EP0995880B1 - Aube de turbine - Google Patents

Aube de turbine Download PDF

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Publication number
EP0995880B1
EP0995880B1 EP99810915A EP99810915A EP0995880B1 EP 0995880 B1 EP0995880 B1 EP 0995880B1 EP 99810915 A EP99810915 A EP 99810915A EP 99810915 A EP99810915 A EP 99810915A EP 0995880 B1 EP0995880 B1 EP 0995880B1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
vane
blade
intermetallic
felt
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
EP99810915A
Other languages
German (de)
English (en)
Other versions
EP0995880A3 (fr
EP0995880A2 (fr
Inventor
Alexander Dr. Beeck
Mohamed Dr. Nazmy
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 Schweiz 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 Schweiz AG filed Critical Alstom Schweiz AG
Publication of EP0995880A2 publication Critical patent/EP0995880A2/fr
Publication of EP0995880A3 publication Critical patent/EP0995880A3/fr
Application granted granted Critical
Publication of EP0995880B1 publication Critical patent/EP0995880B1/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
    • F01D5/182—Transpiration cooling
    • F01D5/183—Blade walls being porous
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F7/00—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression
    • B22F7/002—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of porous nature
    • B22F7/004—Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting wherein at least one part is obtained by sintering or compression of porous nature comprising at least one non-porous part
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C49/00—Alloys containing metallic or non-metallic fibres or filaments
    • C22C49/14—Alloys containing metallic or non-metallic fibres or filaments characterised by the fibres or filaments
    • 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

