CN114105663B - Blade body shaping method of ceramic matrix composite turbine guide blade with cooling cavity - Google Patents
Blade body shaping method of ceramic matrix composite turbine guide blade with cooling cavity Download PDFInfo
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- CN114105663B CN114105663B CN202111391815.3A CN202111391815A CN114105663B CN 114105663 B CN114105663 B CN 114105663B CN 202111391815 A CN202111391815 A CN 202111391815A CN 114105663 B CN114105663 B CN 114105663B
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- 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
- C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
- C04B35/71—Ceramic products containing macroscopic reinforcing agents
- C04B35/78—Ceramic products containing macroscopic reinforcing agents containing non-metallic materials
- C04B35/80—Fibres, filaments, whiskers, platelets, or the like
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- 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
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
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- 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
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
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- 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
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
- C04B2235/5244—Silicon carbide
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- 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
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
- C04B2235/5248—Carbon, e.g. graphite
-
- 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
- C04B2235/5252—Fibers having a specific pre-form
- C04B2235/5256—Two-dimensional, e.g. woven structures
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- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
The invention discloses a blade body shaping method of a ceramic matrix composite turbine guide blade with a cooling cavity, which comprises the following steps: preparing a core mold, an outer mold I and an outer mold II of the blade body, winding fiber cloth along each core mold, splicing according to a design drawing to form a spliced fiber preform, winding the same fiber cloth along the periphery of the spliced fiber preform, clamping the obtained blade body integral fiber preform between the outer mold I, the outer mold II and the core mold, fixing the outer mold I and the outer mold II, and finally sewing the outer mold I, the outer mold II, the blade body integral preform and the core mold into a whole by adopting a suture line to finish the blade body shaping of the blade. The invention can complete the integral shaping of the blade body with a plurality of cooling cavities at one time, the method is simple, and the prepared blade body part after shaping by the method greatly improves the structural stability of the cooling cavities, avoids the air leakage problem among the cooling cavities, and further improves the structural reliability and the cooling effect of the component.
Description
Technical Field
The invention relates to the technical field of gas turbine engine manufacturing, in particular to a blade body shaping method of a ceramic matrix composite turbine guide blade with a cooling cavity.
Background
In the structure of a gas turbine engine such as an aeroengine, a gas turbine and the like, a turbine system is used for converting partial heat energy and potential energy in high-temperature gas into mechanical work and driving a gas compressor and accessories to work, the turbine system is a system with the largest heat load and power load in the gas turbine engine, and is characterized by large output power, high use temperature, light weight requirement and small structural size, and main hot end components in the turbine system comprise guide vanes, a turbine outer ring, a turbine disc, rotor blades and the like, wherein the guide vanes at the inlet of the turbine are parts with the highest working temperature in the turbine system and are used for converting partial heat energy of the high-temperature gas flow into kinetic energy and simultaneously enabling the gas flow to flow out in a certain direction so as to meet the gas flow and inlet direction required by the working turbine.
At present, high-temperature alloy materials commonly used for the turbine guide blade of an engine have the problems of heat resistance temperature of not higher than 1100 ℃, heavy weight and the like, and carbon fiber reinforced carbon matrix composite materials capable of resisting higher temperature have the defect of high temperature and easy oxidation. The density of the ceramic matrix composite is only 1/3-1/4 of high-temperature alloy, the heat-resistant temperature is 150-350 ℃ higher than that of the high-temperature alloy, the ceramic matrix composite is resistant to acid and alkali corrosion and high in toughness, and meanwhile, an oxide protective film generated by the reaction of the ceramic matrix composite in a high-temperature gas environment can block cracks and pores on the surface of the ceramic matrix composite and prevent external oxygen from diffusing into the ceramic matrix composite, so that the high-temperature stability and the long service life of a component are ensured, and therefore the ceramic matrix composite is considered as one of the first-choice materials of a new-generation aircraft engine thermal protection component at home and abroad. The typical structure of the turbine guide vane made of the ceramic matrix composite mainly comprises an upper edge plate, a lower edge plate and a vane body, and in order to prolong the service life of the vane, the vane body of the turbine guide vane of an advanced engine is designed into a hollow structure containing a cooling cavity, so that the cooling of the vane structure is facilitated, and when the guide vane body containing the cooling cavity is prepared by adopting the ceramic matrix composite, the first process flow is the shaping of a fiber preform. At present, cooling cavities in a blade body of a turbine guide blade are mainly manufactured through a blade body skin and a core baffle respectively, and are assembled to form sub-cavities in the later period.
