WO2018141574A1 - Composant de turbine cmc dotée de structures de refroidissement complexes ainsi que procédé de fabrication - Google Patents

Composant de turbine cmc dotée de structures de refroidissement complexes ainsi que procédé de fabrication Download PDF

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Publication number
WO2018141574A1
WO2018141574A1 PCT/EP2018/051518 EP2018051518W WO2018141574A1 WO 2018141574 A1 WO2018141574 A1 WO 2018141574A1 EP 2018051518 W EP2018051518 W EP 2018051518W WO 2018141574 A1 WO2018141574 A1 WO 2018141574A1
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WO
WIPO (PCT)
Prior art keywords
cmc
turbine component
fiber
cooling
prepreg
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.)
Ceased
Application number
PCT/EP2018/051518
Other languages
German (de)
English (en)
Inventor
Christian Xavier Campbell
Stefan Lampenscherf
Gia Khanh Pham
Steffen Walter
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Publication of WO2018141574A1 publication Critical patent/WO2018141574A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B18/00—Layered products essentially comprising ceramics, e.g. refractory products
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B38/00—Porous mortars, concrete, artificial stone or ceramic ware; Preparation thereof
    • C04B38/0003—Porous mortars, concrete, artificial stone or ceramic ware; Preparation thereof containing continuous channels, e.g. of the "dead-end" type or obtained by pushing bars in the green ceramic product
    • 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
    • F01D5/187—Convection cooling
    • 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
    • F01D5/284—Selection of ceramic materials
    • 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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
    • C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
    • C04B2235/52—Constituents or additives characterised by their shapes
    • C04B2235/5208—Fibers
    • C04B2235/5212—Organic
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
    • C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
    • C04B2235/52—Constituents or additives characterised by their shapes
    • C04B2235/5208—Fibers
    • C04B2235/5216—Inorganic
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/60—Aspects relating to the preparation, properties or mechanical treatment of green bodies or pre-forms
    • C04B2235/602—Making the green bodies or pre-forms by moulding
    • C04B2235/6022—Injection moulding
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
    • C04B2237/32—Ceramic
    • C04B2237/38—Fiber or whisker reinforced
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
    • C04B2237/50—Processing aspects relating to ceramic laminates or to the joining of ceramic articles with other articles by heating
    • C04B2237/62—Forming laminates or joined articles comprising holes, channels or other types of openings
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/185—Two-dimensional patterned serpentine-like
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/204—Heat transfer, e.g. cooling by the use of microcircuits
    • 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
    • F05D2300/6033—Ceramic matrix composites [CMC]