Definitions

  • the invention relates to a turbine blade with a metallic Blade body and a protective cover, made of a porous Intermetallik felt is formed and formed in the blade body of the turbine blade cooling air ducts are, which lead to the intermetallic felt to supply this with cooling air.
  • DE 42 41 420 C1 is a consisting of a titanium alloy compressor blade produced, which is provided with an abrasive Schaufelanzanztation.
  • the Shovel armor consists of a nickel matrix enclosed in boron nitride particles are. This blade armor is preferably at the blade tip intended.
  • a seal assembly is known, the one passage seal between a rotating and a non-rotating part.
  • the sealing arrangement has a surface seal arranged on one of the two parts and an edge portion opposite to the surface seal arranged and attached to the other part.
  • the edge part faces into the surface seal protruding teeth on which grooves in rotation in the surface seal cut, whereby the seal assembly forms a labyrinth seal.
  • the surface seal of this known sealing arrangement is composed of metal fibers, which form a mat or felt-like construction.
  • This material is made by sintering a matrix of arbitrarily oriented metal fibers at a high Temperature and reduced pressure produced, with a completely matted Structure of metal fibers forms, the metal bonds at all points of contact comprising the fibers.
  • the sintered material is characterized by an apparent Density that is considerably lower than the density of the fibers themselves.
  • the low Density of the sintered fiber material is approximately in the range of 14 to 30% and thus these materials differ from sintered powdered materials, which have a density of more than 30%.
  • GB 2 053 367 A shows a cooled gas turbine with one rotating Shovels opposite shielding.
  • the shield is made of a Cross-section rectangular tubular ring formed in its interior Can absorb cooling air.
  • On the wall opposite the blades of the Ringes are introduced holes and this wall is outside with a porous Layer provided, which can be penetrated by the cooling air.
  • the porous one Layer consists of a material sintered from small balls.
  • the balls are formed of a nickel-based superalloy.
  • DE 2 038 047 describes a structural provision to guide vanes, within the flow space of a steam turbine, in particular a saturated and wet steam turbine, is arranged and used for drainage of the surfaces of each Guide vanes is used.
  • the vane To the by dropping water to the surfaces of the Blades of wet steam turbines to reduce erosion caused or to avoid, the vane provides drainage channels with porous, liquid-permeable material made of metallic materials or their Alloys is made, filled.
  • porous, liquid-permeable Material is solely for targeted water removal from the interior of a steam turbine.
  • DE 33 27 218 A1 describes a thermally highly stressed, cooled component,
  • a turbine blade for the sake of reducing the Heat load is coated with a metal felt layer, in turn, turn is covered with an additional, ceramic thermal barrier coating.
  • the metal felt layer serves as an elastic carrier material for the ceramic Thermal barrier coating (see page 4, lines 33 to page 5, line 2, page 6, 1. Paragraph and page 7, lines 2 to 7), but the metal felt layer also comes one heat dissipation effect, especially cooling air over cooling air guide grooves 3 (see 1) is supplied to the underside of the metal felt layer to these locally to cool and in this way to optimum heat dissipation through the Thermal insulation layer 6 passing through heat.
  • the invention is based on the object, a turbine blade with a metallic Blade body and a protective cover, made of a porous Intermetallik felt is formed and in the blade body of the turbine blade cooling air ducts are formed, which open at the intermetallic felt to this with cooling air supply, so educate, that the turbine blade is better cooled than it in the case of the prior art is possible. This should also the efficiency the turbine can be increased.
  • the object is achieved by a turbine blade having the features of claim 1 solved.
  • Advantageous embodiments of the invention are specified in the subclaims.
  • the turbine blade according to the invention is characterized in that the intermetallic felt based on an iron or nickel-aluminide alloy, with mixing proportions between Fe: Al or Ni: Al of approx. 50:50, whereby with the ratio the Atomic ratio is meant.
  • the intermetallic felt based on an iron or nickel-aluminide alloy, with mixing proportions between Fe: Al or Ni: Al of approx. 50:50, whereby with the ratio the Atomic ratio is meant.
  • ratios between 40:60 to 60:40 are to include metallic felts obtained, whose oxidizability is very weak, which on the one hand the Life of such metallic felts can be significantly increased and the others keep their felt structure longer.
  • iron or nickel-aluminide alloy further to mix substances or elements of the respective alloy, for example Ta, Nb, Cr, B, Si, Zr or Ga.
  • Essential in the admixture of additional elements is that the atomic Mixing ratio between Fe and Al or Ni and Al in the order of magnitude stays at 50:50.
  • cooling channels are provided according to the invention in the protective coating, which, the Blade body facing, open in the region of the cooling channels. In this way can be ensured that the intermetallic felt additionally increased by cooling air is flowed through. A risk of turbine blade overheating can thus be excluded.
  • the porous intermetallic felt on the surface of the blade body a introduced into this cooling air not immediately with the Hot gases of the turbine in contact, but occurs gradually and on a larger Area distributed through the intermetallic felt.
  • the intermetallic felt the higher surface temperatures than conventional materials for turbine blades can thereby be intensively cooled, causing the turbine blade with a compared to a turbine blade, in which the cooling air ducts directly emerge at the surface, extremely small amount of cooling air to operating temperature can be held. Because the amount of cooling air due to the better heat transfer is much lower, the efficiency of the turbine is accordingly increases because less cooling air does not affect the energy supply in the combustion chamber participates and reduces the efficiency of the turbine.
