EP3583299A1 - Procédé pour produire une combinaison de structures d'amortissement de vibrations conçue pour amortir des vibrations de masses mobiles - Google Patents

Procédé pour produire une combinaison de structures d'amortissement de vibrations conçue pour amortir des vibrations de masses mobiles

Info

Publication number
EP3583299A1
EP3583299A1 EP18727223.2A EP18727223A EP3583299A1 EP 3583299 A1 EP3583299 A1 EP 3583299A1 EP 18727223 A EP18727223 A EP 18727223A EP 3583299 A1 EP3583299 A1 EP 3583299A1
Authority
EP
European Patent Office
Prior art keywords
coating
combination
cavity
further structure
movable
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.)
Pending
Application number
EP18727223.2A
Other languages
German (de)
English (en)
Inventor
Robin Blank
Lena FARAHBOD-STERNAHL
Christoph Kiener
Sascha Martin Kyeck
Yves K STERS
Simon Purschke
Helge Reymann
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 Energy Global GmbH and Co KG
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
Publication of EP3583299A1 publication Critical patent/EP3583299A1/fr
Pending legal-status Critical Current

Links

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
    • F01D5/16—Form or construction for counteracting blade vibration
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D19/00—Casting in, on, or around objects which form part of the product
    • 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
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B33—ADDITIVE MANUFACTURING TECHNOLOGY
    • B33Y—ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING
    • B33Y80/00—Products made by additive manufacturing
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/04—Making non-ferrous alloys by powder metallurgy
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing blade vibration
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F7/00—Vibration-dampers; Shock-absorbers
    • F16F7/10—Vibration-dampers; Shock-absorbers using inertia effect
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
    • F16F7/00—Vibration-dampers; Shock-absorbers
    • F16F7/10—Vibration-dampers; Shock-absorbers using inertia effect
    • F16F7/104—Vibration-dampers; Shock-absorbers using inertia effect the inertia member being resiliently mounted
    • 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
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B22F2998/10—Processes characterised by the sequence of their steps
    • 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
    • B22F2999/00—Aspects linked to processes or compositions used in powder metallurgy
    • 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
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/10—Sintering only
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • 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
    • F05D2240/24—Rotors for turbines
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/282—Three-dimensional patterned cubic pattern
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/283—Three-dimensional patterned honeycomb
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • 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
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P10/00—Technologies related to metal processing
    • Y02P10/25—Process efficiency

Definitions

  • the invention relates to a method for producing a vibration-damping structure combination, an intermediate product of the method for producing the vibration-damping structure combination and the structural combination for damping vibrations of movable masses.
  • a rotating turbomachine such as a turbine for a power plant, for example, has a rotor with a plurality of rotor blades and a stator with a plurality of stator blades.
  • the rotor moves during operation of the turbine to a Ro ⁇ tationsachse with a certain rotational speed, thereby also arranged on the rotor blades move around the rotation axis of the rotor at the determined rotation speed.
  • the rotational speed of the rotor may change during operation, whereby a positive or negative rotational acceleration of the rotor and blades may occur due to the change of the Rotationsgeschwindig ⁇ ness.
  • the positive or negative rotational accelerations of the blades can cause vibrations of the blades
  • the object of the invention is therefore to provide a method for producing a vibration-damping structure combination for damping oscillations of movable masses, an intermediate of the method for producing a vibration-damping structure combination and a structural combination for damping the vibrations of movable masses.
  • the inventive method for manufacturing a vibration-damping structure combination for damping vibrations of movable masses with a first structure and another structure, wherein the further structure within a defined by a first structure surface of the first structure stop surface is movable, has the following Schrit ⁇ te: a) providing the first structure having the first structure surface, which at least in sections defines a coating surface of a coating; b) coating the first structure surface of the first
  • the abutment surface may be a boundary surface within which the further structure may move relative to the first structure.
