EP1251243A1 - Turbinenschaufel mit Kühlluftleiteinrichtung - Google Patents

Turbinenschaufel mit Kühlluftleiteinrichtung Download PDF

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Publication number
EP1251243A1
EP1251243A1 EP02290964A EP02290964A EP1251243A1 EP 1251243 A1 EP1251243 A1 EP 1251243A1 EP 02290964 A EP02290964 A EP 02290964A EP 02290964 A EP02290964 A EP 02290964A EP 1251243 A1 EP1251243 A1 EP 1251243A1
Authority
EP
European Patent Office
Prior art keywords
blade
air
deflector
turbine
cell
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.)
Granted
Application number
EP02290964A
Other languages
English (en)
French (fr)
Other versions
EP1251243B8 (de
EP1251243B1 (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

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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
    • 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 blade being attached to a disc of the turbine and being cooled by a circulation internal air.
  • An axial turbine stage is composed a grid of fixed vanes called distributor and a grid of movable blades called a wheel. It exists monobloc wheels where blades and disc form a unique piece. There are also impellers reported where blades and disc are assembled mechanically, usually by fir tree feet.
  • Figure 1A is a partial view of a blade 1 mounted on a disc 2, the view being represented in a plane perpendicular to the axis of the turbine. It shows more precisely the foot 3 of dawn 1 in position in a cell 4 of the disc 2. The foot is shown in section along the axis of a channel 5 bringing air cooling from the bottom of cell 4 to the internal cooling circuit and not depicted from dawn.
  • the cooling air circulates in cell 4 in a direction perpendicular to the plan of the figure.
  • the air is introduced by one end of the cell, corresponding to a face of the disc called the upstream face, and goes up in channel (or channels) 5, the other end of the socket, corresponding to the other face of the disc 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 to seal the air circuit.
  • the flange is often held on the disc by a hook system called dogs.
  • the hooks also provide another function. They give the cooling air directing towards the alveoli a speed of rotation equal to that of the turbine rotor. Looks like cooling then arrives in front of the cell in turning at the same speed as it and entering inside the socket 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 at the foot of dawn and opposite the cell, and air outlet means.
  • the foot of dawn is provided with a device for channel the dawn cooling air. This device also allows the evacuation of air from cooling after passing inside dawn. The device ensures the separation of the circuits cooling air entering and leaving dawn from dawn.
  • GB-A-1 605 282 discloses a blade for turbine, the blade having a foot allowing to bring it back in a cell of a disc of the turbine.
  • Dawn has an internal circuit of air cooling constituted by channels, comprising air intake means located on the foot of dawn and facing the cell, and means of air outlet located at the blade tip.
  • the foot of the blade is provided with a cooling tube allowing the cooling air to be brought in from the suction air manifold to the air inlets.
  • US-A-4,348,157 discloses a dawn for turbine, attached to a disc by means of a foot.
  • Dawn has an internal circuit of air-cooled including an inlet air.
  • the air inlet port is not located on the at the foot of dawn and opposite the receiving cell of this foot but in the connecting part between the foot and dawn, that is to say in the leg.
  • Passages are provided to supply cooling air up to the air intakes of the blades. These passages can include deflectors.
  • US-A-4,178,129 discloses a system cooling of turbine blades by circulation air. Each blade has a foot allowing the return to a cell of a turbine disc. The blade has an internal cooling circuit by air comprising air inlet means located on the foot of dawn. Cooling air is sent either in an air supply chamber of cooling in which the channels of cooling, either directly in the edge channel attack through a Pitot receiver.
  • the incoming cooling air is supplied by a tube-shaped device communicating with the orifices of the cooling channels.
  • the device tube-shaped can have size holes suitable for channel orifice openings practically corresponding to the width of the cell. In both cases, the formation of a whirlwind.
  • an air cooling tube is provided adapted to the width of the cell. So we cannot avoid the formation of a vortex.
  • Figure 1B illustrates the phenomenon causing a loss of effectiveness of the blade cooling.
  • This figure is a view of the underside of foot 3 and bearing the reference 6 in Figure 1A.
  • Channel (or channels) 5 has not been pictured.
  • the flange pressed against the upstream face of the disc is shown under the reference 7.
  • Under the reference 8 has been shown a sealing flange of the alveolus, downstream side of the disc.
  • the present invention overcomes this problem whenever it arises in a turbine.
  • a turbine blade the dawn presenting a foot allowing to bring it back in a cavity of a turbine disc, the dawn having an internal air cooling circuit comprising air inlet means located on a facing the foot of the dawn and facing said cell, and air outlet means, characterized in that said face of the foot of dawn is equipped with a deflector comprising at least one fin allowing channel the cooling air circulating in the bottom of the cell to regulate the air flow towards the air intake means.
  • the deflector can be an integral part from dawn.