  • the turbine blade according to the invention allows because of the smaller amount of cooling air and the improved aerodynamics a considerable increase in efficiency a turbine equipped with these turbine blades.
  • the intermetallic felt is also insensitive to mechanical loads, such as. Foreign body impact, since these only small, local deformations However, neither the function of the cooling system essential nor the impair the basic function of the blade.
  • Fig. 1 shows a turbine blade 1 according to the invention in section.
  • the turbine blade 1 has a known aerodynamic shape and is composed of two Side walls 2, 3 formed.
  • the turbine blade 1 has an approximately semicircular outer surface which is flush with the outer surfaces the side walls 2, 3 passes.
  • the side walls 2, 3 run from Leading edge region 4 in the direction of a trailing edge 5 together, wherein they are in Area of the trailing edge 5 are firmly connected to each other.
  • Adjacent to the im Section about semicircular leading edge region 4 is between the side walls 2, 3 a cross bar 6 is arranged, the gap between the two Side walls 2, 3 divided into two cooling air channels 7, 8, through which the Turbine blade 1 cooling air is supplied.
  • the leading edge region 4 of the turbine blade is formed in two layers, wherein an inner layer by an approximately annular segment-shaped leading edge part. 9 and an outer layer formed by an intermetallic felt Protective cover 10 are formed.
  • the approximately circular segment-shaped leading edge part 9 is connected to the side walls 2, 3rd each connected via a transition part 11, 12.
  • the transition parts 11, 12 form a tapered region continuously tapering towards the leading edge portion.
  • the two side walls 2, 3, the cross bar 6, the transition parts 11, 12 and the Voderkantenteil 9 are integrally formed of metal and form a Vane base body.
  • the leading edge part 9 is provided with approximately radially extending cooling holes 13, which open into cooling channels 13 ', which protrude into the protective cover 10.
  • further cooling holes 14 may be introduced, which are the side walls 2, 3 running from the inside to the outside in the direction of the trailing edge 5 enforce.
  • the Einschnatingungs Council in the leading edge region 4 forms a recess for Take-up of the protective coating made of the intermetallic felt 10.
  • the intermetallic felt consists of a felt-like material, such as for example, from "VDI Report 1151, 1995, Metallic High Temperature Fibers by melt extraction - manufacture, properties and applications, Stephani et al., page 175ff. "There, fibers are melt-extracted made, pressed the fibers thus produced and sintered.
  • the thus formed Felt-like material is used as a filter and as a catalyst support.
  • This felt-like material is made of intermetallic fibers and used as a protective cover for a turbine blade. To do this advantageously used iron or nickel-based intermetallic phases.
  • the intermetallic felt according to the invention consists of an iron-aluminide or nickel-aluminide alloy with an alloying ratio between both alloying partners from about 50:50.
  • the protective cover 10 of intermetallic felt is in the recess of the turbine blade 1 fixed by high temperature soldering, the solder a higher Melting point than the application temperature in the turbine has.
  • the porosity of the protective coating 10 may be determined by the parameters of the manufacturing process how to set the pressing pressure and sintering temperature. This is the Flow resistance of the protective coating 10 to the respective requirements adjustable.
  • the thickness of the protective coating is e.g. in the range of 2-8 mm.
  • Cooling air is during operation of the turbine through the cooling channel 7 the leading edge part 9 supplied, wherein the cooling air formed by the formed in the leading edge part Holes 13,13 'outward into the protective coating 10 of intermetallic felt flows.
  • the incoming air is distributed over a surface area and flows through the felt. Due to the large contact area between the Intermetallic felt and cooling air have excellent heat transfer properties, so that the vast heat capacity of the cooling air for cooling the Protective cover 10 is exploited.
  • the trailing edge 5 of the turbine blade may be provided with a formed from intermetallic felt protective cover or on to provide a protective coating on the entire surface of the turbine blade.
  • the protective cover may be formed with variable thickness and / or variable porosity be.
  • the porosity may e.g. in the course of the leading edge region 4 to the trailing edge 5, whereby the intermetallic felt on the more exposed to heat Front edge absorbs more cooling air than in the remaining area. It may also be appropriate to vary the porosity along the span.
  • the intermetallic felt may be e.g. also with a corrosion protection layer or a Heat protection layer to be coated.
  • a heat protection layer a so-called TBC (Thermal Barrier Coating) coating typically used is formed of a ceramic base material.
  • the felt can by his Deformability Differences in the thermal expansion behavior of the protective layer and the base material.
  • Another advantage of the protective coating according to the invention is that it faces Foreign body damage is insensitive, that is, that usually only local deformations are generated, which hardly affect the function of the turbine blade.
  • the protective cover may be to loosen during operation and yet the scoop - at reduced Efficiency - still functional.
  • the turbine blades according to the invention are for use in a gas turbine designed.
  • the leading edges of the blades of the first turbine guide row are to be provided with the protective coating of the invention, since they are particularly strongly exposed to the hot gases of the turbine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • General Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Composite Materials (AREA)
  • Manufacturing & Machinery (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (15)

