EP1251243B1 - Turbinenschaufel mit Kühlluftleiteinrichtung - Google Patents

Turbinenschaufel mit Kühlluftleiteinrichtung Download PDF

Info

Publication number
EP1251243B1
EP1251243B1 EP02290964A EP02290964A EP1251243B1 EP 1251243 B1 EP1251243 B1 EP 1251243B1 EP 02290964 A EP02290964 A EP 02290964A EP 02290964 A EP02290964 A EP 02290964A EP 1251243 B1 EP1251243 B1 EP 1251243B1
Authority
EP
European Patent Office
Prior art keywords
cooling
blade
air
turbine
deflector
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.)
Expired - Lifetime
Application number
EP02290964A
Other languages
English (en)
French (fr)
Other versions
EP1251243A1 (de
EP1251243B8 (de
Inventor
Morgan Lionel Balland
Sylvie Coulon
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Moteurs SA
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 SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP1251243A1 publication Critical patent/EP1251243A1/de
Application granted granted Critical
Publication of EP1251243B1 publication Critical patent/EP1251243B1/de
Publication of EP1251243B8 publication Critical patent/EP1251243B8/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/12—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
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Definitions

  • the present invention relates to a dawn for turbine, the dawn being reported on a disk of the turbine and being cooled by a circulation internal air.
  • An axial turbine stage is composed a vanes grid called distributor and a mobile blade grid called a wheel. It exists monobloc wheels where blades and disc form a unique piece. There are also paddle wheels reported where blades and disk are assembled mechanically, usually by feet of fir.
  • Figure 1A is a partial view of a dawn 1 mounted on a disk 2, the view being represented in a plane perpendicular to the axis of the turbine. It shows more precisely the foot 3 of the dawn 1 in position in a cell 4 of the disk 2. The foot is shown in section along the axis of a channel 5 bringing the air cooling from the bottom of the cell 4 to the internal cooling circuit and not represented from dawn. Cooling air circulates in the cell 4 in a direction perpendicular to the plane of the figure. In the example shown, the air is introduced by one end of the cell, corresponding on one side of the so-called upstream face disc, and goes up in the channel (or channels) 5, the other end of the cell, corresponding to the other side of the disk or downstream face, being closed.
  • the cooling air taken from the compressor output is injected through a flange pressed against the upstream face of the disc for seal the air circuit.
  • the flange is often kept on the disc by a system of hooks called jabots.
  • the hooks also provide another function. They give the cooling air itself directing to the cells a rotational speed equal to that of the rotor of the turbine. Looks like cooling then arrives in front of the cell in turning at the same speed as she and enters at inside the cell without side effects.
  • WO-A-99 47792 discloses a dawn for turbine, the blade having a foot allowing bring it back into a cell of a disk of the turbine.
  • Dawn has an internal circuit of air cooling comprising inlet means of air located on the foot of the dawn and next to the cell, and air outlet means.
  • the foot of the dawn is provided with a device allowing channel the cooling air of the dawn. This device also allows the evacuation of air from cooling after it's passed inside of dawn. The device ensures the separation of the circuits cooling air entering the dawn and coming out of dawn.
  • GB-A-1 605 282 discloses a dawn for turbine, the dawn having a foot allowing to bring it back into a cell of a disk of the turbine.
  • Dawn has an internal circuit of air cooling consisting of channels, comprising air inlet means located on the foot dawn and next to the alveolus, and means of air outlet located at the end of the blade.
  • the foot of the dawn is provided with a cooling tube to bring the cooling air from the suction air manifold to the air inlets.
  • US-A-4 348 157 discloses a dawn for turbine, reported on a disk by means of a foot.
  • Dawn has an internal circuit of air cooling comprising an inlet port air.
  • the air inlet is not located on the foot of dawn and next to the receiving cell of this foot but in the connecting part between the foot and dawn, that is, in the leg.
  • Passages are provided to bring cooling air to the air intakes of the blades. These passages can understand deflectors.
  • US-A-4 178 129 discloses a system cooling turbine blades by circulation air. Each dawn has a foot allowing the bring into a cell a disc of the turbine. Dawn has an internal cooling circuit by air comprising air inlet means located on the foot of dawn. The cooling air is sent either in an air supply chamber of cooling in which the channels of cooling, either directly in the edge channel attacking through a Pitot receiver.
  • incoming cooling air is brought in by a tube-shaped device communicating with the orifices of the cooling channels.
  • the device shaped tube can have size orifices suitable for the openings of the channels or orifices corresponding substantially to the width of the cell. In both cases, one can not avoid the formation of a whirlwind.
  • an air cooling tube is provided adapted to the width of the cell. We can not avoid the formation of a whirlpool.
  • Figure 1B illustrates the phenomenon causing a loss of effectiveness of the blade cooling.
  • This figure is a view of the underside of the foot 3 and bearing the reference 6 in Figure 1A.
  • the channel (or channels) 5 does not have been represented.
  • the flange pressed against the upstream face The disc is shown as 7.