  • a movement responsible for the oscillation may also be, for example, a linear movement, a tilting movement, a movement along a curve, an accelerated movement or any other form of movement.
  • the coating of the ers ⁇ th surface structure described in process step b) can be by way of example, carried out by means of a Gal ⁇ vanmaschine or chemical vapor deposition such as CVD. Other coating methods may also be used.
  • the first structure surface area is coated such that the filler can produce no unwanted contact with the first structure during the filling of the hollow space ⁇ with the filler.
  • the first structure may be in contact with the hardened filler, the further structure, in order to allow advantageous transport, advantageous handling or advantageous assembly of the structural combination.
  • the connection between the first structure and the further structure can be exemplified by means of a single application of force or by means of a one-time application
  • the described in process step c) filler may be at ⁇ play, a molten metal or slurry.
  • the fillers used should be selected based on the desired requirements and / or on the material used in the first structure.
  • the curing of the filler can be carried out, for example, without an active action in the curing process over a longer period of time, or be carried out by the active action in the curing process via an active cooling and / or an active heating of the structure combination.
  • the removal of the coating can be carried out, for example, by means of an etching process or by means of another chemical or physical process.
  • Possibility to remove the coating is that the structure combination with the coating on a
  • Melting point or a vaporization point of the coating is heated, whereby the coating loses its solid form and can be removed.
  • the removal can also take place during operation of the structural combination, as a result of which the further structure is better protected during transport, handling and assembly.
  • removal of the coating during operation must take place in such a way that the further structure to the first structure is movable within the stop surface defined by the first structure surface.
  • the intermediate product according to the invention for producing a vibration-damping structure combination has a first structure which has a first structure surface which abuts at least in sections on a coating surface of a coating and a further structure having a further structure surface which consists of a cured with a Filler filled cavity is formed, wherein the further structure surface is at least partially applied to the coating surface of the Beschich ⁇ tion, wherein the coating is removable to the to make further structure movable within a stop surface defined by the first structure surface.
  • the intermediate is a product of the process that was performed up to step d) curing of the filler.
  • the intermediate product has the coating, where ⁇ abuts at least in sections on the coating surface of the coating by the further structure.
  • the intermediate product is advantageously transportable, manageable and mountable.
  • the coating removed, the other structure is inner ⁇ half of the abutment surface defined by the first structure surface movable, which by means of a Ausretesbewe ⁇ account the other structure and / or by means of a beating-up of the further structure to the abutment surface of the first structure Vibrations of the first structure become dampened.
  • the removal of the coating can take place, for example, after transport, handling or after assembly.
  • the coating can be removed by means of an etching or by means of a temperature application.
  • the temperature treatment may be by way of example be designed such that the melting point of the coating material and / or the vaporization point of the coating material is exceeded, whereby the liquid or gaseous Be ⁇ coating is exemplary discharged via a small opening.
  • the temperature application can also take place in a first operating phase during operation of the moving masses, as a result of which the further structure to the first structure can only be moved during operation.
  • the assembly can be carried out particularly advantageous.
  • the liquid or gaseous coating may remain in the cavity throughout the life of the structural combination and operate as a damping means between the further structure and the first structure act. If the operating temperature of the moving masses by way of example above the melting point of the coating or above the vaporization point of the coating, it is conceivable that the coating is in solid form outside of the operation to exemplary perform maintenance processes advantageous ⁇ way, and that the coating during the Operating in liquid or gaseous form to function in operation as a damping means between the first structure and the other structure.
  • another damping means such as, for example, an oil or an inorganic liquid, may be interposed between the first structure and the further structure in order to move the further structure relative to the first structure until the other structure strikes to dampen the first structure surface.
