EP1207268B1 - Aube de turbine à gaz et procédé de fabrication d'une aube de turbine à gaz - Google Patents

Aube de turbine à gaz et procédé de fabrication d'une aube de turbine à gaz Download PDF

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Publication number
EP1207268B1
EP1207268B1 EP00125031A EP00125031A EP1207268B1 EP 1207268 B1 EP1207268 B1 EP 1207268B1 EP 00125031 A EP00125031 A EP 00125031A EP 00125031 A EP00125031 A EP 00125031A EP 1207268 B1 EP1207268 B1 EP 1207268B1
Authority
EP
European Patent Office
Prior art keywords
platform
gas turbine
slot
turbine blade
edge
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
EP00125031A
Other languages
German (de)
English (en)
Other versions
EP1207268A1 (fr
Inventor
Peter Tiemann
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 EP00125031A priority Critical patent/EP1207268B1/fr
Priority to DE50009497T priority patent/DE50009497D1/de
Priority to CA002361978A priority patent/CA2361978A1/fr
Priority to JP2001350479A priority patent/JP4040864B2/ja
Priority to US10/004,478 priority patent/US6719529B2/en
Publication of EP1207268A1 publication Critical patent/EP1207268A1/fr
Application granted granted Critical
Publication of EP1207268B1 publication Critical patent/EP1207268B1/fr
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
    • F01D5/186—Film 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
    • F01D5/12—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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the invention relates to a gas turbine blade with a Platform and a profile adjacent to the platform.
  • the invention also relates to a process for the preparation a gas turbine blade.
  • a gas turbine blade discloses DE 26 28 807 A or US-A-6 082 961.
  • a such gas turbine blade is exposed to extremely high temperatures and therefore has to be cooled.
  • the gas turbine blade has a platform that is the boundary of a flow channel serves, in which the gas turbine bucket installed is.
  • the platform is followed by a profile that fits into the Flow channel protrudes and flows around the hot gas.
  • the Platform is exposed to the hot gas.
  • the platform will cooled by an impingement cooling system, one at the bottom the platform arranged impingement cooling plate comprises, from which about impact cooling holes cooling air on the bottom the platform is flowing. About Filmkühlbohritch occurs then this cooling air at the top of the platform and forms there a cooling film.
  • the object of the invention is the specification of a gas turbine blade, the platform withstands very high temperatures, at a comparatively low cooling air requirement.
  • Another object of the invention is the specification of a method for producing such a gas turbine blade.
  • a gas turbine blade Task solved by specifying a gas turbine blade with a platform and a platform on top the platform subsequent profile, the platform a leading edge and a trailing edge for a gas turbine blade having flowing hot gas and wherein the Platform one extending parallel to the leading edge Slot, open into the channels, through the Platform through to one of the platform top opposite Lead platform base.
  • the platform is particularly special at its leading edge exposed to high temperatures.
  • the leading edge is the the edge of the platform facing the incoming hot gas.
  • This area of the platform is difficult to cool, because the preceding profile and a thickened, as rounded Transition area between profile and platform one yield difficult to cool geometry. It is with the invention now possible in a simple manufacturing technology, to efficiently cool the platform inflow edge. This happens in that cooling air from the platform underside through the Channels are routed into the slot where they are in the platform Entry edge area efficiently cools.
  • the between the Slot and the leading edge formed wall is preferably 1-3 mm thick Due to this comparatively thin design results in good cooling, without a negative Influencing load-bearing areas.
  • the slot is in a direction from the platform underside so inclined to the platform top to the profile, that a cooling fluid emerging from the slot is a Film cooling of the platform top effects.
  • the slot is so over its height in one direction from the leading edge tilted to the trailing edge.
  • the inclination is dimensioned that exiting under normal operating conditions Cooling fluid, in particular cooling air, forming a film on the Along the top of the platform and thus film cooling causes. After cooling the leading edge of the platform by the cooling fluid, this thus also serves subsequently a movie cooling the deck top.
  • the channels are directed so that they in the Open slot in one direction to the leading edge.
  • the gas turbine blade is a blade executed.
  • the slot is eroded into the platform.
  • the channels are in the platform by means of Laser drilling introduced.
  • Preferred dimensions is on the the leading edge adjacent wall of the slot in front of the Completing the laser drilling a light-scattering protection applied so that this wall of the slot is not through the Laser radiation is damaged.
  • this light-scattering protection a teflon strip.
  • Material-saving and efficient production of the channels Laser drilling initially involves the risk of being pierced the channels ultimately adjacent to the leading edge Wall of the slot through at the end of the manufacturing process from the channels emerging laser radiation is damaged. This is prevented by the light-scattering protection, wherein In particular, the application of the Teflon strip a simple and fast method represents.
  • FIG. 1 shows a gas turbine blade 1, which serves as a moving blade is trained.
  • a platform 3 is included Profile 5 on.
  • the platform 3 has a platform top side 7 on which surrounds the profile 5.
  • Opposite the platform top 7 is a platform base 8.
  • the platform 3 has a leading edge 9 and a trailing edge 11.
  • At the platform underside 8 is closed by a blade root 13 on, with the gas turbine blade 1 with a not closer illustrated rotor of a gas turbine is used.
  • the gas turbine blade 1 When using the gas turbine blade 1 flows around a hot gas 23, the gas turbine blade 1, whereby, among other things, the Platform 3 and there especially the leading edge 9 thermally is heavily loaded.
  • a particularly effective cooling of the leading edge 9 results from the leadership of one Cooling fluid 25, in particular cooling air, from an area below the platform 3 through the channels 17 and into the Slot 15 into it. Due to the orientation of the channels 17, of which also provided more than the two channels 17 shown can be, the cooling fluid 25 is perpendicular to the wall 21st the slot 15 and thus cools this wall 21 and thus the leading edge 9 efficiently with a baffle cooling. After a flow calming in the slot 15 then enters the Cooling fluid 25 by the inclination of the slot 15 so from the Slot 15 off, making it a cooling film over the Platform top 7 flows out.
  • FIG. 2 A method of making such a gas turbine blade 1 is shown in more detail in Figure 2, which in a Longitudinal section shows the leading edge region of the platform 3.
  • the formed between the slot 15 and the leading edge 9 Wall 21 has a maximum thickness D of 1 - 3 mm.
  • the im Slot 15 lying surface 31 of the wall 21 is provided with a Teflon strip 33 provided a light-scattering protection represents.
  • This light-scattering protection 33 serves for protection in front of a laser radiation 37 from a laser 35, with which the Holes 17 are made by laser drilling. At the Passage of the laser radiation 37 through the finished drilled Channel 17, the wall 21 is not damaged because of the teflon strip 33 this radiation 37 scatters.
  • the opening of the Slot 15 in the direction of the profile 5 with a slope 41 bevelled.