  • the deflector can be an added element at the foot of dawn and provided with means of access to air intake means.
  • the means of access can include at least one calibrated hole.
  • the fin can be straight or tilted by relation to the general axis of dawn.
  • the deflector includes at least one fin allowing to channel the cooling air entering the socket and at least one fin allowing channel exhaust air to the center of the cell.
  • Figure 2A is a view of a blade 11 according to the invention and mounted on a disc 12, the view being represented in a plane perpendicular to the axis of the turbine as in FIG. 1A.
  • Foot 13 of the blade 11 is in position in a cell 14 of the disc 12.
  • the foot is shown in section along the axis of a channel 15 bringing the cooling air from the bottom of cell 14 to the cooling circuit internal and not shown from dawn.
  • the circulation of the air in the socket is made as described previously for Figure 1A.
  • the blade of Figure 2A is equipped with a deflector 20 secured to the underside 16 of the dawn foot.
  • the deflector 20 has fins to channel the cooling air circulating in the bottom of the cell 14.
  • FIG. 2A shows that the deflector has a hole 18 in correspondence with channel 15 and serving as means access to the cooling air channel. This hole can be a calibrated hole whose realization is easy to be obtained on a part such as a deflector reported.
  • FIG 2B corresponding to Figure 1B for the prior art, shows by arrows from which way is channeled the cooling air at the bottom of the socket, 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 for aligning the holes 21.
  • the fins are arranged so as to form a baffle species.
  • the deflector shown has four holes for the passage of air from cooling.
  • the deflector can be an insert by welding or soldering on the blade root. Alternatively, the deflector can be an integral part of the dawn.
  • Figure 3 is a perspective view of the deflector 20 mentioned previously. This figure allows to better see the fins 22 and 23 as well as the holes 21.
  • Figure 4 is a partial sectional view a turbine equipped with a blade according to the invention.
  • the Figure 4 shows a blade 11 equipped with a deflector 20 and mounted in a cell 14 of the disk 12. This figure also shows the flange 17 plated against the upstream face of the disc 12 and the flange 18 obturation of the alveolus.
  • the cooling air is taken in chamber background and accelerated through a series injectors such as injector 31. This air passes then through holes, such as hole 32, drilled on the flange 17 and goes up towards the bottoms of the alveoli as indicated by arrows on the Figure 4.
  • holes such as hole 32, drilled on the flange 17 and goes up towards the bottoms of the alveoli as indicated by arrows on the Figure 4.
  • the hooks or dogs that the invention allows remove In dashed lines, the hooks or dogs that the invention allows remove.
  • Figures 5 and 6 show, in position on the underside of a blade root, others forms of deflectors usable by the present invention.
  • the deflector 40 comprises two fins 41 and 42 present over the entire length of the deflector. Holes 43 for access to the canals of blades are also shown.
  • the deflector 50 comprises a first series of fins 51 and 53, located in a side of the deflector, and a second series of fins 52 and 54, located on the other side of the deflector.
  • the fins are arranged to form baffles. of the 55 access holes to the blade channels are also represented.
  • the deflector may also include one or more several fins of curved shape and allowing a cooling air guidance along a path more scalable.
  • Figures 7 to 10 give, by way of examples, other forms of deflectors that can be used by the present invention. All of these views are cross-sectional representations made according to a cooling air passage hole.
  • the deflector 60 of FIG. 7 is in rail shape. It has fins 61 and 62 arranged at right angles to the bearing face 63 of the deflector on the blade root.
  • the fins 61 and 62 can run the entire length of the deflector or be interrupted to form baffles.
  • the deflector 70 has fins 71 and 72 which are flared relative to the bearing face 73 of the deflector on the blade root.
  • Deflector 80 has fins 81 and 82 which extend closer to the bearing face 83 of the deflector on the blade root.
  • the deflector 90 includes four parallel fins 91, 92, 93 and 94 arranged at right angles to the bearing face 95 of the deflector on the blade root.
  • the invention provides a gain of static pressure in the center of the cell which fills in approximately 75% of the existing pressure drop without the arrangement made. This improvement in cooling air supply to the blade reduces the average dawn temperature according to the operating conditions and to increase consequently its lifespan.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
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 true EP1251243A1 (de) 2002-10-23
EP1251243B1 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)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005012695A1 (en) * 2003-07-28 2005-02-10 Pratt & Whitney Canada Corp. Gas turbine blade inlet cooling flow deflector
FR2858829A1 (fr) * 2003-08-12 2005-02-18 Snecma Moteurs Aube refroidie de moteur a turbine a gaz
EP1574670A3 (de) * 2004-03-13 2009-02-25 Rolls-Royce Plc Aufbauanordnung für Turbinenschaufeln
EP2436879A3 (de) * 2010-10-04 2014-01-08 Rolls-Royce plc Turbinenscheiben-Kühlanordnung
EP1987903B1 (de) 2007-04-30 2015-11-11 United Technologies Corporation Verfahren zum Herstellen einer Schaufelskomponente
EP3093433A1 (de) * 2015-05-01 2016-11-16 General Electric Company Turbinenschwalbenschwanznuthitzeschild