  • the structural combination according to the invention for damping vibrations of movable masses has a first movable
  • Structure which has a certain first inertia and having a ers ⁇ te structure surface, which is designed as a stop surface and a mitbewegbare other structure on which is molded from a filled with a cured filling agent cavity, wherein the further structure comprises a BE ⁇ has more inertia and has a further structure surface and the other structure to the first structure within the defined by the first surface structure ⁇ defined abutment surface is movable, whereby vibrations that can be triggered via positive and / or negative accelerations of the movable masses are, by means of a further inertia of the further structure conditional compensating movement and / or by means of a striking of the further structure surface of the further structure to the abutment surface of the first structure can be damped.
  • the compensating movement is one of the positive or negative acceleration opposing movement of the further structure from a rest position to a deflected position. Due to gravity or due to the centrifugal force during a rotational movement, the compensating movement is usually possible only by overcoming a static friction.
  • the static friction is the force that prevents a sliding of touching bodies and depends on material properties and properties
  • Structure and the other structure can be influenced in such a way that a defined starting of the desired compensation movement is made possible.
  • the compensation movement can be influenced on the basis of the friction of the first structure moving away from one another and another structure.
  • Another way the compensation movement to beeinflus ⁇ sen is to make the shape of the abutment surface of the first structure such that a restoring force which is responsible for returning the other structure in the rest position, increases with the deflection of the further structure from the rest position , The greater the deflection from the rest position, the greater the restoring force acting on the further structure.
  • This may be possible, for example, by means of a parabolic stop surface on which the further structure moves.
  • the shape of the abutment surface thereby influences the compensatory movement.
  • a wave ⁇ shaped or jagged stop surface is also conceivable.
  • the compensation movement can also be influenced by means of insertion of spring elements and / or damping elements, whereby a spring-damper system is formed.
  • the spring elements and / or the damping elements are by way of example be fastened to the first structure and the further structure, whereby the deflection of the further structure from the rest position and the return to the rest position are impressive flow ⁇ bar.
  • the behavior of the spring-damper system can be controlled.
  • the right spring element with the appropriate spring constant and / or the right Dämpfele- can be ment selected with the appropriate damping constant depending on the Anforde ⁇ implications of structural combination.
  • the striking of the further structure against the stop surface can also dampen the vibrations.
  • the compensatory movement is stopped.
  • a force due to the inertia of the moving masses can further damp the vibration of the first structure.
  • the position of the abutment surface, which stops the equalizing movement of the further structure, defines when the compensating movement is stopped, and thereby the occurring due to the inertia of the moving masses
  • the position of the stop surface defines when the oscillation of the first structure can be damped by means of abutment with the stop surface.
  • a shock which occurs due to the abutment of the further structure on the abutment surface may be elastic or plastic.
  • This can be influenced by means of the material properties of the first structure and of the further structure.
  • an elastic behavior of the joint, in which no kinetic energy is transformed into internal energy such ⁇ way of heat or deformation desired the material properties of the first structure and should further structure can be chosen accordingly. If a plastic impact is desired, the material properties should also be selected accordingly.
  • a lattice network structure is provided as the first structure.
  • the grid structure can be constructed, for example, from a plurality of juxtaposed unit cells.
  • the unit cell is a specific geometric shape such as for example, a cube or a cuboid, having a certain number of unit cells at ⁇ interfaces depending on the shape.
  • the unit cell has in its interior a physical area and a disembodied area.
  • the physical area is filled with filling material and the disembodied area is free of filling material.
  • the physical area and the disembodied area are such arranged in the unit cell, that when flat against one another arranged unit cells connected a physical structure and a connected disembodied structural ⁇ tur arise.
  • Typical forms of the physical structure of one of the unit cells are, for example, star geometries or cross geometries.
  • the grid structure can be produced by way of example by means of additive manufacturing.
  • a preferred method may be a selective laser fusion.
  • the additive manufacturing processes make it possible to produce lattice structures of different materials such as aluminum alloy AlSilOMg, a superalloy for high temperature applications MP1 - CoCrMo, a high performance steel MaragingSteel MSI, stainless steels or plastics.
