EP2907969A1 - Aube de turbine et procédé de fabrication ou de restauration d'une aube de turbine - Google Patents

Aube de turbine et procédé de fabrication ou de restauration d'une aube de turbine Download PDF

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Publication number
EP2907969A1
EP2907969A1 EP14155134.1A EP14155134A EP2907969A1 EP 2907969 A1 EP2907969 A1 EP 2907969A1 EP 14155134 A EP14155134 A EP 14155134A EP 2907969 A1 EP2907969 A1 EP 2907969A1
Authority
EP
European Patent Office
Prior art keywords
airfoil
trailing edge
recesses
turbine blade
wall
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Withdrawn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
EP14155134.1A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Nihal Kurt
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 EP14155134.1A priority Critical patent/EP2907969A1/fr
Priority to PCT/EP2015/050138 priority patent/WO2015120995A1/fr
Publication of EP2907969A1 publication Critical patent/EP2907969A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/005—Repairing methods or devices
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
    • 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 turbine blade having a cast airfoil comprising a suction-side airfoil wall and a pressure-side airfoil wall, said airfoil extending in a spanwise direction from a foot-side end to a head-side end and in a flow-around direction from a leading edge to a trailing edge, immediately upstream of the trailing edge in one of the two airfoil walls along the trailing edge recesses for blowing a coolant are distributed, such that the relevant airfoil wall ends in profile cuts with recesses upstream of the trailing edge.
  • the invention relates to a method for producing or restoring such a turbine blade.
  • cut-back turbine blades In the extensive state of the art, the turbine blades described above are known as so-called cut-back turbine blades.
  • the English term "cut-back" describes in detail that the one, for example the pressure-side, blade wall is cut back relative to the other, then the suction side, blade wall.
  • Recesses result in recesses to which a coolant guided in the interior of the airfoil can be fed via openings opening therefrom.
  • the recesses are dimensioned such that the (pressure side) surface of the remaining (suction side) airfoil wall is cooled to the trailing edge by the outflowing coolant.
  • comparatively narrow trailing edges are provided which are aerodynamically less lossy than trailing edges of turbine blades which have a central blow-off.
  • the object of the invention is therefore to provide a turbine blade and the disclosure of a method for producing or restoring a turbine blade, which has a prolonged life.
  • the object directed to the turbine blade is achieved by the features of claim 1 and the object directed to the method is achieved by a method according to the features of claim 6.
  • the turbine blade of the aforementioned type comprises according to the invention a plate-shaped cover member, by which at least one of the recesses is partially covered.
  • the method of manufacturing a turbine blade or restoring an operationally stressed turbine blade provides that after casting a blade having a suction side airfoil wall and a pressure side airfoil wall, said airfoil extending in a spanwise direction from a root end to a head end and in a flow direction from one Leading edge extends to a trailing edge, wherein immediately upstream of the trailing edge in one of the airfoil walls along the trailing edge recesses for blowing a coolant are distributed, such that the relevant airfoil wall ends in profile cuts with recesses upstream of the trailing edge, at least one of the recesses by the attachment, in particular Welding a cover is partially covered.
  • the invention is based on the recognition that the lifetime-shortening cracks in the region of the trailing edge arise because the cooling fluid flowing out of the openings into the recesses moves too fast with the airfoil flowing around the airfoil Hot gas mixed.
  • the portion of the pressure-side recess on the pressure side exposed suction-side trailing edge is flowed around by a fluid mixture which is hotter than originally provided.
  • the blade material is no longer sufficiently cooled in the region of the trailing edge.
  • the local thermal overheating occurring there leads to mechanical stresses that cause the material to age prematurely there and possibly cause it to rupture.
  • the invention proposes to provide a cover in the region of the trailing edge which is suitable for guiding the coolant flowing in the recess region longer along the blade leaf wall, even in the cut-away region of the cast turbine blade, thus better improving the cast material of the blade against the effects of the hot gas to protect. This reduces impermissibly high thermal influences and thermal stresses in the cast material of the airfoil, which increases the service life of said turbine blade.
  • the plate-shaped cover can be made of the same material as the cast airfoil. But it can also be made of a different material, such as Inconel 617.
  • the cover is to be dimensioned in its dimensions so that the recess is not completely closed, as further a residual opening is required, from which the coolant can flow. Furthermore, the cover should not serve to throttle the amount of coolant flowing out. In other words, the amount of effluent Coolant is determined solely by the geometry of the interior of the cast airfoil.
  • the plate-shaped cover is angled at two of its edges to form flanges so as to be able to mechanically load this higher.
  • the flanges of the cover can be dimensioned so that they represent a positioning aid in securing the cover in the recess to ensure a step-free arrangement between the hot gas Umströmungs Strets.
  • aerodynamic losses can be kept low in the hot gas.
  • At least one of the recesses arranged in the spanwise direction in the middle region is partially covered by a cover element and a plurality of recesses arranged in the spanwise direction on the foot side and / or on the head side are free of cover.
