EP1709298B1 - Aube refroidie pour une turbine a gaz - Google Patents

Aube refroidie pour une turbine a gaz Download PDF

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Publication number
EP1709298B1
EP1709298B1 EP05701516.6A EP05701516A EP1709298B1 EP 1709298 B1 EP1709298 B1 EP 1709298B1 EP 05701516 A EP05701516 A EP 05701516A EP 1709298 B1 EP1709298 B1 EP 1709298B1
Authority
EP
European Patent Office
Prior art keywords
blade
cooling
cooling duct
inlet
cooling medium
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.)
Not-in-force
Application number
EP05701516.6A
Other languages
German (de)
English (en)
Other versions
EP1709298A1 (fr
Inventor
Shailendra Naik
Sacha Parneix
Ulrich Rathmann
Helene Saxer-Felici
Stefan Schlechtriem
Beat Von Arx
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1709298A1 publication Critical patent/EP1709298A1/fr
Application granted granted Critical
Publication of EP1709298B1 publication Critical patent/EP1709298B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • 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
    • 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
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
    • 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
    • F05D2260/221—Improvement of heat transfer

Definitions

  • the present invention relates to the field of gas turbine technology. It relates to a cooled blade for a gas turbine according to the preamble of claim 1.
  • Such a blade is for example from the document US-A-4,278,400 known.
  • Fig. 1 is a basic configuration of a shovel with shroud shown.
  • the blade 10 comprises an airfoil 11 that merges downwards over a blade shank 25 into a blade root 12. At the upper end, that is, at the blade tip or blade tip, the blade 11 goes into a shroud portion 21, which forms a closed, annular shroud together with the shroud portions of the other blades at a complete blade ring.
  • the airfoil has a span that extends from the blade shank to the blade tip. If the blade is installed in a turbine, the span of the blade is oriented in the radial direction of the turbine cross-section, which is why the direction of the span is hereinafter also referred to as the radial direction.
  • the Blade sheet 11 has a front edge 19, which is flowed by the hot gas, and a trailing edge 20.
  • a plurality of radial cooling channels 13, 14 and 15 are arranged, which are connected to each other by flow deflection 17, 18 with each other and a Serpentine with several Windings form (see the flow arrows in the cooling channels 13, 14,15 of Fig. 1 ).
  • the cooling medium Due to the one-time passage of the cooling medium through the serpentine-like successive cooling channels 13, 14, 15, the cooling medium flows through the cooling channels with increasing temperature and reaches the highest temperature in the last cooling channel 15 of the trailing edge 20.
  • the trailing edge 20 of the blade 10 can therefore be excessively high under certain operating conditions Temperatures of the cooling medium and the blade material or metal reach. The resulting mismatch of metal temperature over the axial length of the blade can lead to high temperature creep and consequently deformation of the trailing edge 20.
  • a shovel with shroud as in Fig. 1 is shown, there is a tilting of the shroud segments 21 in the axial, radial and circumferential direction as a secondary effect of the trailing edge deformation.
  • the tilting of the shroud segments 21 may cause the gaps between individual shroud segments to open and allow the entry of high temperature hot gas into the shroud cavity.
  • the temperatures of the shroud metal can increase significantly and quickly induce creep of the shroud and eventually lead to high temperature failure of the shroud.
  • an additional flow of cooling medium is diverted directly from the main cooling inlet and via a between the Main cooling inlet and the second deflection region extending opening, in an exemplary embodiment, a bore or an opening made during casting, is fed to the running along the trailing edge of the cooling channel. Since the flow of the cooling medium is diverted through the bypass bore from the main cooling flow and later added again, the cooling medium flow remains unchanged overall.
  • An advantageous embodiment of the invention is characterized in that the bore is formed and arranged so that the flowing through the bore cooling medium flows through the second deflection directly into the second cooling channel. This results in a particularly efficient temperature reduction by the bypass flow in the cooling channel of the trailing edge.
  • a preferred embodiment of a cooled gas turbine blade with multiple feed of the cooling medium according to the invention is in the Fig. 1 and 2 played.
  • the main flow of the cooling medium occurs in the region of the blade shank 25 through a main cooling inlet 16 from below into the cooling channel 13 and passes partially through openings in the shroud section 21 (bores 27, Fig. 3 to 6 ) and partially along the trailing edge 20 again (see the in Fig. 1 Plotted arrows on the shroud portion 21 and at the trailing edge 20).
  • a portion of the cooling medium flowing into the main cooling inlet 16 is branched off through a bore 23 and fed via the second deflection region 18 to the cooling channel 15 at the trailing edge.
  • the bore 23 is preferably formed and arranged (i.e., obliquely upwardly in the present case) in such a way that the cooling medium flow flowing through it is directed directly into the cooling channel 15 without detours.
  • the purpose of the bypass bore 23 is to introduce cooler cooling medium directly into the trailing edge region of the blade 10.
  • the shroud portion 21 of the blade 10 further holes 27, 28, 29 are provided ( Fig. 3 to 6 ).
  • the cooling medium exiting through the bores 27, 28, 29 serves to actively cool the shroud section 21.
  • the cooling bores 27, 28, 29 in the shroud section 21 preferably have an inner diameter in the range between 0.6 mm and 4 mm. All three holes 27,28, 29 are positioned and dimensioned on the shroud portion 21, that an uneven Beam penetration takes place in the main flow of the shroud cavity.