  • Under the reference 8 was figured a flange shutter the cell, side downstream side of the disc.
  • the inventors came to the conclusion that when the air is no longer guided to the cell, the cooling air arrives in the cell with a rotation speed lower than when it is guided. The air is then scooped and whirls in the cell by forming a whirlwind as shown on the Figure 1B.
  • the center of this whirlpool (or vortex) is a very large pressure dip that's detrimental to the dawn feeding in air from cooling.
  • the present invention makes it possible to remedy this problem whenever it comes in a turbine.
  • a turbine blade dawn with a foot to bring it back in a cell of a disk of the turbine, dawn having an internal air cooling circuit comprising air inlet means located on a face of the foot of the dawn and facing said cell, and air outlet means, characterized in that said face of the foot of the dawn is equipped with a deflector comprising at least one fin allowing to channel the cooling air circulating in the bottom of the cell to regulate the flow of air to the air inlet means.
  • the deflector can be an integral part of dawn.
  • the deflector may be a reported element on the foot of dawn and provided with means of access to air inlet means.
  • the means of access may include at least one calibrated hole.
  • the winglet can be straight or inclined by relation to the general axis of dawn.
  • the deflector comprises at least one fin allowing channel cooling air penetrating into the cell and at least one fin allowing channel repressed air towards the center of the cell.
  • Figure 2A is a view of a dawn 11 according to the invention and mounted on a disk 12, the view being represented in a plane perpendicular to the axis of the turbine as for Figure 1A.
  • The: foot 13 of the dawn 11 is in position in a cell 14 of the disk 12.
  • the foot is shown in section along the axis of a canal 15 bringing the cooling air from the bottom of cell 14 to the cooling circuit internal and not represented at dawn.
  • the circulation of the air in the cell is as described previously for Figure 1A.
  • the blade of FIG. 2A is equipped with a deflector 20 secured to the lower face 16 of the dawn foot.
  • the deflector 20 has fins to channel the cooling air circulating in the bottom of the cell 14.
  • Figure 2A shows that the deflector has a hole 21 in correspondence with channel 15 and serving as channel access for cooling air. This hole can be a calibrated hole whose realization is easy to get on a piece such as a baffle reported.
  • FIG 2B corresponding to Figure 1B for the prior art, shows by arrows which way is channeled the cooling air to the bottom of the cell between the flanges 17 and 18 of the disc 12.
  • the deflector is equipped with two fins 22 and 23 located on either side of the axis of alignment of the holes 21.
  • the fins are arranged so as to form a species of chicane.
  • the baffle shown has four holes for the passage of air from cooling.
  • the deflector can be a patch by welding or brazing on the blade root. In a variant, the deflector can be an integral part of dawn.
  • Figure 3 is a perspective view of deflector 20 mentioned above. This figure allows to better see the fins 22 and 23 as well as the holes 21.
  • FIG. 4 is a partial sectional view a turbine equipped with a blade according to the invention.
  • the FIG. 4 shows a blade 11 equipped with a deflector 20 and mounted in a cavity 14 of the disc 12.
  • figure can also see flange 17 plated against the upstream face of the disk 12 and the flange 18 shutter of the cell.
  • the cooling air is taken in chamber background and accelerated through a series injectors such as the injector 31. This air passes then through holes, such as hole 32, pierced on the flask 17 and goes back to the funds of alveoli as indicated by arrows on the Figure 4. In broken lines, the hooks or claws that the invention allows to remove.
  • Figures 5 and 6 show, in position on the underside of a dawn foot, others forms of deflectors usable by this invention.
  • the deflector 40 comprises two fins 41 and 42 present along the entire length of the deflector. Holes 43 for access to the channels of blades are also represented.
  • the deflector 50 comprises a first series of fins 51 and 53, located in a side of the baffle, and a second set of fins 52 and 54, located on the other side of the baffle.
  • the fins are arranged to form baffles. of the 55 holes access to the channels of the vanes are also represented.
  • the deflector may also include one or several fins curved shape and allowing a guiding the cooling air along a path more evolutionary.
  • Figures 7 to 10 give, as examples, other forms of usable deflectors by the present invention. All these views are cross-sectional representations made according to a hole for the passage of cooling air.
  • the deflector 60 of FIG. rail shape It has fins 61 and 62 arranged at right angles to the support face 63 of the deflector on the dawn foot.
  • the fins 61 and 62 can run the full length of the baffle or be interrupted to form baffles.
  • the deflector 70 has fins 71 and 72 which flare in relation to the bearing face 73 of the deflector on the dawn foot.
  • the baffle 80 has fins 81 and 82 which are going to closer to the bearing face 83 of the deflector on the dawn foot.
  • the baffle 90 includes four parallel fins 91, 92, 93 and 94 arranged at right angles to the support face 95 of the deflector on the dawn foot.
  • the invention makes it possible to obtain a gain of static pressure in the center of the cell that fills at about 75% the pressure dip existing without the layout brought.
  • This improvement of dawn feeding in cooling air helps reduce the average temperature of dawn according to the operating conditions and to increase as a result its lifespan.