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GB0227745D0 (en) * 2002-11-28 2003-01-08 Rolls Royce Plc Blade cooling
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
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
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
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

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US4178129A (en) * 1977-02-18 1979-12-11 Rolls-Royce Limited 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
GB1605282A (en) * 1973-10-27 1987-12-23 Rolls Royce 1971 Ltd Bladed rotor for gas turbine engine
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
WO1999047792A1 (en) * 1998-03-16 1999-09-23 Siemens Westinghouse Power Corporation Turbine blade assembly with cooling air handling device

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Patent Citations (7)

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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
US4178129A (en) * 1977-02-18 1979-12-11 Rolls-Royce Limited 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
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
WO1999047792A1 (en) * 1998-03-16 1999-09-23 Siemens Westinghouse Power Corporation Turbine blade assembly with cooling air handling device

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005012695A1 (en) * 2003-07-28 2005-02-10 Pratt & Whitney Canada Corp. Gas turbine blade inlet cooling flow deflector
US6974306B2 (en) 2003-07-28 2005-12-13 Pratt & Whitney Canada Corp. Blade inlet cooling flow deflector apparatus and method
FR2858829A1 (fr) * 2003-08-12 2005-02-18 Snecma Moteurs Aube refroidie de moteur a turbine a gaz
EP1508670A2 (de) * 2003-08-12 2005-02-23 Snecma Moteurs Gekühlte Schaufel einer Gasturbine
EP1508670A3 (de) * 2003-08-12 2005-03-09 Snecma Moteurs Gekühlte Schaufel einer Gasturbine
US7204675B2 (en) 2003-08-12 2007-04-17 Snecma Moteurs Cooled gas turbine engine vane
EP1574670A3 (de) * 2004-03-13 2009-02-25 Rolls-Royce Plc Aufbauanordnung für Turbinenschaufeln
EP1987903B1 (de) 2007-04-30 2015-11-11 United Technologies Corporation Verfahren zum Herstellen einer Schaufelskomponente
EP1987903B2 (de) † 2007-04-30 2022-07-27 Raytheon Technologies Corporation Schichtstrukturen mit integrierten Lötmaterialien
EP2436879A3 (de) * 2010-10-04 2014-01-08 Rolls-Royce plc Turbinenscheiben-Kühlanordnung
US8807942B2 (en) 2010-10-04 2014-08-19 Rolls-Royce Plc Turbine disc cooling arrangement
EP3093433A1 (de) * 2015-05-01 2016-11-16 General Electric Company Turbinenschwalbenschwanznuthitzeschild
CN106224011A (zh) * 2015-05-01 2016-12-14 通用电气公司 涡轮燕尾槽隔热罩
US10094228B2 (en) 2015-05-01 2018-10-09 General Electric Company Turbine dovetail slot heat shield
CN106224011B (zh) * 2015-05-01 2019-02-19 通用电气公司 涡轮燕尾槽隔热罩

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
US6981845B2 (en) 2006-01-03
EP1251243B8 (de) 2005-11-02
EP1251243B1 (de) 2005-09-07
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

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