EP0995880A2 - Aube de turbine - Google Patents

Aube de turbine Download PDF

Info

Publication number
EP0995880A2
EP0995880A2 EP99810915A EP99810915A EP0995880A2 EP 0995880 A2 EP0995880 A2 EP 0995880A2 EP 99810915 A EP99810915 A EP 99810915A EP 99810915 A EP99810915 A EP 99810915A EP 0995880 A2 EP0995880 A2 EP 0995880A2
Authority
EP
European Patent Office
Prior art keywords
turbine blade
felt
intermetallic
turbine
blade according
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
EP99810915A
Other languages
German (de)
English (en)
Other versions
EP0995880B1 (fr
EP0995880A3 (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
ABB Asea Brown Boveri Ltd
Alstom SA
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Alstom SA, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
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 intermetallic felt is formed and cooling air channels are formed in the blade body of the turbine blade which open on the intermetallic felt to supply it with cooling air.
  • a sealing arrangement which has a passage to 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 part that is opposite the surface seal arranged and attached to the other part.
  • the edge part points into the surface seal protruding teeth on the grooves when rotating in the surface seal cut, whereby the seal assembly forms a labyrinth seal.
  • the surface seal of this known seal arrangement is composed of metal fibers, which form a mat or felt-like construction.
  • This material is achieved by sintering a matrix of randomly oriented metal fibers at a high Temperature and reduced pressure, creating a completely matted Structure made of metal fibers that forms metal bonds at all contact points which has fibers.
  • the sintered material is characterized by an apparent Density, which is considerably less than the density of the fibers themselves. The low The density of the sintered fiber material is approximately in the range from 14 to 30% and thus these materials differ from sintered powdered materials, that have a density of more than 30%.
  • Have this type of surface seals Proven as it has both the required strength, rigidity and compactness have as well as elastic, crushable and rubable.
  • GB 2 053 367 A shows a cooled gas turbine with one rotating Blade opposite shield.
  • the shield is made of an im Cross-section rectangular tubular ring formed in its interior Can absorb cooling air.
  • On the wall of the Rings are holes and this wall is porous on the outside Provide layer, which can be penetrated by the cooling air.
  • the porous Layer consists of a material sintered from small balls.
  • the balls are made of a nickel-based super alloy.
  • DE 2 038 047 describes a structural precaution on guide vanes that are inside the flow space of a steam turbine, in particular a saturated and wet steam turbine, is arranged and to drain the surfaces of each Guide vanes.
  • the guide vane provides drainage channels that are covered with porous, liquid-permeable material made of metallic materials or their Alloys is made, are filled.
  • porous, liquid-permeable Material is used solely for the targeted removal of water from the interior of a steam turbine.
  • DE 33 27 218 A1 describes a thermally highly stressed, cooled component, in particular a turbine blade which, for the sake of reducing the Thermal stress is covered with a metal felt layer, which in turn is covered with an additional, ceramic thermal insulation layer.
  • the metal felt layer serves as an elastic carrier material for the ceramic Thermal insulation layer (see page 4, lines 33 to page 5, line 2, page 6, 1. Paragraph and page 7, lines 2 to 7), but there is also a metal felt layer heat-dissipating effect, especially since cooling air via cooling air guide grooves 3 (see 1) is fed to the underside of the metal felt layer to make it local to cool and in this way to optimal heat dissipation by the Thermal insulation layer 6 to pass through flowing heat.
  • the invention has for its object a turbine blade with a metallic Blade body and a protective cover made of a porous intermetallic felt is formed and in the blade body of the turbine blade cooling air channels are formed, which open on the intermetallic felt to this with cooling air supply in such a way that the turbine blade can be cooled better than it is possible in the case of the prior art. This is also intended to increase efficiency the turbine can be increased.
  • the turbine blade according to the invention is characterized in that the intermetallic felt based on an iron or nickel-aluminide alloy, with mixed proportions between Fe: Al and Ni: Al of approx. 50:50, with the ratio that Atomic ratio is meant.