  • the first structure may also consist of a body whose outer shell is made of solid material and whose inner structure is constructed of a lattice network structure.
  • the first structure can also have a plurality of grid network structures which are separate from one another and / or have several different grid structures that are interconnected.
  • the structural combination can also be constructed in such a way that more than one cavity with the liquid filler is to be filled after the coating.
  • more than one cavity is to be filled with the liquid filler, a number of further structures are formed, which can be moved relative to the first structure after the removal of the coating.
  • the coating of the grid structure of the first structure must be such that even after the coating, the disembodied areas of the unit cells are still connected to each other, whereby the coherent cavity is ⁇ forms, which can be filled with the filler. Since ⁇ by that the continuous cavity can be disposed within the Git ⁇ ternetzteil is further
  • Structure which forms from the cured filler, arranged captive to the first structure. After the coating has been removed, relative movement of the further structure to the first structure and / or attachment of the further structure to the first structure is made possible.
  • the further structure can be separated from the first structure without change in shape and / or without structural change.
  • the shape of the first structure must be chosen such that by means of the coating surface and any additional moldings fillable with the filler cavity and simultaneously after Aushär ⁇ tion of the filler and after removal of the additional moldings and the coating a relative movement the further structure to the first structure and an abutment of the further structure at the abutment surface of the first structure is made possible and the abutment surface of the first structure ⁇ tur the movement of the further structure is not limited in all directions and / or all direction combinations, but a free movement in at least one of the directions
  • At least one region of the first structure is preferably formed surrounded by the further structure and / or at least one region of the further structure is formed by the first structure
  • the two structures are inseparably connected to one another and can be located within one another Structure surface be ⁇ bound stop surface in all directions and / or move in all direction combinations. However, a free movement, a release of the first structure of the further structure prevented.
  • the another structure that forms within the first structure also have a more Gitternetzstruk- ture is. It forms a combination of structures consisting of two intertwined grid structures.
  • the grid structures are captive to each other arranged, but can move relative to each other within the stop surface.
  • the cavity is preferably formed in sections with the coating tung-surface and / or in sections, with a Oberflä ⁇ che an additional molded part. Characterized in that the cavity is formed with the coating surface and / or with the surface of an additional molding, egg ⁇ ne even freer design of the cavity is made possible.
  • the moldings make it possible to form a cavity which would not be moldable by means of the coating surface alone.
  • FIG. 1 shows a schematic representation of a turbine blade.
  • Figure 2 shows a schematic representation of a cross section through the turbine blade shown in Figure 1, which has an embodiment of a structural combination according to the invention.
  • Figure 3 shows a schematic representation of an output ⁇ point of an embodiment of a method for Her ⁇ provide the structure combination.
  • FIG. 4 shows a schematic representation of a further method step for producing the structure combination.
  • FIG. 5 again shows the method step illustrated in FIG.
  • FIG. 6 shows a schematic representation of a further method step for producing the structure combination.
  • FIG. 7 again shows the method step illustrated in FIG.
  • FIG. 8 shows a schematic representation of a further method step for producing the structure combination.
  • FIG. 9 again shows the method step illustrated in FIG. 8, but in a different sectional plane.
  • Figures 1 and 2 show a turbine blade 11 of a ro ⁇ animal forming turbomachine.
  • the rotating turbomachine may be a turbine or even a compressor, each having a rotor with a plurality of blades and a stator with a plurality of vanes.
  • the turbine blade 11 shown in Figures 1 and 2 is formed ⁇ in the present embodiment as a blade. Notwithstanding the present embodiment, the turbine blade 11 may also be formed as a guide vane.
  • the turbine blade 11 has in the present perennialsbei ⁇ play on an airfoil 12, a platform 13 and a fastening portion Be ⁇ fourteenth
  • the turbine window 11 can be connected to the rotor.
  • Adjoining the attachment portion 14 is the platform 13 which separates the attachment portion 14 from the airfoil 12.