  • the cover element is welded to the airfoil wall.
  • the invention thus relates to a turbine blade with a cast airfoil comprising a suction-side airfoil wall and a pressure-side airfoil wall extending in a spanwise direction from a foot-side end to a head-side end and in a flow-around direction from a leading edge to a trailing edge, immediately upstream of the trailing edge in one of the two airfoil walls recesses for blowing a coolant along the trailing edge are distributed such that the relevant airfoil wall ends in profile cuts with recesses upstream of the trailing edge.
  • at least one of the recesses arranged in the cast airfoil wall is maximally partially covered by a plate-shaped cover element.
  • FIG. 1 shows a side view of a turbine blade 10 for a gas turbine.
  • the turbine blade 10 is designed according to this embodiment as a guide blade of a turbine stage monolithic and produced by casting.
  • the turbine blade 10 comprises, in addition to a foot-side platform 12 and a head-side platform 15 an aerodynamically curved blade 14 arranged therebetween.
  • the base-side platform 12 is arranged in the installed state of the turbine blade 10 in an axially flowed gas turbine radially outward and the head-side platform 15 radially inside.
  • the airfoil 14 has a front edge 16 from which both a pressure-side airfoil wall 18 (FIG. FIG. 2 ) as well as a suction side airfoil wall 20 to a trailing edge 19 extend.
  • a Spannweiteraum which coincides in the installed state with the radial direction of the gas turbine, extending from the blade end 24 to a blade end 26 side.
  • the cross section along the section line II-II FIG. 1 shows FIG. 2 ,
  • the section line II-II through the airfoil 14 of the turbine blade 10 is selected so that its aerodynamically curved contour is shown.
  • This contour is also referred to as a profile, which is why such sections are also referred to as profile sections.
  • the sectional planes of the profile sections are generally perpendicular to the spanwise direction of the airfoil.
  • FIG. 1 can be seen immediately upstream of the trailing edge 19 on the pressure side a plurality of recesses 28 along the trailing edge 19 distributed and each separated by webs 34 from each other.
  • Each of these recesses 28 communicates fluidly with a cavity 31 of the turbine blade 10.
  • This cavity 31 is supplied via a foot side or head side arranged access coolant, which The turbine blade 10 can also leave through the recesses 28.
  • the cavity 31 in the airfoil interior is divided into passages 30 by ribs 32 extending from the pressure-side airfoil wall 18 to the suction-side airfoil wall 20 and extending from the foot region to the airfoil tip region.
  • the passages 30 can be flowed through sequentially, in parallel or in any combination, by a coolant, for example cooling air, whereby the coolant flowing in the passage 30 adjacent to the trailing edge 19 is guided through channels 35 to the recesses 28.
  • a coolant for example cooling air
  • the cooling air leaves the cast airfoil 14 through an opening 37 and flows into the recesses 28 before it leaves the turbine blade 10 completely.
  • a trailing edge 22 of the pressure-side airfoil wall 18 lies upstream of the recess 28 for profile sections.
  • both a trailing edge 21 of the suction-side airfoil wall 18 coincides with the pressure-side trailing edge 22.
  • FIG. 1 schematically illustrated turbine blade 10 to a turbine blade 10 with a so-called cut-back trailing edge.
  • the recesses 28 set immediately upstream of the trailing edge 19, the sides facing the pressure side of the suction side airfoil wall 20 free.
  • FIG. 3 shows the in FIG. 1 with the detail X highlighted area of the trailing edge 19 of the turbine blade 10 in a perspective view.
  • a cover 36 is arranged in one of the recesses 28 shown. Through the cover member 36 is a part of that imaginary surface of the recess 28, which would coincide with the corresponding surface 42 of the airfoil 18, formed. In other words, the cast pressure-side airfoil wall 18 is lengthened by the subsequently attached cover element 36. As a result, the exiting from the openings 37 cooling air over a longer distance along the exposed through the recesses 28 to the pressure side facing surface 38 of the suction side wall 20 is performed as in recesses 28 without such a cover.
  • the cover element 36 is embodied substantially rectangular and thus has transversely projecting flanges 40 at its two longitudinal edges, so that the cover element 36 according to this exemplary embodiment has a U-shape.
  • the size of the flanges 40 is selected so that incorrect positioning of the cover member 36 during assembly thereof can be prevented. A faulty positioning of the web of the cover element connecting the two flanges 40 could reduce the resulting outflow cross section of the cooling air flowing out of the turbine blade 10, whereby the cooling effect would be reduced. However, this throttling effect is prevented due to the angled edges.
  • FIG. 4 shows a second embodiment of the cover of a recess 28 at the trailing edge 19 of the turbine blade 10.
  • the cover 36 is designed purely as a plate and arranged so that it is step-free with the surface 42 of the pressure-side airfoil wall 18.
  • the cover member 36 may be mounted on both unused and already used turbine blades 10. As a common and reliable fastening methods both soldering and welding have been found.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP14155134.1A 2014-02-14 2014-02-14 Aube de turbine et procédé de fabrication ou de restauration d'une aube de turbine Withdrawn EP2907969A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP14155134.1A EP2907969A1 (fr) 2014-02-14 2014-02-14 Aube de turbine et procédé de fabrication ou de restauration d'une aube de turbine
PCT/EP2015/050138 WO2015120995A1 (fr) 2014-02-14 2015-01-07 Aube de turbine et procédé de fabrication ou de rectification d'une aube de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14155134.1A EP2907969A1 (fr) 2014-02-14 2014-02-14 Aube de turbine et procédé de fabrication ou de restauration d'une aube de turbine