Landscapes

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

Claims (8)

  1. Kühlungsvorrichtung für eine Turbinenschaufel, die eine Schaufel (11), eine Scheibe (12) umfasst, wobei die Schaufel einen Fuß (13) aufweist, mittels dessen sie in einer Zelle (14) der Scheibe (12) der Turbine eingebaut werden kann, wobei die Schaufel einen inneren Luft-Kühlungskreislauf besitzt, der Lufteinlassmittel (15) aufweist, die sich an einer Seite des Fußes der Schaufel gegenüber dieser Zelle befinden, und Laufauslassmittel aufweist, wobei diese Seite des Schaufelfußes mit einer Ablenkeinrichtung (20) versehen ist, die eine Rippe (22, 23) enthält,
       dadurch gekennzeichnet,    dass sich die Rippe auf der einen Seite oder der anderen Seite der Ausrichtachse der Lufteinlassmittel (15) befindet.
  2. Kühlungsvorrichtung für eine Turbinenschaufel, die eine Schaufel (11), eine Scheibe (12) umfasst, wobei die Schaufel einen Fuß (13) aufweist, mittels dessen sie in einer Zelle (14) der Scheibe (12) der Turbine eingebaut werden kann, wobei die Schaufel einen inneren Luft-Kühlungskreislauf besitzt, der Lufteinlassmittel (15) aufweist, die sich an einer Seite des Fußes der Schaufel gegenüber dieser Zelle befinden, und Laufauslassmittel aufweist, wobei diese Seite des Schaufelfußes mit einer Ablenkeinrichtung (20) versehen ist, die mindestens zwei Rippen (22, 23) enthält,
       dadurch gekennzeichnet,    dass sich die Rippen beiderseits der Ausrichtachse der Lufteinlassmittel (15) befinden.
  3. Kühlungsvorrichtung für eine Turbinenschaufel nach einem der Ansprüche 1 oder 2,
       dadurch gekennzeichnet,    dass die Ablenkeinrichtung einen integrierenden Bestandteil der Schaufel bildet.
  4. Kühlungsvorrichtung für eine Turbinenschaufel nach einem der Ansprüche 1 oder 2,
       dadurch gekennzeichnet,    dass die Ablenkeinrichtung (20) ein an den Fuß (13) der Schaufel (11) angebautes Element ist und mit Zugangsmitteln (21) zu den Lufteinlassmitteln (15) versehen ist.
  5. Kühlungsvorrichtung für eine Turbinenschaufel nach Anspruch 4,
       dadurch gekennzeichnet,    dass die Zugangsmittel (21) mindestens ein kalibriertes Loch umfassen.
  6. Kühlungsvorrichtung für eine Turbinenschaufel nach einem der Ansprüche 1 bis 5,
       dadurch gekennzeichnet,    dass diese Rippe (22, 23) gerade oder zur Hauptachse der Schaufel geneigt ausgeführt ist.
  7. Kühlungsvorrichtung für eine Turbinenschaufel nach einem der Ansprüche 1 bis 6,
       dadurch gekennzeichnet,    dass die Ablenkeinrichtung (20) mindestens eine Rippe (22) umfasst, mit der die in die Zelle eintretende Kühlungsluft kanalisiert werden kann, sowie mindestens eine Rippe (23), mit der die zum Zentrum der Zelle strömende Luft kanalisiert werden kann.
  8. Kühlungsvorrichtung für eine Turbinenschaufel nach einem der Ansprüche 1 bis 7,
       dadurch gekennzeichnet,    dass die Ablenkeinrichtung mindestens eine gebogene Rippe umfasst.
EP02290964A 2001-04-19 2002-04-17 Turbinenschaufel mit Kühlluftleiteinrichtung Expired - Lifetime EP1251243B8 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0105289 2001-04-19
FR0105289A FR2823794B1 (fr) 2001-04-19 2001-04-19 Aube rapportee et refroidie pour turbine