  1. Aube de turbine avec un corps d'aube métallique et un revêtement de protection (10) qui est formé d'un feutre intermétallique poreux et dans le corps d'aube de l'aube de turbine (1) sont formés des alésages de refroidissement (13), qui débouchent au niveau du feutre intermétallique, afin d'approvisionner ce dernier en air de refroidissement, caractérisée en ce que le feutre intermétallique est à base d'un alliage d'aluminiure de fer ou de nickel, avec des proportions de mélange entre Fe : Al ou Ni : Al d'environ 50 : 50, et
    en ce que le revêtement de protection présente des canaux de refroidissement (13') qui, tournés vers le corps d'aube, débouchent dans la zone des alésages de refroidissement (13).
  2. Aube de turbine selon la revendication 1, caractérisée en ce que l'alliage d'aluminiure de fer ou de nickel présente des composants supplémentaires de Ta, Nb, Cr, B, Si, Zr ou Ga.
  3. Aube de turbine selon la revendication 1 ou 2, caractérisée en ce que des canaux de refroidissement (13') sont prévus, qui traversent entièrement le revêtement de protection.
  4. Aube de turbine selon l'une des revendications 1 à 3, caractérisée en ce que des canaux de refroidissement (13') sont prévus, qui ne pénètrent que partiellement dans le revêtement de protection.
  5. Aube de turbine selon l'une des revendications 1 à 4, caractérisée en ce qu'une arête avant (4) du corps d'aube est pourvue du feutre intermétallique.
  6. Aube de turbine selon l'une des revendications 1 ou 5, caractérisée en ce qu'une arête arrière (5) du corps d'aube est pourvue du feutre intermétallique.
  7. Aube de turbine selon l'une des revendications 1 à 6, caractérisée en ce que le corps d'aube est pourvu d'un creux, dans la zone pourvue du feutre intermétallique, dans lequel est disposé le feutre intermétallique de telle sorte qu'il isole à fleur de la zone limitrophe du corps d'aube.
  8. Aube de turbine selon l'une des revendications 1 à 7, caractérisée en ce que l'ensemble du corps d'aube est revêtu avec le feutre intermétallique.
  9. Aube de turbine selon l'une des revendications 1 à 8, caractérisée en ce que le feutre intermétallique est formé de fibres intermétalliques comprimées et frittées.
  10. Aube de turbine selon la revendication 9, caractérisée en ce que le feutre intermétallique est formé d'une phase intermétallique à base de fer ou à base de nickel.
  11. Aube de turbine selon l'une des revendications 1 à 10, caractérisée en ce que les fibres du feutre intermétallique sont enduites.
  12. Aube de turbine selon la revendication 11, caractérisée en ce que les fibres du feutre intermétallique sont enduites d'une couche anticorrosive et / ou d'un revêtement calorifuge.
  13. Aube de turbine selon l'une des revendications 1 à 12, caractérisée en ce que l'aube de turbine est disposée au niveau du rotor d'une turbomachine.
  14. Aube de turbine selon la revendication 12, caractérisée en ce que les aubes de turbine disposées dans une première rangée de guidage sont pourvues du revêtement de protection formé de feutre intermétallique.
  15. Aubes de turbine selon la revendication 13 ou 14, caractérisées en ce que la turbomachine est une turbine à gaz.
EP99810915A 1998-10-19 1999-10-07 Aube de turbine Expired - Lifetime EP0995880B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19848104A DE19848104A1 (de) 1998-10-19 1998-10-19 Turbinenschaufel
DE19848104 1998-10-19

Publications (3)

Publication Number Publication Date
EP0995880A2 EP0995880A2 (fr) 2000-04-26
EP0995880A3 EP0995880A3 (fr) 2002-01-23
EP0995880B1 true EP0995880B1 (fr) 2003-12-03

Family

ID=7884915

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99810915A Expired - Lifetime EP0995880B1 (fr) 1998-10-19 1999-10-07 Aube de turbine

Country Status (3)

Country Link
US (1) US6241469B1 (fr)
EP (1) EP0995880B1 (fr)
DE (2) DE19848104A1 (fr)

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DE19848104A1 (de) 2000-04-20
EP0995880A3 (fr) 2002-01-23
DE59907926D1 (de) 2004-01-15
EP0995880A2 (fr) 2000-04-26
US6241469B1 (en) 2001-06-05

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