Definitions

  • the invention relates to non-metallic turbine components, in particular gas turbine components, for example for stati ⁇ onary gas turbines, made of ceramic matrix composite materials (CMCs).
  • gas turbine components for example for stati ⁇ onary gas turbines, made of ceramic matrix composite materials (CMCs).
  • CMCs ceramic matrix composite materials
  • Turbine components particularly turbine blades, made at least in part of CMCs have the advantage over metallic components that they can be used in stationary turbines, such as gas turbines, at significantly higher temperatures. This means that with the increase of the operating temperature an increase in efficiency of the gas turbine is possible and in particular that under certain circumstances efficiencies greater than 63% can be achieved.
  • the CMC material is a ceramic composite consisting of ceramic fibers and / or fiber fabrics, such as mullite and / or alumina fiber, which is embedded in a ceramic matrix of - again, for example - alumina. From WO 2016/159933 such a turbine component is known.
  • thermal limits are also set for this material, which are achieved, inter alia, with the temperature at which the reinforcing fibers start to recrystallise. For a long service life of the gas turbine component under the above-mentioned operating conditions, cooling is therefore essential.
  • Cooling structures and / or cooling channels in metallic gas turbine components ie, for example, in blades and / or blades, produced by casting processes.
  • casting cores are used according to the prior art for internal cooling structures, which image the filigree cooling channels and / or structures during the metal casting and, above all, are inaccessible in the interior of the turbine component.
  • Cooling channels that are accessible from the outside are, in contrast, introduced by erosion and / or laser drilling. Accordingly, it is an object of the present invention to provide a turbine component which is at least partially made of CMC and has suitable cooling structures in the CMC, as well as to provide a method for the production of cooling structures in such turbine components.
  • the subject of the present invention ei ⁇ ne turbine component, which is at least partially made of ceramic matrix composite material by means of a lamination process, wherein placeholder in the CMC prepreg, a CMC prepreg precursor and / or the CMC prepreg layers formed laminate before and / or be introduced during the lamination process, which are removable during sintering of the turbine component by decomposition and / or evaporation and leave defined cavities in the CMC, which are used as cooling structures.
  • the cavities formed by the removal of the placeholder are identifiable depending on placeholder, because they have, unlike subsequently cut, etched or milled channel structures no sharp edges, but smooth surfaces.
  • a cracked and / or separated reinforcing fiber in a cooling channel of the finished CMC component can not be excluded in individual cases.
  • the usable here wildcards are flexible, pliable or rigid, depending on the type cooling channel is desired in the finished construction ⁇ part.
  • the Materi ⁇ alien the sacrificial elements are directed thereafter, of the type of ceramic reinforcing fibers and ceramic matrix in which CMC. It is crucial that the sacrificial material with the ceramic material under pressure and temperature increase, such as the debinding step before the sintering ⁇ step, not react with the ceramic material and that the vaporous decomposition products of the sacrificial material also no reactions and / or damage to the Ceramics cause.
  • the sacrificial micro tubes are, for example KunststoffPro ⁇ -products, for example, based on organic, inorganic and / or organometallic polymers which, in turn, for example, used nal Modellen in the form of tubes and / or injection molded Ka.
  • the sacrificial fibers are fibers, fibrous webs and / or fiber composites in which at least two types of fibers are present, at least one first type of fiber which remains stable under the conditions of sintering the CMC component and at least ei ⁇ ne second type of fiber, among the Conditions of sintering of the CMC component decompose and evaporate.
  • This fiber composites with at least two types of fibers are also called Hyb ⁇ ridfasern, hybrid fiber fabric and / or hybrid fiber composites.
  • a higher density of cooling structures may be provided in some regions than closer to the surface of the laminate.
  • Cooling-air structures in the turbine component which are of very thin-walled design are understood as “complex cooling-channel structures.” Cooling-channel structures, for example, are described in US 2016/0376957 A1.
  • CMC prepreg When lamination for the production of the turbine component from CMCs in a first step CMC prepreg are Herge ⁇ represents, that is fibers, fiber woven fabric and / or fiber composites, which are infiltrated with a ceramic matrix and / or impregnated and, deposited on molds, such as press cores , in particular stored in layers, that is laminated, are.
  • CMC prepreg laminate a stack is referred to meh ⁇ of exemplary CMC prepreg layers of impregnated fabric in the present case, which is sintered for producing a CMC turbine component.
  • the fibers forming the fabric are ent ⁇ speaking of ceramic material that is stable to the Sinte- approximately process conditions. It is particularly advantageous if the fibers have at least portions which are kris ⁇ tallin and their crystallization is maintained during the sintering, which are therefore neither subject to re-crystallization nor a change in the modification by the sintering process.
  • the placeholder preference ⁇ are introduced.
  • the placeholders are also inside the CMC prepreg laminates and / or CMC prepreg sheets and optionally have a connection opening on the surface.
  • placeholders can pierce CMC prepreg layers or portions of layers.
  • the CMC prepreg laminates are also formed around the placeholders.
  • placeholder ⁇ be introduced, which do not pass the upper CMC prepreg plies extend prior to the application of an upper CMC prepreg ply.
  • the placeholders may pierce multiple CMC prepreg layers and / or be disposed along a CMC prepreg layer. After sintering cavities form at ⁇ put the wildcard at least occupy the space of the placeholder, but under certain circumstances, because the removal of the placeholder usually during
  • Debinding step takes place under gas evolution, ⁇ Kings nen cavities may be larger or smaller than the incorporated in the CMC prepreg layer placeholder.
  • the CMC prepreg laminate is compressed in a second process step, preferably by autoclaving, at high pressure and dried.
  • a lamination method is known, for example, from WO
  • a finished CMC component is obtained, wherein fibers, fiber fabric and / or fiber composite, which are stable against ⁇ over the conditions of the sintering process, substantially unchanged, ie not or only slightly recrystallize, for example, during sintering.
  • the cavities form, for example thin-walled and / or com plex ⁇ channel structures. These are, for example, along fibers, fiber fabrics and / or fiber composites and / or perpendicular thereto, so that they pass through at least one plane or layer, but usually several planes or layers vertically.
  • micro-tubes containing the fibers are inserted into a CMC prepreg laminate which is burnt out during drying, debindering and / or during sintering of the CMC.
