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
  • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
  • F01D5/282—Selecting composite materials, e.g. blades with reinforcing 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
  • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
  • F01D5/288—Protective coatings for 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
  • F05D2260/00—Function
  • F05D2260/95—Preventing corrosion
• • 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
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/10—Metals, alloys or intermetallic compounds
  • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
  • F05D2300/133—Titanium
• • 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
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/20—Oxide or non-oxide ceramics
  • F05D2300/21—Oxide ceramics
  • F05D2300/2112—Aluminium oxides
• • 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
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/20—Oxide or non-oxide ceramics
  • F05D2300/21—Oxide ceramics
  • F05D2300/2118—Zirconium oxides
• • 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
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/20—Oxide or non-oxide ceramics
  • F05D2300/22—Non-oxide ceramics
  • F05D2300/226—Carbides
  • F05D2300/2261—Carbides of silicon
• • 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
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
  • F05D2300/603—Composites; e.g. fibre-reinforced
• • 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
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
  • F05D2300/614—Fibres or filaments
• • 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
  • F05D2300/00—Materials; Properties thereof
  • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
  • F05D2300/615—Filler
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
  • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
  • Y10T29/00—Metal working
  • Y10T29/49—Method of mechanical manufacture
  • Y10T29/49316—Impeller making
  • Y10T29/49336—Blade making
  • Y10T29/49337—Composite blade

Definitions

• Turbine blade in particular blade for a steam turbine, and manufacturing method thereof
• the present invention relates to a turbine blade, in particular blade for a steam turbine, and to a method for producing a turbine blade.
• Known turbine blades are usually hollow or solid of a metallic material such. As steel, and are needed for example for steam turbines.
• Turbine supplied steam converted into mechanical work For this purpose, steam turbines comprise at least one high-pressure steam inlet and at least one low-pressure steam outlet.
• a shaft extending through the turbine, the so-called turbine rotor, is driven by turbine blades.
• By coupling the rotor with an electric generator allows a steam turbine z. B. the generation of electrical energy.
• vanes For driving the rotor typically blades and vanes are provided, wherein the blades are attached to the rotor and rotate therewith, whereas the vanes are mostly stationary on a turbine housing (alternatively: on a vane support) are arranged.
• the vanes provide a favorable flow of steam through the turbine to achieve the most efficient energy conversion. In this reaction, the enthalpy of the vapor is reduced in the course between the steam inlet and the steam outlet. This reduces both the temperature and the pressure of the steam.
• the highest possible enthalpy difference between supplied and discharged steam is one to aim for so-called final stage of the steam turbine.
• a relatively low pressure of the steam to be discharged is advantageous.
• the final stage of a steam turbine is usually a limiting assembly with respect to maximum flow area or maximum rotational speed of the rotor, since in this area in particular the centrifugal forces lead to high tensile stresses in the material of the rotor blades.
• the use of turbine blades in lightweight construction eg made of light metal
• this approach failed from the outset because corresponding lightweight construction materials are subject to even faster wear due to drop impact erosion.
• the turbine blade according to the invention is characterized in that at least a portion of the turbine blade is formed by a fiber composite material having a matrix and fibers embedded therein and the matrix has nanoparticles disposed therein and / or distributed thereon.
• the at least partial formation of the turbine blade made of a fiber composite material results in an advantageously reduced weight.
• the nanoparticles to be introduced into the matrix of the fiber composite material or to be attached to the matrix in a simple manner make it possible to achieve a number of advantages.
• the incorporation of nanoparticles into the matrix can improve the adhesion between the fibers and the matrix.
• nanoparticles deposited on the matrix can improve adhesion to adjacent sections of the turbine blade and / or, if the attached nanoparticles form an outer surface of the turbine blade, significantly enhance erosion resistance.
• Surface sections of the turbine blade are formed by the fiber composite material, in particular at locations that are exposed to a particularly high erosion load during operation of the turbine blade and / or contribute relatively strong to the generation of centrifugal force due to their relatively large distance from the rotor axis of rotation.
• Other surface sections and / or core areas may here be made of a different material (eg another fiber composite material or light metal).
• it is provided that substantially the entire surface of the turbine blade is formed by the fiber composite material. This may be exempted z.
• Turbine blade which are covered during operation due to the attachment of the blade root on the turbine rotor and thus are not directly in the vapor flow.
• the fiber composite material is an outer fiber composite layer on a core of the turbine blade.