  • the airfoil 12 has a blade leading edge 15, a blade trailing edge 16 and Blade cavities 17 on.
  • the airfoil 12 extends from the platform 13 to a radially further outward or further inward end.
  • the airfoil 12 of the flow of the turbine is exposed to and moves by way of example to a turbine axis of rotation of the turbine, while a fluid from the blade leading edge 15 along the blade 12 flows to the blade trailing edge 16.
  • Un ⁇ ter Kunststoffliche flow rates can be exemplified vibrations of the blade 12 cause.
  • the vibration constricting portions 10 of the airfoil 12 illustrate the movable front ⁇ lying embodiment masses 10. These vibrations can cause cracking or exacerbate an existing cracking process.
  • the cracks can damage the airfoil 12, the turbine blade 11 and the entire turbine.
  • the blade 12 is set in Be ⁇ operation of a high temperature load due to a high temperature of the air flow around the blade 12 ⁇ .
  • the blade 12 has, for example, blade cavities 17, through which a cooling fluid can flow to cool the blade 12.
  • FIG. 2 shows by way of example three blade cavities 17 through which the cooling fluid can flow.
  • the blade cavities 17 serve, inter alia, to cool the blade 12.
  • vibrations of the turbine blade 11 may cause cracking or enhance an existing crack formation process.
  • a structural combination 18 for damping vibrations is provided in the blade cavity 17 in the present exemplary embodiment.
  • the structural combination 18 has in the present embodiment, a first structure 2 and a further structure 3, wherein the further structure 3 relative to the first Structure 2 is movable within the stop surface defined by the first structure surface 5 of the first structure 2.
  • the abutment surface can be a boundary surface within which the further structure 3 can move to the first structure 2.
  • there does not necessarily have to be a "stop" or a mechanical contact According to one embodiment, a direct stop or mechanical contact between the first structure 2 and the further structure 3 does not occur.
  • the further structure 3 is interlaced with the first structure 2 in the present exemplary embodiment.
  • the first structure 2 and the further structure 3 are captively connected to each other in the present embodiment.
  • the further structure 3 of the first structure 2 solvable, i. is designed to be lost.
  • the occurring during operation of the turbine blade 11 oscillations ⁇ conditions are attenuated by the compensating movement and / or by the striking of the other structure 3 to the stop surface of the first structure. 2
  • the temperature load occurring during operation can continue to be effected by means of the flow of the cooling fluid through the blade cavities 17.
  • the first structure 2 an example of a grid structure and across the entire blade height associated with the airfoil 12, one patch from the airfoil surface ⁇ made heat energy is conducted to the grid structure and there received by the passing cooling fluid.
  • the grid structure increases the surface area at which the heat transfer can take place, as a result of which a larger amount of heat can be removed, as a result of which the temperature of the
  • Airfoil 12 can be lowered. In addition, will simultaneously attenuated by the further structure, the vibrations of the turbine blade 11 occurring.
  • the entire turbine blade 11 can be produced by means of additive manufacturing methods, wherein the blade cavities 17 and / or additional co-manufactured
  • Structures serve as the first structure 2 in the context of the present invention.
  • the vane cavities 17 are filled with a lattice ⁇ network structure which is then coated with the vane cavity 17, thereby defining the cavity.
  • the filler 9 can be filled in the hollow space 8 ⁇ .
  • the cured filler 9 forms the further structure 3 interwoven with the first structure 2.
  • the removal of the coating 4 can then take place, for example, by means of an etching process, whereby the further structure 3 is movable relative to the first structure 2 and vibrations can thereby be damped.
  • Figures 3 to 9 show process steps for manufacturing the vibration damping structure combination 18 for damping vibrations of movable masses 10, which are, in the present exemplary embodiment, portions of the turbine blade.
  • the finished structure combination 18 has a bottom plate 1, the first structure 2 with the first structure surface 5 and the further structure 3 with the further structure surface 7.