  • hybrid fibers, woven fabrics and / or composites may also be incorporated into a CMC prepreg laminate to form the micro-hoses and / or the injection-molded channel structures.
  • Hybrid fiber composites are for example 3- ⁇ dimansionale fiber composites, in which two different Fasermate- are at least rials processed, for example, ceramic fibers and carbon fibers.
  • the principle is that a first type of fiber, for example, a ceramic fiber is stable to the conditions of sintering, whereas a second type of fiber during sintering, especially in the
  • Debinding step is removable and leaves cavities, which are used in the finished component as a cooling channel.
  • the two types of fibers are woven together and / or braided together to form hybrid structures with sacrificial fiber cords, sacrificial fiber fabrics, and / or sacrificial fiber composites.
  • any 3-dimensional fiber composites can be used with placeholders to form the CMC prepreg layers.
  • sacrificial fibers may be braided around the stable ceramic fibers, or vice versa, different diameters of sacrificial fibers and stable fibers may be combined, and tissues having sacrificial fibers of various diameters may serve to form desired zones in the turbine component with different thicknesses. to receive canceled cooling channel structures after sintering.
  • correspondingly fine cooling channel structures can be produced.
  • correspondingly thicker sacrificial fibers for example in the range from 7000 to 15,000 denier, correspondingly larger cooling channel structures can be formed.
  • cooling channels that a
  • cooling channels with the stated diameters can be formed in different regions of the CMC component.
  • cooling channels and areas without cooling channels alternate, or areas with three different diameters on cooling channels with areas with only one diameter of cooling channels.
  • filigree cooling channels and structures that are located inside the CMC component can be produced in this way.
  • the cooling channel structures simulate the position of the placeholders before the sintering process.
  • the cooling duct structures ⁇ braided and interwoven hybrid fibers can have very complex structures, for example, wind around the reinforcing fibers of the CMC component.
  • FIGS. 1 a and 1 b show a photograph of a CMC turbine component with a placeholder before the sintering process and with a cooling channel after the sintering process.
  • Figures 2a to 2d show schematically the lamination process with installation of placeholders
  • Figures 3a and 3b show an exemplary hybrid fiber composite a) without laminate in a schematic, perspective DarStellung; b) within a CMC prepreg laminate;
  • FIGS. 4a and 4b show the installation of 2D hybrid weaves for producing small cooling channel cross sections.
  • FIGS. 5a and 5b show the installation of 2D hybrid weaves for producing large cooling channel cross sections.
  • FIG. 6 shows a schematic representation of an exemplary 3D hybrid fiber composite for introduction into a CMC prepreg laminate.
  • FIG. 1 a shows a photograph of a CMC prepreg laminate before the sintering process. To recognize the is
  • FIGS. 2a to 2d show the incorporation of polymeric channel structures into the CMC prepreg laminate, which can be produced by means of injection molding.
  • Figure 2a shows the first method ⁇ step in which the base structure 6 - a so-called "core structure" -. Launched the CMC prepreg layers 7 are thus laminated on the interface 8 between the single ⁇ NEN CMC prepreg layers can also be seen.
  • a placeholder 9 nal Korean in the form of an injection molded Ka pressed into the already formed CMC prepreg laminate a ⁇ and in the basic structure 6 into the corresponding Wells 10 anchored.
  • Figure 2c shows - always in cross-section - further CMC prepreg layers of the CMC prepreg laminate 7, ie conventional layers of CMC prepreg, as described for example in WO 2016/159933 AI ⁇ written outside the Platzhalter 9, so that the place ⁇ holder 9 is inside the formed CMC prepreg laminate 7, is located.
  • the basic structure can be removed structural ⁇ 6 for the debinding and sintering process. This results in a CMC prepreg laminate 7 with a placeholder 9, as shown in Figure 2d.
  • the cooling channel structure shown here has openings 11 where the CMC prepreg laminate 7 rests on the base structure 6 and laterally.
  • Figures 3a and 3b show the formation and incorporation of hybrid fiber, cords and / or tapes.
  • FIG. 3b shows how the hybrid fiber cord is introduced 14 into the CMC prepreg laminate 7, for example, in addition to the square ⁇ holder 9 of Figure 1 and / or 2 is shown.
  • the cross-sectional view shown in Figure 3b goes through the CMC prepreg laminate 7 and by the inserted hybrid fiber cord 14.
  • Figures 4a and 4b show by way of example a 2D hybrid fabric 15 of ceramic fibers 13 and sacrificial fibers 12 in a CMC prepreg laminate 7, wherein the sacrificial fiber 12 has only a small cross-section of, for example, 1500 denier.
  • FIG. 4 a shows a 2-dimensional fiber fabric made of ceramic, for example oxidic, fiber 13, which is laid both in the x and y directions. In this 2-dimensional tissue is still a sacrificial fiber 12 is woven into the y-direction.
  • FIG. 4 b shows an exemplary layer of a hybrid fabric 15 in a CMC prepreg laminate 7.
  • FIG. 5 shows another example of a hybrid weave 15 in which the sacrificial fiber 12 has a substantially larger cross-section than the ceramic fiber 13.
  • a woven fabric of ceramic fiber 13 is woven in the x-direction and in the y-direction, wherein a fat sacrificial fiber 12 a after the other 12 b, 12 c, ... is once covered by the ceramic fabric 13 like a wave and alternatively once on the fabric 13 comes to rest.
  • a "fat" sacrificial fiber is a 10,000 denier roving carbon fiber.
  • FIG. 5b again shows the incorporation of this hybrid tissue into a CMC prepreg laminate 7, the thick sacrificial fibers 12 being visible here.
  • FIG. 6 shows an exemplary hybrid fiber composite 16 which is formed by interweaving three fibers 12, 13 and 17. It is freely selectable, where in the composite, the sacrificial fibers 12 and where the ceramic fibers 13 are, as well as the choice of the third fiber 17 as a sacrificial fiber or ceramic fiber, because the composite 16 by producing the sintered CMC Component is stable even after removing the sacrificial fibers.
  • oxide ⁇ ical ceramic fibers can also be processed with carbon fibers.
  • the carbon fibers may burn out during the temperature treatment and create a fine channel network for cooling a component.
  • the ceramic matrix for producing the CMC turbine component is subsequently infiltrated into the SD molding, for example via a transfer molding process.
  • at least one cooling channel or at least a portion of a cooling channel is supplemented with the Ver ⁇ reinforcing fibers of the CMC component to a pattern.
  • the present invention provides a turbine component ⁇ will be unveiled that has nal Modellen on fine and complexdeka-.
  • This cooling channel structures are produced in the CMC turbine component without these mecha nically ⁇ tiring process, such as etching, milling, cutting, etc. is subjected. This can be seen, for example, on the inner walls of the cooling ⁇ channels.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Materials Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Composite Materials (AREA)
  • Structural Engineering (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Powder Metallurgy (AREA)