Publications (3)

Publication Number Publication Date
EP1251243A1 EP1251243A1 (de) 2002-10-23
EP1251243B1 true EP1251243B1 (de) 2005-09-07
EP1251243B8 EP1251243B8 (de) 2005-11-02

Family

ID=8862464

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02290964A Expired - Lifetime EP1251243B8 (de) 2001-04-19 2002-04-17 Turbinenschaufel mit Kühlluftleiteinrichtung

Country Status (10)

Country Link
US (1) US6981845B2 (de)
EP (1) EP1251243B8 (de)
JP (1) JP4112986B2 (de)
CA (1) CA2444862C (de)
DE (1) DE60205977T2 (de)
ES (1) ES2244738T3 (de)
FR (1) FR2823794B1 (de)
RU (1) RU2325537C2 (de)
UA (1) UA73655C2 (de)
WO (1) WO2002086291A1 (de)

Families Citing this family (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0227745D0 (en) * 2002-11-28 2003-01-08 Rolls Royce Plc Blade cooling
US6974306B2 (en) * 2003-07-28 2005-12-13 Pratt & Whitney Canada Corp. Blade inlet cooling flow deflector apparatus and method
FR2858829B1 (fr) * 2003-08-12 2008-03-14 Snecma Moteurs Aube refroidie de moteur a turbine a gaz
GB0405679D0 (en) * 2004-03-13 2004-04-21 Rolls Royce Plc A mounting arrangement for turbine blades
ES2337800T3 (es) 2004-03-30 2010-04-29 Alstom Technology Ltd Dispositivo para la presurizacion de aire de refrigeracion en un alabe de rodete.
US7578652B2 (en) * 2006-10-03 2009-08-25 United Technologies Corporation Hybrid vapor and film cooled turbine blade
SG143087A1 (en) * 2006-11-21 2008-06-27 Turbine Overhaul Services Pte Laser fillet welding
US20090068446A1 (en) 2007-04-30 2009-03-12 United Technologies Corporation Layered structures with integral brazing materials
US8128365B2 (en) 2007-07-09 2012-03-06 Siemens Energy, Inc. Turbine airfoil cooling system with rotor impingement cooling
FR2937372B1 (fr) * 2008-10-22 2010-12-10 Snecma Aube de turbine equipee de moyens de reglage de son debit de fluide de refroidissement
WO2011026503A1 (en) 2009-09-04 2011-03-10 Siemens Aktiengesellschaft A method and a device of tangentially biasing internal cooling on nozzle guide vane
US8622702B1 (en) * 2010-04-21 2014-01-07 Florida Turbine Technologies, Inc. Turbine blade with cooling air inlet holes
GB201016597D0 (en) 2010-10-04 2010-11-17 Rolls Royce Plc Turbine disc cooling arrangement
IT1403416B1 (it) * 2010-12-21 2013-10-17 Avio Spa Rotore palettato di una turbina a gas per motori aeronautici e metodo per il raffreddamento di detto rotore palettato
DE102011121634B4 (de) * 2010-12-27 2019-08-14 Ansaldo Energia Ip Uk Limited Turbinenschaufel
US20120315139A1 (en) * 2011-06-10 2012-12-13 General Electric Company Cooling flow control members for turbomachine buckets and method
EP2639407A1 (de) * 2012-03-13 2013-09-18 Siemens Aktiengesellschaft Gasturbinenanordnung zur Reduzierung von Spannungen an Turbinenscheiben und zugehörige Gasturbine