• the core can be z. B. consist of one of the fiber composite material differing further fiber composite material. This is possible both in the case of a blade surface that is only partially and substantially completely formed by the fiber composite material.
• the preferred core material is a fiber composite material which is expediently selected or optimized with respect to its mechanical properties.
• z. B. a radially elongated fiber composite core advantageous whose fibers have a preferred orientation in the radial direction, in particular z. B. are formed as over the substantially entire radial extent of the core continuous fibers.
• the "further fiber material” already mentioned above, which forms the optionally provided turbine blade core, can be obtained from the (first-mentioned) fiber composite material z. B. with respect to the matrix (resin system) and / or differ in the type of fiber.
• a core of CFRP carbon fiber reinforced plastic
• GRP glass fiber reinforced
• the two matrix materials may differ, or be identically provided (for example, both as an epoxy resin).
• a difference in fiber type between the two materials core material and a surface area of the turbine blade forming material
• a difference in fiber length (or fiber length distribution) and / or fiber orientation (or fiber orientation distribution) may also be provided.
• nanoparticulated fiber composite material is used as an outer fiber composite layer on one of a further fiber composite material
• Fiber composite material "formed core of the turbine blade is provided, and here the same synthetic resin system is provided as terixmaterial, the production of the turbine blade can advantageously be carried out with an infiltration step, in which, for example, in a mold, a fiber material inserted therein infiltrated
• a fiber material inserted therein infiltrated
• nanoparticles to be provided at least to a superficial region of the turbine blade may be admixed with the liquid or viscous resin system used for this purpose Admit resin system, which flows into the mold.
• Another manufacturing method by means of which a fiber composite core and a superficial fiber composite layer of the turbine blade can be made even more universal and independent of each other, is to substantially complete the vane core in a first step (eg, from only partially cured "further fiber composite material") in a second step, forming at least a part or substantially the entire surface of the turbine blade through the (first) fiber composite material.
• the blade core made in the first step eg made of CFRP
• the turbine blade also has another core material (preferably a "further fiber material", but also conceivable, for example, metal), then this core may be hollow or solid.
• the fibers embedded therein are significantly shorter than the maximum, measured along the respective surface portion distance between two points of this surface portion. In other words, no generally continuous fibers are provided over the surface section (s) concerned.
• the fibers each have a length in the range of 1 to 10 cm, in particular 1 to 5 cm.
• the length of the individual fibers varies in a relatively narrow range around an average value of the fiber length.
• z it may be the case that the upper quartile of the fiber length distribution is at most a factor of 1.5 greater than the lower quartile of the fiber length distribution.
• the fiber length distribution it is by no means essential in the context of the invention for the fiber length distribution to be uniform for the surface area (s) concerned. Rather, a locally varying fiber length distribution, in particular locally varying mean fiber length, could also be provided.
• the advantage of a fiber length which is significantly lower (for example by at least a factor of 10) than the blade length is, above all, that improved ductility and homogeneity of the fiber composite can be achieved in comparison with a continuous fiber arrangement.
• the fibers are embedded in the matrix in a disordered manner, ie if appreciable portions of all (at least in the surface plane) fiber orientations are present. This is not intended to exclude that in this disordered Fasereinbettung statistically considered a preferred direction (in particular, for example, in the radial direction) is present. In this case, it can be provided that the extent and / or the orientation of the preferred direction varies locally over the surface section (s) concerned.
• the embedding of the fibers in loose form or in the form of a fiber fleece is preferred over their embedding as fabric, braid or the like. It has proven to be particularly advantageous if the proportion of fibers in the fiber composite material is in the range from 20 to 70% by volume, in particular from 30 to 60% by volume.
• fibers basically all known and customary fibers from the field of fiber composite technology come into consideration (eg carbon fibers, synthetic synthetic fibers, natural fibers, etc.).
• fibers eg carbon fibers, synthetic synthetic fibers, natural fibers, etc.
• z As glass fibers embedded in the matrix.
• the matrix of the fiber composite material can, for. B. of epoxy resin, polyimide, cyanate ester or phenolic resin.
• a thermosetting matrix such as epoxy resin with embedded glass fibers is particularly interesting.
• nanoparticles is intended in particular to designate particles having a typical extent in the range from 10 to 100 nm. It has been found that such, z.