  • a coating 4 with a coating surface 6 temporarily rests against the first structure surface 5 in the course of the process.
  • the coating surface 6 defines a cavity 8 which is filled with a liquid filler. tel 9 is fillable, whereby the further structure 3 can be formed.
  • FIG. 3 shows the starting point of the method.
  • the illustrated first structure 2 has been produced on the base plate 1 by way of example by means of additive manufacturing methods.
  • the bottom plate 1 and the first structure 3 are connected to each other and the bottom plate 1 limits the Strukturkombina ⁇ tion 18 in one direction.
  • the first structure 2 has, for example, a grid structure.
  • the exemplary Git ⁇ ternetzteil is to be produced by the additive manufacturing relatively easy and comparatively cost effective.
  • a coating 4 is applied to the first structure surface 5.
  • the coating can be carried out by way of example by means of a chemical vapor deposition, such as CVD, or a galvanization.
  • the coating was performed such that the entire first structure surface is wetted 5 of the first structure 2 with loading ⁇ coating. 4 Unwanted uncoated sections of the first structure surface can lead to problems in the further course of the process.
  • FIG. 4 shows the first structure 2 after the coating process with which the coating 4 was applied to the first structure surface 5.
  • the coating 4 is applied to the first structure surface 5.
  • Figure 5 again shows the 4 with the coating ⁇ be coated first structure 2, wherein the coating surface 6 of the coating 4 defining the cavity. 8
  • the first structure 2 shows the first structure 2 with the coating 4 and the filled with the filler 9 cavity 8.
  • the filler 9 fills the cavity 8 is completely formed and there ⁇ by the further structure 3.
  • Curing of the filler 9 can be exemplified by cooling the filler 9 when the filler 9 is a metal by way of example, or by burning the filler 9 when the filler 9 is, for example, a slurry.
  • the respective materials used for the first structure 3 and the other structure 3 should be used. If it is desired by way of example that the further structure 3 is not electrically conductive, the further structure 3 should consist, for example, of a ceramic.
  • an intermediate product 19 for the production of the vibration damping structure combination is 18.
  • the other structure surface 7 is situated at least partially on the coating surface 6 of the coating 4, where ⁇ removable at the coating 4, to make the additional structure 3 within a defined by the first structure surface 5 stop surface movable.
  • Figure 7 again shows the first structure 2, the loading ⁇ coating 4 and the cured filler 9 that forms the white ⁇ tere structure. 3
  • the coating 4 prevents relative movement of the white ⁇ direct structure 3 relative to the first structure 2 and an abutment of the other structure 3 at the first surface structure 5.
  • the damping of vibrations of the moving masses 10 is made possible, however, this can be an example for the Trans ⁇ port or assembly of the structural combination hindering why the coating 4 after transport or the Assembly is removed in a further step.
  • the Be ⁇ coating 4 can be exemplified removed by an etching process, egg ⁇ ner temperature treatment or other chemical or physical process.
  • FIG. 8 shows the structure combination 18 freed from the coating 4. As a result of the coating 4 having been removed, the further structure 3 is relative to the first one
  • the An ⁇ impact surface 20 is formed in the present embodiment, the ⁇ art that it limits a movement of the other structure 3 in the direction of all spatial axes x, y, z and direction combinations of all spatial axes.
  • the stop surface 20 in the present embodiment is formed on all sides be ⁇ border.
  • the stop surface 20 is formed spherical surface-shaped We ⁇ sentlichen.
  • the dimensions of the further structure 3 may be greater than the dimensions of the recesses in the respective extension direction.
  • FIG. 9 again shows the structure combination 18 with the first structure 2 and the further structure 3, wherein the first structure 2 is connected to the bottom plate 1 and the further structure 3 is interwoven with the first structure 2, but within that of the first structure Surface 5 defi ⁇ defined stop surface is movable. Furthermore, it can be seen in particular with reference to FIG. 9 that the structural combination 18 has a structure structure based on a unit cell 21. In other words, the structure combination 18 has a periodically repeating structure in its extension directions.