Landscapes

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

Claims (7)

  1. Aube refroidie (10) pour une turbine à gaz, aube (10) qui présente une pale (11) avec un bord d'attaque (19) et un bord de fuite (20), qui s'étend avec une envergure de pale depuis un pied d'aube (12) avec un corps d'aube (25) jusqu'à une pointe d'aube, et dans laquelle une multiplicité de canaux de refroidissement sont disposés à l'intérieur de la pale (11), qui sont connectés en série au point de vue de l'écoulement et qui s'étendent le long de l'envergure de pale depuis le corps d'aube jusqu'à la pointe d'aube, parmi lesquels un premier canal de refroidissement (13) est disposé le long du bord d'attaque (19) et un deuxième canal de refroidissement (15) est disposé le long du bord de fuite (20), lesdits premier et deuxième canaux de refroidissement étant conçus et disposés en vue de l'écoulement d'un courant principal d'un fluide de refroidissement dans la direction de l'envergure de la pale vers la pointe d'aube, dans laquelle l'entrée du premier canal de refroidissement (13) est en communication avec une entrée de refroidissement principale (16) et la sortie du premier canal de refroidissement (13) est en communication fluidique avec l'entrée du deuxième canal de refroidissement (15) via une première région de déviation (17), au moins un troisième canal de refroidissement disposé entre le premier et le deuxième canaux de refroidissement (13, 15), et une deuxième région de déviation (18), qui est disposée entre le troisième canal de refroidissement et le deuxième canal de refroidissement, et dans laquelle il est prévu des premiers moyens (23), par lesquels un courant additionnel du fluide de refroidissement est ajouté au courant principal du fluide de refroidissement chauffé circulant d'un troisième canal de refroidissement (14) au deuxième canal de refroidissement (15), caractérisée en ce que les premiers moyens comprennent une ouverture (23) allant de l'entrée de refroidissement principale (16) à la deuxième région de déviation (18).
  2. Aube selon la revendication 1, caractérisée en ce que l'ouverture (23) est configurée et disposée de telle manière que le fluide de refroidissement circulant à travers l'ouverture (23) pénètre directement dans le deuxième canal de refroidissement (15) par la deuxième région de déviation (18).
  3. Aube selon une des revendications 1 ou 2, caractérisée en ce que l'ouverture est un perçage.
  4. Aube selon l'une quelconque des revendications précédentes, caractérisée en ce qu'il est prévu des ouvertures de sortie (27, ..., 29), qui sont disposées entre l'entrée de refroidissement principale (16) et la deuxième région de déviation (18), et par lesquelles un courant partiel du courant principal du fluide de refroidissement sort.
  5. Aube selon la revendication 4, caractérisée en ce que l'aube (10) présente une partie de bande de recouvrement (21) à son extrémité supérieure et en ce que les ouvertures de sortie additionnelles comprennent des perçages (27, ..., 29) disposés dans la partie de bande de recouvrement (21).
  6. Aube selon la revendication 5, caractérisée en ce qu'il est prévu dans la partie de bande de recouvrement au moins trois perçages (27, ..., 29), qui présentent un diamètre intérieur compris dans la plage de 0,6 mm à 4 mm.
  7. Aube selon l'une quelconque des revendications précédentes, qui présente exactement un troisième canal de refroidissement.
EP05701516.6A 2004-01-16 2005-01-14 Aube refroidie pour une turbine a gaz Not-in-force EP1709298B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004002327A DE102004002327A1 (de) 2004-01-16 2004-01-16 Gekühlte Schaufel für eine Gasturbine
PCT/EP2005/050137 WO2005068783A1 (fr) 2004-01-16 2005-01-14 Aube refroidie pour une turbine a gaz

Publications (2)

Publication Number Publication Date
EP1709298A1 EP1709298A1 (fr) 2006-10-11
EP1709298B1 true EP1709298B1 (fr) 2015-11-11

Family

ID=34716622

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05701516.6A Not-in-force EP1709298B1 (fr) 2004-01-16 2005-01-14 Aube refroidie pour une turbine a gaz