US9435206B2 (en) * 2012-09-11 2016-09-06 General Electric Company Flow inducer for a gas turbine system
EP2725191B1 (de) * 2012-10-23 2016-03-16 Alstom Technology Ltd Gasturbine und Turbinenschaufel für solch eine Gasturbine
US8926283B2 (en) * 2012-11-29 2015-01-06 Siemens Aktiengesellschaft Turbine blade angel wing with pumping features
US20160090841A1 (en) * 2014-09-29 2016-03-31 United Technologies Corporation Gas turbine engine blade slot heat shield
US10094228B2 (en) 2015-05-01 2018-10-09 General Electric Company Turbine dovetail slot heat shield
WO2017005781A1 (en) * 2015-07-06 2017-01-12 Siemens Aktiengesellschaft Turbine stator vane and/or turbine rotor vane with a cooling flow adjustment feature and corresponding method of adapting a vane
DE102015111746A1 (de) * 2015-07-20 2017-01-26 Rolls-Royce Deutschland Ltd & Co Kg Gekühltes Turbinenlaufrad, insbesondere für ein Flugtriebwerk
GB201516657D0 (en) 2015-09-21 2015-11-04 Rolls Royce Plc Seal-plate anti-rotation in a stage of a gas turbine engine
US20170234447A1 (en) * 2016-02-12 2017-08-17 United Technologies Corporation Methods and systems for modulating airflow
KR102025147B1 (ko) * 2017-10-13 2019-09-27 두산중공업 주식회사 버킷의 쓰로틀 플레이트 결합구조와 이를 포함하는 회전체 및 가스터빈
DE102019206432A1 (de) * 2019-05-06 2020-11-12 MTU Aero Engines AG Turbomaschinenschaufel
KR102284507B1 (ko) * 2020-02-25 2021-08-02 두산중공업 주식회사 로터 및 이를 포함하는 터보머신
US11560844B2 (en) * 2021-02-18 2023-01-24 Pratt & Whitney Canada Corp. Inertial particle separator for a turbine section of a gas turbine engine
US12018590B1 (en) * 2023-04-04 2024-06-25 Ge Infrastructure Technology Llc Method for turbine blade and assembly with dovetail arrangement for enlarged rotor groove
US12110809B1 (en) 2023-04-04 2024-10-08 Ge Infrastructure Technology Llc Turbine blade and assembly with dovetail arrangement for enlarged rotor groove

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1605282A (en) * 1973-10-27 1987-12-23 Rolls Royce 1971 Ltd Bladed rotor for gas turbine engine
GB1561229A (en) * 1977-02-18 1980-02-13 Rolls Royce Gas turbine engine cooling system
US4348157A (en) * 1978-10-26 1982-09-07 Rolls-Royce Limited Air cooled turbine for a gas turbine engine
US4626169A (en) * 1983-12-13 1986-12-02 United Technologies Corporation Seal means for a blade attachment slot of a rotor assembly
US4820123A (en) * 1988-04-25 1989-04-11 United Technologies Corporation Dirt removal means for air cooled blades
DE3835932A1 (de) * 1988-10-21 1990-04-26 Mtu Muenchen Gmbh Vorrichtung zur kuehlluftzufuehrung fuer gasturbinen-rotorschaufeln
US5403156A (en) * 1993-10-26 1995-04-04 United Technologies Corporation Integral meter plate for turbine blade and method
US6059529A (en) * 1998-03-16 2000-05-09 Siemens Westinghouse Power Corporation Turbine blade assembly with cooling air handling device