  • an increase in surface area in the area of the abutment surface 20 can be achieved, so that a particularly large contact area for force transmission is provided when the further structure 3 comes into contact with the first structure 2 during operation.
  • the bottom plate 1 and the first structure 2 are of the same material in the present embodiment.
  • the bottom plate 1 and the first structure 2 are made of the same material or of materials having almost the same material properties. This ensures that, due to heating, no or only slight, thermally induced stresses form in the connection region between the bottom plate 1 and the first structure 2, since the respective thermal expansion coefficients are equal or nearly equal.
  • the material of the coating 4 has a melting point and / or evaporation point and / or sublimation point which is below the respective melting point and / or evaporation point and / or sublimation point and / or an ashing temperature of the material of the base plate 1, the first structure 2 and the further structure 3 and the filler 9 is located.
  • first structure 2 is movable within the abutment surface defined by the first structure surface 5
  • vibrations which are triggered, for example, via positive or negative accelerations of the moved first structure 2 can be achieved by means of a compensating movement and / or by abutment of the other Structure surface 7 the further structure 3 are damped against the abutment surface of the first structure. This prolongs the life of the turbine blade 11.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Manufacturing & Machinery (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Vibration Prevention Devices (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un procédé pour produire une combinaison de structures (18) d'amortissement de vibrations conçue pour amortir des vibrations pour des masses mobiles (10), comprenant une première structure (2) et une structure supplémentaire (3), cette structure supplémentaire (3) étant mobile sur une surface de butée (20) définie par une première surface de structure (5) de la première structure (2). Le procédé selon l'invention comprend les étapes qui consistent : a) à fournir la première structure (2) comportant la première surface de structure (5) et prédéfinissant, au moins sur certaines parties, une surface de revêtement (6) d'un revêtement (4) ; b) à revêtir la première surface de structure (5) de la première structure (2) au moyen du revêtement (4), la surface de revêtement (6) du revêtement (4) étant appliquée de manière à former au moins une cavité (8) ; c) à remplir cette cavité (8) au moyen d'une matière de remplissage (9) ; d) à faire durcir cette matière de remplissage (9) jusqu'à ce que la structure supplémentaire (3) soit formée avec une surface de structure supplémentaire (7) adjacente à la surface de revêtement (6) ; e) à supprimer le revêtement (4), la structure supplémentaire (3) étant mobile vers la première structure (2) sur la surface de butée définie par la première surface de structure (5).
EP18727223.2A 2017-05-22 2018-05-18 Procédé pour produire une combinaison de structures d'amortissement de vibrations conçue pour amortir des vibrations de masses mobiles Pending EP3583299A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102017208631.9A DE102017208631A1 (de) 2017-05-22 2017-05-22 Verfahren zum Herstellen einer schwingungsdämpfenden Strukturkombination zur Dämpfung von Schwingungen bewegbarer Massen
PCT/EP2018/063041 WO2018215323A1 (fr) 2017-05-22 2018-05-18 Procédé pour produire une combinaison de structures d'amortissement de vibrations conçue pour amortir des vibrations de masses mobiles

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EP3583299A1 true EP3583299A1 (fr) 2019-12-25

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US (1) US11761338B2 (fr)
EP (1) EP3583299A1 (fr)
JP (1) JP7184809B2 (fr)
DE (1) DE102017208631A1 (fr)
WO (1) WO2018215323A1 (fr)

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Publication number Publication date
JP7184809B2 (ja) 2022-12-06
JP2020521906A (ja) 2020-07-27
DE102017208631A1 (de) 2018-11-22
WO2018215323A1 (fr) 2018-11-29
US20200080611A1 (en) 2020-03-12
US11761338B2 (en) 2023-09-19

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