Publications (1)

Publication Number Publication Date
EP2907969A1 true EP2907969A1 (fr) 2015-08-19

Family

ID=50114274

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EP14155134.1A Withdrawn EP2907969A1 (fr) 2014-02-14 2014-02-14 Aube de turbine et procédé de fabrication ou de restauration d'une aube de turbine

Country Status (2)

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EP (1) EP2907969A1 (fr)
WO (1) WO2015120995A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19961565A1 (de) * 1999-12-20 2001-06-21 Abb Alstom Power Ch Ag Verfahren zur Einstellung des Durchflussvolumens eines Kühlmediums durch eine Turbinenkomponente
EP1288436A2 (fr) * 2001-08-30 2003-03-05 General Electric Company Aube de turbine
US6551063B1 (en) * 2001-12-20 2003-04-22 General Electric Company Foil formed structure for turbine airfoil trailing edge
JP2010043568A (ja) * 2008-08-11 2010-02-25 Ihi Corp タービン翼及びタービン翼後縁部の放熱促進部品
EP2163726A1 (fr) * 2008-09-11 2010-03-17 Siemens Aktiengesellschaft Aube de turbine dotée d'un rebord arrière modulaire et graduée

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19961565A1 (de) * 1999-12-20 2001-06-21 Abb Alstom Power Ch Ag Verfahren zur Einstellung des Durchflussvolumens eines Kühlmediums durch eine Turbinenkomponente
EP1288436A2 (fr) * 2001-08-30 2003-03-05 General Electric Company Aube de turbine
US6551063B1 (en) * 2001-12-20 2003-04-22 General Electric Company Foil formed structure for turbine airfoil trailing edge
JP2010043568A (ja) * 2008-08-11 2010-02-25 Ihi Corp タービン翼及びタービン翼後縁部の放熱促進部品
EP2163726A1 (fr) * 2008-09-11 2010-03-17 Siemens Aktiengesellschaft Aube de turbine dotée d'un rebord arrière modulaire et graduée

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Publication number Publication date
WO2015120995A1 (fr) 2015-08-20

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