitachi Ltd ガスタービン静翼
JPH1113406A (ja) 1997-06-23 1999-01-19 Hitachi Ltd ガスタービン静翼
JPH1110809A (ja) 1997-06-24 1999-01-19 Mitsui Chem Inc 包装用フィルム
EP0924384A3 (fr) * 1997-12-17 2000-08-23 United Technologies Corporation Refroidissement de l'arête amont d'une aube pour une turbomachine
US6132204A (en) * 1998-06-30 2000-10-17 Praxair Technology, Inc. Wide flame burner
US6237344B1 (en) * 1998-07-20 2001-05-29 General Electric Company Dimpled impingement baffle
US6176646B1 (en) * 1998-10-23 2001-01-23 Deep Oil Technology, Incorporated Riser guide and support mechanism
US6183202B1 (en) * 1999-04-30 2001-02-06 General Electric Company Stress relieved blade support
JP2000329493A (ja) 1999-05-20 2000-11-30 Toyo Radiator Co Ltd 積層型熱交換器
AU2001232891A1 (en) 2000-02-03 2001-08-14 Corning Incorporated Refractory burner nozzle with stress relief slits
CA2334071C (fr) * 2000-02-23 2005-05-24 Mitsubishi Heavy Industries, Ltd. Aube mobile de turbine a gaz
JP2001234703A (ja) 2000-02-23 2001-08-31 Mitsubishi Heavy Ind Ltd ガスタービン動翼
JP2002205161A (ja) 2000-12-28 2002-07-23 Kurosaki Harima Corp スライディングノズルプレートれんがの欠け防止構造
JP2002206161A (ja) 2001-01-09 2002-07-26 Citizen Watch Co Ltd 装飾成形部材およびその製造方法
US6547524B2 (en) * 2001-05-21 2003-04-15 United Technologies Corporation Film cooled article with improved temperature tolerance
US6491498B1 (en) 2001-10-04 2002-12-10 Power Systems Mfg, Llc. Turbine blade pocket shroud
US6955522B2 (en) 2003-04-07 2005-10-18 United Technologies Corporation Method and apparatus for cooling an airfoil
DE50306044D1 (de) * 2003-09-05 2007-02-01 Siemens Ag Schaufel einer Turbine
US7147440B2 (en) 2003-10-31 2006-12-12 General Electric Company Methods and apparatus for cooling gas turbine engine rotor assemblies
RU2323343C2 (ru) 2006-03-20 2008-04-27 Федеральное государственное унитарное предприятие "Московское машиностроительное производственное предприятие "САЛЮТ" (ФГУП "ММПП "САЛЮТ") Охлаждаемая лопатка турбомашины
FR2911632B1 (fr) * 2007-01-18 2009-08-21 Snecma Sa Disque de rotor de soufflante de turbomachine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2010022A (en) * 1931-06-27 1935-08-06 Holzwarth Gas Turbine Co Cooling of gas turbine blades
US5653110A (en) * 1991-07-22 1997-08-05 General Electric Company Film cooling of jet engine components
WO2003062607A1 (fr) * 2002-01-25 2003-07-31 Alstom (Switzerland) Ltd Élément refroidi pour turbine à gaz
GB2438861A (en) * 2006-06-07 2007-12-12 Rolls Royce Plc Film-cooled component, eg gas turbine engine blade or vane

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3054855A1 (fr) * 2016-08-08 2018-02-09 Safran Aircraft Engines Disque de rotor de turbomachine
US10954795B2 (en) 2016-08-08 2021-03-23 Safran Aircraft Engines Turbo engine rotor disc

Also Published As

Publication number Publication date
JP2013503289A (ja) 2013-01-31
US8956116B2 (en) 2015-02-17
EP2473710A1 (fr) 2012-07-11
WO2011026903A1 (fr) 2011-03-10
RU2547354C2 (ru) 2015-04-10
CN102482944A (zh) 2012-05-30
CN102482944B (zh) 2016-01-27
RU2012112591A (ru) 2013-10-10
US20120207615A1 (en) 2012-08-16

Similar Documents

Publication Publication Date Title
EP1907670B1 (fr) Aube de turbine refroidie pour turbine a gaz et utilisation d'une aube de turbine de ce type
EP1757773B1 (fr) Aube creuse de turbine
EP1740797B1 (fr) Turbine a gaz
DE60018817T2 (de) Gekühlte Gasturbinenschaufel
DE602005000350T2 (de) Turbinenstatorschaufel mit verbesserter Kühlung
EP3056683B1 (fr) Bague intérieure séparée axialement pour une turbomachine et stator
EP1766192B1 (fr) Roue a aubes d'une turbine presentant une aube et au moins un canal refrigerant
EP3121373B1 (fr) Roue de turbine refroidie, plus particulièrement pour un réacteur
EP1219781A2 (fr) Dispositif et méthode de refroidissement d'une plate-forme d'une aube de turbine
EP1848904B1 (fr) Element d'etancheite s'utilisant dans une turbomachine
EP2299056A1 (fr) Refroidissement d'un composant de turbine à gaz sous la forme d'un disque de rotor ou d'une aube
DE102007037208B4 (de) Turbinenschaufel mit zumindest einer Einsatzhülse zum Kühlen der Turbinenschaufel
EP3056677B1 (fr) Aube et turbomachine
EP3762587B1 (fr) Pale d'aube pour une aube de turbine
EP1905950A1 (fr) Aube de turbine
EP3473808B1 (fr) Pale d'aube pour une aube mobile de turbine à refroidissement intérieur ainsi que procédé de fabrication d'une telle pale
EP2411630B1 (fr) Rotor de turbomachine axiale doté d'un refroidissement d'aube
EP1857635A1 (fr) Aube de turbine pour une turbine à gaz
DE19940556B4 (de) Vorrichtung zum Kühlen von Leit- oder Laufschaufeln in einer Gasturbine
EP2860356B1 (fr) Turbomachine
EP3039246B1 (fr) Aube de turbine
EP1016773B1 (fr) Aube de turbine refroidissable
DE19856199A1 (de) Kühlung in Gasturbinen
EP3623576B1 (fr) Aube de turbine à gaz
DE102008029528A1 (de) Vorrichtung zur Gasführung zwischen Rotorscheiben eines Verdichters

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR

AX Request for extension of the european patent

Extension state: AL BA RS

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20110924