Also Published As

Publication number Publication date
FR2823794B1 (fr) 2003-07-11
JP4112986B2 (ja) 2008-07-02
DE60205977T2 (de) 2006-07-06
US20040115054A1 (en) 2004-06-17
RU2325537C2 (ru) 2008-05-27
WO2002086291A1 (fr) 2002-10-31
EP1251243A1 (de) 2002-10-23
US6981845B2 (en) 2006-01-03
EP1251243B8 (de) 2005-11-02
JP2004522049A (ja) 2004-07-22
DE60205977D1 (de) 2005-10-13
UA73655C2 (uk) 2005-08-15
FR2823794A1 (fr) 2002-10-25
ES2244738T3 (es) 2005-12-16
RU2003133669A (ru) 2005-04-20
CA2444862A1 (fr) 2002-10-31
CA2444862C (fr) 2009-11-24

Similar Documents

Publication Publication Date Title
EP1251243B1 (de) Turbinenschaufel mit Kühlluftleiteinrichtung
EP2406463B1 (de) Turbinenschaufel mit entstaubungsloch am schaufelfuss
EP3134620B1 (de) Turbinenschaufel einer turbomaschine mit einem kühlkreislauf mit verbesserter homogenität
CA2635636C (fr) Dispositif de refroidissement des alveoles d'un disque de rotor de turbomachine
EP1726783B1 (de) Hohle Laufschaufel für die Turbine eines Gasturbinentriebwerks, mit einem Hohlraum
EP0062558B1 (de) Stufe eines Turbostrahltriebwerks mit Luftkühlvorrichtung der Turbinenrotorscheibe
CA2550442C (fr) Circuits de refroidissement pour aube mobile de turbomachine
CA2569566C (fr) Circuit de refroidissement central pour aube mobile de turbomachine
EP3680451B1 (de) Rotor, mit einem solchen rotor ausgerüstete turbine und turbinentriebwerk, das mit einer solchen turbine ausgestattet ist
FR2858352A1 (fr) Circuit de refroidissement pour aube de turbine
FR2864990A1 (fr) Perfectionnements apportes aux fentes d'evacuation de l'air de refroidissement d'aubes de turbine haute-pression
CA2806031A1 (fr) Etancheite inter-aubes pour une roue de turbine ou de compresseur de turbomachine
FR2890103A1 (fr) Deflecteur d'air pour circuit de refroidissement pour aube de turbine a gaz
CA2456705C (fr) Plate-forme annulaire de distributeur d'une turbine basse-pression de turbomachine
CA2418241A1 (fr) Aube mobile de turbine haute pression munie d'un bord de fuite au comportement thermique ameliore
EP2839165B1 (de) Kraftfahrzeuggebläse mit reduzierter achsengrösse
FR2960603A1 (fr) Diffuseur radial de turbomachine
FR3009039A1 (fr) Moyeu de carter intermediaire pour turboreacteur d'aeronef comprenant des deflecteurs de guidage d'air
EP3942158A1 (de) Mit optimiertem kühlkreislauf ausgestattete turbinentriebwerksschaufel
FR3028494A1 (fr) Pale de turbomachine, comprenant des pontets s'etendant depuis la paroi d'intrados jusqu'a la paroi d'extrados
FR2927674A1 (fr) Aube de soufflante avec aspiration en pied et soufflage au bord de fuite
FR2927673A1 (fr) Aube de soufflante avec aspiration en pied et soufflage en tete
FR3066530A1 (fr) Aube pour turbine de turbomachine comprenant une configuration optimisee de cavites internes de circulation d'air de refroidissement

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

17P Request for examination filed

Effective date: 20020422

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE TR

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

AKX Designation fees paid

Designated state(s): DE ES FR GB IT SE

17Q First examination report despatched

Effective date: 20040715

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE ES FR GB IT SE

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: SNECMA

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20050907

REF Corresponds to:

Ref document number: 60205977

Country of ref document: DE

Date of ref document: 20051013

Kind code of ref document: P

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2244738

Country of ref document: ES

Kind code of ref document: T3

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20060608

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: ES

Payment date: 20120410

Year of fee payment: 11

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20140613

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20130418

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 14

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 15

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 20170324

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20170322

Year of fee payment: 16

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170717

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 17

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180418

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180417

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20210323

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20210324

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20210323

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R071

Ref document number: 60205977

Country of ref document: DE

REG Reference to a national code

Ref country code: GB

Ref legal event code: PE20

Expiry date: 20220416

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION

Effective date: 20220416