  • the intermetallic felt based on an iron or nickel-aluminide alloy with mixed proportions between Fe: Al and Ni: Al of approx. 50:50, with the ratio that Atomic ratio is meant.
  • Metallic felts are also said to comprise ratios between 40:60 to 60:40 obtained, the oxidizability is very weak, which on the one hand The lifespan of such metallic felts can be increased significantly and others retain their felt structure for longer.
  • iron or nickel-aluminide alloy Add substances or elements of the respective alloy, e.g. Ta, Nb, Cr, B, Si, Zr or Ga. It is essential when adding additional elements that the atomic Mixing ratio between Fe and Al or Ni and Al in the order of magnitude remains at 50:50.
  • cooling channels are provided according to the invention in the protective coating Blade body facing, open in the area of the cooling channels. In this way it can be ensured that the intermetallic felt is additionally increased by cooling air is flowed through. This can create a risk of turbine blade overheating be excluded.
  • the porous intermetallic felt on the surface of the blade body does not immediately cool air introduced into it with the Hot gases come into contact with the turbine, but occurs gradually and on a larger scale Surface distributed through the intermetallic felt.
  • the intermetallic felt the higher surface temperatures than conventional materials for turbine blades can be intensively cooled as a result, whereby the turbine blade with a compared to a turbine blade, in which the cooling air ducts directly emerge on the surface, extremely small amount of cooling air at operating temperature can be held. Because the amount of cooling air because of better heat transfer the efficiency of the turbine is correspondingly much lower increased because less cooling air does not affect the energy supply in the combustion chamber participates and reduces the efficiency of the turbine.
  • the gradual flow of cooling air through the intermetallic felt causes the exit velocity of the cooling air on the surface of the turbine blade is very low and does not adversely affect the aerodynamics in the manner known hitherto. This is especially true if the intermetallic felt is on the leading edge the turbine blade is arranged because then, unlike conventional ones cooled turbine blades, the flow behavior of the turbine blade impinging gases are not adversely affected by counter-flowing cooling air becomes.
  • the cooling channels incorporated in the intermetallic felt which the felt layer does not necessarily push through completely, but only partially penetrate the felt, ensure that the protective cover is optimally supplied with cooling air.
  • 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. Impact of foreign objects, as these only result in small, local deformations lead, but neither the function of the cooling system essential nor affect 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 made of two Side walls 2, 3 formed.
  • the turbine blade has in the leading edge region 4 1 has an approximately semicircular outer surface that is flush with the outer surfaces the side walls 2, 3 merges.
  • the side walls 2, 3 run from Front edge area 4 together in the direction of a rear edge 5, wherein they in Area of the rear edge 5 are firmly connected.
  • Adjacent to the im Cut approximately semicircular leading edge area 4 is between the side walls 2, 3 a transverse web 6 is arranged, the space 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 front edge region 4 of the turbine blade is designed in two layers, wherein an inner layer by a front edge part 9 which is approximately ring segment-shaped in section and an outer layer by an intermetallic felt Protective cover 10 are formed.
  • the approximately circular segment-shaped front edge part 9 is with the side walls 2, 3 each connected via a transition part 11, 12.
  • the transition parts 11, 12 form a constriction area continuously tapering toward the leading edge portion.
  • the two side walls 2, 3, the crossbar 6, the transition parts 11, 12 and the leading edge part 9 are formed in one piece from metal and form one Blade body.
  • the front edge part 9 is provided with approximately radially extending cooling bores 13, which open into cooling channels 13 'which protrude into the protective coating 10.
  • further cooling bores 14 can be introduced, which form the side walls 2, 3 sloping from the inside to the outside towards the rear edge 5 enforce.
  • the constriction area in the leading edge area 4 forms a recess for Inclusion of the protective cover 10 consisting of the intermetallic felt.