Landscapes

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

Claims (9)

  1. Aube (1) de turbine à gaz comprenant une plateforme (3) et un profilé (5) se raccordant à la face (7) supérieure de la plateforme (3), la plateforme (3) ayant un bord (9) d'attaque et un bord (11) de fuite pour un gaz (23) chaud contournant l'aube (1) de turbine à gaz, caractérisé en ce que la plateforme (3) a une fente (15) qui s'étend parallèlement au bord (9) d'attaque et dans laquelle débouchent des canaux (17) qui mènent à travers la plateforme (3) à une face (8) inférieure de la plateforme opposée à la face (7) supérieure de la plateforme.
  2. Aube (1) de turbine à gaz suivant la revendication 1, dans laquelle il est formé entre la fente (15) et le bord (9) d'attaque une paroi d'une épaisseur de 0,53 mm.
  3. Aube (1) de turbine à gaz suivant la revendication 1, dans laquelle la fente (15) est inclinée vers le profilé (5) dans une direction allant de la face (8) inférieure de la plateforme à la face (7) supérieure de la plateforme de façon à ce qu'un fluide (25) de refroidissement sortant de la fente (15) provoque un refroidissement pelliculaire de la face (7) supérieure de la plateforme.
  4. Aube (1) de turbine à gaz suivant la revendication 1, dans laquelle les canaux (17) débouchent dans la fente (15) dans une direction allant vers le bord (9) d'entrée.
  5. Aube (1) de turbine à gaz suivant la revendication 1, réalisée en tant qu'aube mobile.
  6. Procédé de fabrication d'une aube (1) de turbine à gaz ayant une plateforme (3) et un profilé (5) se raccordant à la face (7) supérieure de la plateforme (3), la plateforme (3) ayant un bord (9) d'attaque et un bord (11) de fuite pour un gaz chaud contournant l'aube (1) de la turbine à gaz, une fente (15) s'étendant parallèlement au bord (9) d'attaque étant ménagée dans la plateforme (3), et il est ménagé dans la plateforme (3) des canaux (17) qui débouchent dans la fente (15) et qui mènent à travers la plateforme (3) à une face (8) inférieure de la plateforme opposée à la face (7) supérieure de la plateforme.
  7. Procédé suivant la revendication 6, dans lequel on ménage la fente (15) dans la plateforme par usinage par érosion.
  8. Procédé suivant la revendication 6, dans lequel on ménage les canaux (17) dans la plateforme (3) au moyen d'un perçage laser.
  9. Procédé suivant la revendication 8, dans lequel on dépose sur la paroi (21), voisine du bord (9) d'entrée, de la fente (15) avant la réalisation du perçage laser, une protection (33) par dispersion de la lumière de sorte que cette paroi (21) de la fente (15) n'est pas endommagée par le rayonnement (37) laser.
EP00125031A 2000-11-16 2000-11-16 Aube de turbine à gaz et procédé de fabrication d'une aube de turbine à gaz Expired - Lifetime EP1207268B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP00125031A EP1207268B1 (fr) 2000-11-16 2000-11-16 Aube de turbine à gaz et procédé de fabrication d'une aube de turbine à gaz
DE50009497T DE50009497D1 (de) 2000-11-16 2000-11-16 Filmkühlung von Gasturbinenschaufeln mittels Schlitzen für Kühlluft
CA002361978A CA2361978A1 (fr) 2000-11-16 2001-11-14 Aube de turbine a gaz et methode de fabrication
JP2001350479A JP4040864B2 (ja) 2000-11-16 2001-11-15 ガスタービン翼とその製造方法
US10/004,478 US6719529B2 (en) 2000-11-16 2001-11-16 Gas turbine blade and method for producing a gas turbine blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP00125031A EP1207268B1 (fr) 2000-11-16 2000-11-16 Aube de turbine à gaz et procédé de fabrication d'une aube de turbine à gaz