Abstract

L'invention concerne des composants de turbine non métalliques, notamment des composants de turbine à gaz, par exemple pour des turbines à gaz fixes, en matériaux composites à matrice céramique (CMC). La présente invention concerne tout d'abord un composant de turbine en CMC, qui dispose de structures canaux de refroidissement fins et complexes. Ces structures canaux de refroidissement sont réalisés dans les composants de turbine CMC, sans soumettre ces derniers aux procédés mécaniquement éprouvants, tels que la gravure, le fraisage, la coupe etc.. Cela est reconnaissable, par exemple, aux parois internes des canaux de refroidissement.
PCT/EP2018/051518 2017-01-31 2018-01-23 Composant de turbine cmc dotée de structures de refroidissement complexes ainsi que procédé de fabrication Ceased WO2018141574A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102017201505.5A DE102017201505A1 (de) 2017-01-31 2017-01-31 rCMC-Turbinenkomponente mit komplexen Kühlstrukturen sowie Verfahren zur Herstellung dazu
DE102017201505.5 2017-01-31

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Publication Number Publication Date
WO2018141574A1 true WO2018141574A1 (fr) 2018-08-09

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Publication number Priority date Publication date Assignee Title
DE102018204470A1 (de) * 2018-03-23 2019-09-26 Siemens Aktiengesellschaft Verfahren zur Herstellung eines keramischen Faserverstärkten-Matrixwerkstoff-CMC-Formkörpers mit Kühlkanälen, sowie entsprechender Formkörper
WO2020112076A1 (fr) * 2018-11-26 2020-06-04 Siemens Aktiengesellschaft Composants composites à matrice céramique renforcée
US11680488B2 (en) * 2019-12-20 2023-06-20 General Electric Company Ceramic matrix composite component including cooling channels and method of producing

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WO2016159933A1 (fr) 2015-03-27 2016-10-06 Siemens Aktiengesellschaft Composants composites hybrides à matrice céramique pour turbines à gaz
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EP3115199A1 (fr) * 2015-07-10 2017-01-11 General Electric Technology GmbH Fabrication de panneaux simples ou multiples
EP3255247A1 (fr) * 2016-06-06 2017-12-13 General Electric Company Composant de turbine et procédés de fabrication et de refroidissement d'un composant de turbine
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