• synthetically produced particles in the matrix can improve the adhesion of the fibers and improve the erosion resistance of the turbine blade on the surface of the turbine blade.
• nanoparticles are arranged substantially homogeneously distributed in the volume of the matrix.
• the nanoparticles can be added to the not yet solidified matrix material and mixed with it.
• the fibers to be embedded may also be added, as long as they are not arranged separately on a core material of the turbine blade, for example as a semifinished fiber product (eg woven fabric, scrim, nonwoven, etc.).
• the proportion of nanoparticles in the matrix is less than 30% by weight, in particular in the range from 5 to 20% by weight.
• nanoparticles are deposited on a matrix surface, which represents a surface of the finished turbine blade, in which case it is further preferred that these nanoparticles are arranged distributed substantially homogeneously on this surface.
• the proportion of nanoparticles on a surface of the matrix is greater than 70% by weight, in particular in the range of 90 to 100% by weight.
• concentration of the nanoparticles on the surface is preferably relatively large and preferably relatively small in the volume of the matrix, it is provided according to a more specific embodiment that a gradient of the Na at least in an outermost layer region of a matrix material forming a blade surface region. nop firmwarekonzentration is provided (with decreasing to the blade interior particle concentration).
• the material of the nanoparticles is selected from the group consisting of
• Alumina, silicon carbide, silica, zirconia and titania (including combinations thereof).
• nanoparticles of such a material having a substantially spherical shape and / or a typical extension in the range of 10 to 50 nm may be used.
• the structure of the formed by the fiber composite material surface portions of the turbine blade can be varied locally and thus z.
• B. the expected erosion load and mechanical stress can be adjusted.
• Such a variation may be z.
• the proportion, the type, the length and the arrangement (orientation or orientation distribution) of the refer, but also z.
• the proportion of nanoparticles in the matrix are examples of the proportion of nanoparticles in the matrix.
• the inventive design can be advantageously combined with other known erosion control measures, such.
• Fig. 1 is a schematic representation of a conventional
• FIG. 2 is a side view of a turbine blade according to a first embodiment
• FIG. 3 is a side view of a turbine blade according to a second embodiment
• FIG. 4 is a side view of a turbine blade according to a third embodiment.
• Fig. 5 shows a detail of Fig. 4 in a modified embodiment.
• a steam turbine 1 illustrates a steam turbine 1, comprising a high-pressure-side steam supply line 2 for supplying live steam (for example via a controllable valve) and a low-pressure vapor discharge line 3, which, for. B. leads to a (not shown) capacitor of a steam cycle, from which after heating the condensate live steam is generated again ("condensing steam turbine").
• the live steam z. B. with a pressure of about 10 2 bar and a temperature of about 500 0 C via the supply line 2 at the entrance of Tur- bine 1 supplied.
• the steam expands so that both its pressure and its temperature are reduced.
• the steam passes through the drain 3 z. B. with about ICT 1 bar and about 40 0 C again (eg., 0.05 bar and 33 ° C).
• the thermal energy of the supplied steam is first converted into mechanical turning work.
• a turbine runner 4 extending through the turbine 1 in an axial direction is driven by blades 5 attached thereto and in turn drives an electric generator 7 via an optional gear 6.
• the turbine 1 could alternatively or additionally z.
• the blades 5 alternate with guide vanes 8, which ensure favorable flow guidance of the steam through the turbine 1.
• the vanes 8 are attached to the inside of a turbine housing and project radially inwardly from.
• the turbine 1 in the illustrated example comprises a total of 6 blade ring pairs 8, 5.
• Energy conversion is the lowest possible final pressure of the low-pressure side (after the last blade ring 8, 5) on the discharge 3 exiting steam advantage.
• the blades 5 of the turbine 1 which are arranged farther to the right in FIG. 1 belong to a second expansion section or a low-pressure step group 1-2, whereas the blades located on the left in FIG. 1 belong to a first expansion section or a high-pressure step group 1 -1.
• Turbine blades of the type described below can be used in particular in an installation environment of the type shown in FIG. 1, for example as rotor blades 5 in the low pressure region 1-2 or in the final stage of the steam turbine 1.
• Fig. 2 shows a turbine blade 10 having a blade root 12 for attachment to a turbine runner and a blade body 14 for converting the thermal energy of the steam into mechanical turning work on the turbine runner.