Publications (2)

Publication Number Publication Date
EP1207268A1 EP1207268A1 (fr) 2002-05-22
EP1207268B1 true EP1207268B1 (fr) 2005-02-09

Family

ID=8170398

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00125031A Expired - Lifetime EP1207268B1 (fr) 2000-11-16 2000-11-16 Aube de turbine à gaz et procédé de fabrication d'une aube de turbine à gaz

Country Status (5)

Country Link
US (1) US6719529B2 (fr)
EP (1) EP1207268B1 (fr)
JP (1) JP4040864B2 (fr)
CA (1) CA2361978A1 (fr)
DE (1) DE50009497D1 (fr)

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US7144215B2 (en) * 2004-07-30 2006-12-05 General Electric Company Method and apparatus for cooling gas turbine engine rotor blades
US7198467B2 (en) * 2004-07-30 2007-04-03 General Electric Company Method and apparatus for cooling gas turbine engine rotor blades
US7131817B2 (en) * 2004-07-30 2006-11-07 General Electric Company Method and apparatus for cooling gas turbine engine rotor blades
US7217096B2 (en) * 2004-12-13 2007-05-15 General Electric Company Fillet energized turbine stage
US7134842B2 (en) * 2004-12-24 2006-11-14 General Electric Company Scalloped surface turbine stage
US7249933B2 (en) * 2005-01-10 2007-07-31 General Electric Company Funnel fillet turbine stage
US7309212B2 (en) * 2005-11-21 2007-12-18 General Electric Company Gas turbine bucket with cooled platform leading edge and method of cooling platform leading edge
US7553534B2 (en) * 2006-08-29 2009-06-30 General Electric Company Film cooled slotted wall and method of making the same
US7766618B1 (en) * 2007-06-21 2010-08-03 Florida Turbine Technologies, Inc. Turbine vane endwall with cascading film cooling diffusion slots
US8057178B2 (en) * 2008-09-04 2011-11-15 General Electric Company Turbine bucket for a turbomachine and method of reducing bow wave effects at a turbine bucket
US8292587B2 (en) * 2008-12-18 2012-10-23 Honeywell International Inc. Turbine blade assemblies and methods of manufacturing the same
US8221055B1 (en) * 2009-07-08 2012-07-17 Florida Turbine Technologies, Inc. Turbine stator vane with endwall cooling
US9630277B2 (en) * 2010-03-15 2017-04-25 Siemens Energy, Inc. Airfoil having built-up surface with embedded cooling passage
US8540486B2 (en) * 2010-03-22 2013-09-24 General Electric Company Apparatus for cooling a bucket assembly
US8398364B1 (en) * 2010-07-21 2013-03-19 Florida Turbine Technologies, Inc. Turbine stator vane with endwall cooling
US8870536B2 (en) * 2012-01-13 2014-10-28 General Electric Company Airfoil
US9091180B2 (en) 2012-07-19 2015-07-28 Siemens Energy, Inc. Airfoil assembly including vortex reducing at an airfoil leading edge
EP3232001A1 (fr) 2016-04-15 2017-10-18 Siemens Aktiengesellschaft Aube rotorique de turbine
US10590781B2 (en) * 2016-12-21 2020-03-17 General Electric Company Turbine engine assembly with a component having a leading edge trough
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Also Published As

Publication number Publication date
EP1207268A1 (fr) 2002-05-22
JP4040864B2 (ja) 2008-01-30
CA2361978A1 (fr) 2002-05-16
DE50009497D1 (de) 2005-03-17
JP2002213203A (ja) 2002-07-31
US20020110454A1 (en) 2002-08-15
US6719529B2 (en) 2004-04-13

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