Country Status (6)

Country Link
US (1) US7520724B2 (fr)
EP (1) EP1709298B1 (fr)
CN (1) CN100408812C (fr)
DE (1) DE102004002327A1 (fr)
TW (1) TWI356870B (fr)
WO (1) WO2005068783A1 (fr)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2898384B1 (fr) * 2006-03-08 2011-09-16 Snecma Aube mobile de turbomachine a cavite commune d'alimentation en air de refroidissement
US7731483B2 (en) * 2007-08-01 2010-06-08 General Electric Company Airfoil shape for a turbine bucket and turbine incorporating same
US7988420B2 (en) * 2007-08-02 2011-08-02 General Electric Company Airfoil shape for a turbine bucket and turbine incorporating same
ES2398303T3 (es) 2008-10-27 2013-03-15 Alstom Technology Ltd Álabe refrigerado para una turbina de gas y turbina de gas que comprende un tal álabe
EP2230383A1 (fr) 2009-03-18 2010-09-22 Alstom Technology Ltd Aube de turbine avec refroidissement de l'extrémité
WO2013167513A1 (fr) 2012-05-07 2013-11-14 Alstom Technology Ltd Procédé de fabrication d'éléments en superalliages monocristallins (sx) ou solidifiés de manière directionnelle (ds)
US10145269B2 (en) 2015-03-04 2018-12-04 General Electric Company System and method for cooling discharge flow
GB201506728D0 (en) * 2015-04-21 2015-06-03 Rolls Royce Plc Thermal shielding in a gas turbine
GB201512810D0 (en) 2015-07-21 2015-09-02 Rolls Royce Plc Thermal shielding in a gas turbine
JP5905631B1 (ja) * 2015-09-15 2016-04-20 三菱日立パワーシステムズ株式会社 動翼、これを備えているガスタービン、及び動翼の製造方法
US10683763B2 (en) * 2016-10-04 2020-06-16 Honeywell International Inc. Turbine blade with integral flow meter
US10378363B2 (en) 2017-04-10 2019-08-13 United Technologies Corporation Resupply hole of cooling air into gas turbine blade serpentine passage
US10961854B2 (en) * 2018-09-12 2021-03-30 Raytheon Technologies Corporation Dirt funnel squealer purges
US11021961B2 (en) 2018-12-05 2021-06-01 General Electric Company Rotor assembly thermal attenuation structure and system
US11118462B2 (en) * 2019-01-24 2021-09-14 Pratt & Whitney Canada Corp. Blade tip pocket rib
US11371359B2 (en) 2020-11-26 2022-06-28 Pratt & Whitney Canada Corp. Turbine blade for a gas turbine engine

Family Cites Families (11)

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Publication number Priority date Publication date Assignee Title
US4278400A (en) * 1978-09-05 1981-07-14 United Technologies Corporation Coolable rotor blade
FR2468727A1 (fr) * 1979-10-26 1981-05-08 Snecma Perfectionnement aux aubes de turbine refroidies
US4775296A (en) * 1981-12-28 1988-10-04 United Technologies Corporation Coolable airfoil for a rotary machine
US4474532A (en) * 1981-12-28 1984-10-02 United Technologies Corporation Coolable airfoil for a rotary machine
EP0340149B1 (fr) * 1988-04-25 1993-05-19 United Technologies Corporation Moyens de dépoussiérage pour une aube refroidie par de l'air
WO1995014848A1 (fr) * 1993-11-24 1995-06-01 United Technologies Corporation Profil de turbine a refroidissement ameliore
US5915923A (en) * 1997-05-22 1999-06-29 Mitsubishi Heavy Industries, Ltd. Gas turbine moving blade
JPH11241602A (ja) * 1998-02-26 1999-09-07 Toshiba Corp ガスタービン翼
US6832889B1 (en) * 2003-07-09 2004-12-21 General Electric Company Integrated bridge turbine blade
US6966756B2 (en) * 2004-01-09 2005-11-22 General Electric Company Turbine bucket cooling passages and internal core for producing the passages
US7137780B2 (en) * 2004-06-17 2006-11-21 Siemens Power Generation, Inc. Internal cooling system for a turbine blade

Also Published As

Publication number Publication date
EP1709298A1 (fr) 2006-10-11
US20060292006A1 (en) 2006-12-28
TW200532096A (en) 2005-10-01
WO2005068783A1 (fr) 2005-07-28
DE102004002327A1 (de) 2005-08-04
US7520724B2 (en) 2009-04-21
CN1910343A (zh) 2007-02-07
TWI356870B (en) 2012-01-21
CN100408812C (zh) 2008-08-06

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