• a special feature of the blade 10 is that its substantially entire surface is formed by a fiber composite material 16 having a matrix and fibers embedded therein and the matrix contains nanoparticles arranged distributed therein at least in a volume region close to the shovel surface. Alternatively or additionally, the nanoparticles may be attached directly to the blade surface (on the outer matrix surface).
• the fiber composite material 16 is z.
• a fiberglass-epoxy resin composite wherein the fiber content in the mate- rial 16 is about 50 vol .-% and wherein the nanoparticles z. B. are substantially spherical particles of silicon carbide with a typical (eg., Average) diameter of about 10 to 30 nm whose proportion in the volume of the matrix is about 10 to 20 wt .-% and increases towards the blade surface (on z B. over 70 wt .-%).
• a "further fiber composite material” which differs from the material 16
• a metallic material such as, for example, aluminum
• the blade root 12 with an integrally associated blade core 18, which may be hollow or solid, is formed.
• the entire surface of the fiber composite blade core 18 was provided with a layer of the fiber composite material 16, that is coated with this material.
• a not yet solidified matrix material eg epoxy resin
• glass fibers or glass fiber sections the nanoparticles and a hardener (to form a reaction resin system) and apply them to the blade core 18.
• a hardener to form a reaction resin system
• To realize the mentioned increase in the nanoparticle concentration towards the blade surface can z. B. be provided in addition to metering nanoparticles in an increasing amount in a resin flow used for infiltration and / or after completing the infiltration such additional nanoparticles directly on the matrix surface and / or in the superficial matrix volume reaching into reaching. The latter succeeds relatively easily and with good results if the attachment to the not yet cured (or at least not fully cured) matrix takes place.
• Another possibility is to first drape the glass fibers in the form of a semifinished product (eg fiberglass fabric, etc.) onto the surface of the blade core 18 and to apply the resin system together with nanoparticles in a further step (infiltration).
• a semifinished product eg fiberglass fabric, etc.
• a heatable molding tool can be used for infiltration and subsequent hardening (eg thermal) of the matrix material.
• nanoparticles can also already be deposited on the relevant fiber material before it is infiltrated with the liquid or viscous matrix material. This alternative or in addition to an integration of nanoparticles during and / or after infiltration.
• the superficial layer of the fiber composite material 16 leads, in particular with substantially homogeneous distribution of the nanoparticles in the matrix and / or on the matrix surface, to a considerable improvement in the mechanical properties and / or on the erosion resistance and thus in a reduction of the problem of drop impact erosion in the case the use in the low pressure region of a condensing steam turbine.
• Fig. 3 shows a blade 10a according to another embodiment.
• a fiber composite material 16a of the type already described.
• the fiber composite material 16a effectively forms a radially outer cap of the blade 10.
• a mass reduction effects a particularly efficient reduction of the centrifugal force load during turbine operation (relatively large distance from the axis of rotation).
• this area is subject during operation of a relatively large drop impact load (relatively large peripheral speed).
• FIG 4 shows a turbine blade 10b, for example of the type already described above, and illustrates in the right-hand part of the FIGURE in an enlarged schematic representation a preferred arrangement of the fibers in a relevant surface section 16b within the scope of the invention.
• the fiber orientation within the surface plane is "completely disordered” or stochastic.
• Fig. 5 illustrates in a representation corresponding to the right part of Fig. 4 also a disordered fiber orientation, but having a preferred direction (in the figure vertically).
• a preferred use of the turbine blades described above and / or the turbine blades produced as described above results in the provision of rotor blades in a low-pressure region, in particular the end stage, of a steam turbine.

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• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Materials Engineering (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Composite Materials (AREA)
• Turbine Rotor Nozzle Sealing (AREA)

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• 2009
  • 2009-01-28 DE DE102009006418A patent/DE102009006418A1/de not_active Withdrawn
• 2010
  • 2010-01-20 EP EP10702847A patent/EP2382375A2/de not_active Withdrawn
  • 2010-01-20 CN CN2010800037650A patent/CN102264999A/zh active Pending
  • 2010-01-20 WO PCT/EP2010/050626 patent/WO2010086268A2/de not_active Ceased
  • 2010-01-20 JP JP2011546780A patent/JP2012516405A/ja active Pending
  • 2010-01-20 BR BRPI1007406A patent/BRPI1007406A2/pt not_active IP Right Cessation
  • 2010-01-20 US US13/146,495 patent/US20110299994A1/en not_active Abandoned

Non-Patent Citations (1)

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