  • the intermetallic felt is made of a felt-like material, such as it, for example, from "VDI Report 1151, 1995, Metallic High Temperature Fibers by melt extraction - manufacture, properties and applications, Stephani et al., page 175ff ".
  • the so educated Felt-like material is used as a filter and as a catalyst carrier.
  • this felt-like material is made from intermetallic fibers and used as a protective covering for a turbine blade.
  • the intermetallic felt consists of an iron-aluminide or nickel-aluminide alloy with an alloy ratio between each of the two alloy partners of about 50:50.
  • These alloys have high heat resistance and high oxidation resistance and advantageous thermal conductivity properties.
  • the above are Properties by choosing the intermetallic phase in a wide range Range adjustable.
  • the protective cover 10 made of intermetallic felt is in the recess of the turbine blade 1 fixed by high temperature soldering, the solder a higher Melting point as the application temperature in the turbine.
  • the porosity of the protective coating 10 can 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 the leading edge part through the cooling channel 7 during operation of the turbine 9 supplied, the cooling air through the formed in the leading edge part Bores 13, 13 'to the outside in the protective cover 10 made of intermetallic felt flows.
  • the incoming air is distributed over an area and flows through the felt. Because of the large contact area between the Intermetallic felt and the cooling air have excellent heat transfer properties, so that the predominant heat capacity of the cooling air for cooling the Protective cover 10 is used. It also works from an intermetallic felt existing protective coating 10 as a thermal insulator against the blade body.
  • the rear edge 5 of the turbine blade with a protective cover made of intermetallic felt to provide a protective coating over the entire surface of the turbine blade.
  • the protective cover can be of variable thickness and / or of variable porosity his.
  • the porosity can e.g. in the course from the leading edge area 4 to the trailing edge 5 remove, causing the intermetallic felt to be more exposed to heat Front edge absorbs more cooling air than in the rest of the area. It can also be useful be to vary the porosity along the span.
  • the intermetallic felt can e.g. also with a corrosion protection layer or Thermal protection layer to be coated.
  • a so-called TBC layer Thermal Barrier Coating
  • the felt can be Deformability Differences in the thermal expansion behavior of the protective layer and balance the base material.
  • Another advantage of the protective coating according to the invention is that it has Foreign body damage is insensitive, i.e. usually only local deformations are generated that hardly affect the function of the turbine blade.
  • the turbine blades according to the invention are for use in a gas turbine designed.
  • the front edges of the blades of the first turbine guide row are to be provided with the protective coating according to the invention, since they are special are strongly exposed to the hot gases of the turbine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Composite Materials (AREA)
  • Manufacturing & Machinery (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
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 true EP0995880A2 (fr) 2000-04-26
EP0995880A3 EP0995880A3 (fr) 2002-01-23
EP0995880B1 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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GB2348276A (en) * 1999-03-20 2000-09-27 Abb Alstom Power Ch Ag Combustion chamber wall
EP1512911A1 (fr) * 2003-09-04 2005-03-09 Rolls-Royce Deutschland Ltd & Co KG Arrangement pour refroidir des éléments soumis à de fortes contraintes thermiques

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Cited By (4)

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Publication number Priority date Publication date Assignee Title
GB2348276A (en) * 1999-03-20 2000-09-27 Abb Alstom Power Ch Ag Combustion chamber wall
GB2348276B (en) * 1999-03-20 2003-07-16 Abb Alstom Power Ch Ag Combustion chamber wall
EP1512911A1 (fr) * 2003-09-04 2005-03-09 Rolls-Royce Deutschland Ltd & Co KG Arrangement pour refroidir des éléments soumis à de fortes contraintes thermiques
US7204089B2 (en) 2003-09-04 2007-04-17 Rolls-Royce Deutschland Ltd & Co Kg Arrangement for the cooling of thermally highly loaded components

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EP0995880B1 (fr) 2003-12-03
EP0995880A3 (fr) 2002-01-23
DE19848104A1 (de) 2000-04-20
US6241469B1 (en) 2001-06-05
DE59907926D1 (de) 2004-01-15

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