Disclosure of Invention
In order to solve the technical problems, the invention aims to provide a blade body shaping method of a turbine guide blade made of a ceramic matrix composite material and provided with a cooling cavity, so as to solve the problems that in the prior art, when the turbine guide blade made of the ceramic matrix composite material and provided with the cooling cavity is adopted, the process is complicated, and the structure of the manufactured turbine guide blade is not reliable.
The technical scheme for solving the technical problems is as follows: the blade body shaping method of the ceramic matrix composite turbine guide blade with the cooling cavity comprises the following steps:
(1) respectively preparing a core mold by taking each cooling cavity of the blade body as a reference, preparing a first outer mold by taking the blade back as a reference, and preparing a second outer mold by taking the blade basin as a reference; the core mold, the outer mold I and the outer mold II are all made of high-temperature-resistant materials;
(2) winding fiber cloth along a core mold of each cooling cavity to form a single-cavity fiber preform, splicing according to a design drawing to form a spliced fiber preform, and winding the same fiber cloth along the periphery of the spliced fiber preform to form a blade body integral fiber preform;
(3) clamping the blade body integral fiber prefabricated body between the outer mold I, the outer mold II and the core mold, and fixing the outer mold I and the outer mold II;
(4) and sewing the outer die I, the outer die II, the blade body integral prefabricated body and the core die into a whole by using the vent holes as sewing paths and adopting sewing lines to finish the blade body shaping of the blade.
The invention has the beneficial effects that: the method can realize the integral shaping of the blade body of the ceramic matrix composite guide blade with the cooling cavity, and has simple working procedures and high structural reliability.
On the basis of the technical scheme, the invention can be further improved as follows:
further, the diameter of the vent hole in the step (1) is 2-5 mm.
Further, the wall thickness of the first outer die and the second outer die in the step (1) is 3-10 mm.
Further, the high-temperature resistant material in the step (1) is electrode graphite or high-purity graphite.
Further, high purity graphite means that the carbon content of graphite is > 99.99%.
Further, the raw material of the fiber cloth in the step (2) is carbon fiber and/or silicon carbide fiber.
Further, the fiber cloth in the step (2) is two-dimensional woven fiber cloth, 2.5-dimensional woven fiber cloth, a unidirectional tape or the combination of at least two of the three.
Further, in the step (2), the winding thickness of the fiber cloth along the core mold is 0.5-0.6 times of the thickness of the blade body.
Further, the thickness of the fiber cloth wound along the periphery of the spliced fiber preform in the step (2) is 0.6-0.8 times of the thickness of the blade body.
Further, after the spliced fiber preform is formed in the step (2), holes left at the corner during splicing are filled with the same fiber cloth as the single-cavity fiber preform, and then the same fiber cloth is wound along the periphery of the spliced fiber preform.
Further, in the step (3), the first outer die and the second outer die are fixed by bolts/nuts, and the materials of the bolts/nuts are the same as those of the first outer die and the second outer die.
Further, the suture thread in the step (4) is a carbon fiber bundle or a silicon carbide fiber bundle.
The invention also provides a blade body of the ceramic matrix composite turbine guide blade with the cooling cavity, which is formed by the method.
The invention has the following beneficial effects:
the blade body integral shaping device can complete integral shaping of the blade with a plurality of cooling cavities at one time, and does not need precise machining and assembling in the later period to form the cooling cavities;
the blade body of the ceramic matrix composite turbine guide blade with the cooling cavity, which is formed by the method, can be subjected to the subsequent densification process of the ceramic matrix by adopting a chemical vapor infiltration method, a resin impregnation cracking method or a melt infiltration method, and the process adaptability is good.
After the shaping is carried out by the method, the prepared blade body has continuous fibers in the circumferential direction and the radial direction of the section of the blade body, and a completely continuous fiber layering is also arranged at the cavity separation plate of the cooling cavity, so the shaping mode structurally ensures the structural rigidity and the strength of the blade body and the cooling cavity; in addition, the cavity-separating partition plate and the blade body prefabricated body are integrally formed, other assembling parts needing to be matched do not exist, and the problem of air leakage between cooling cavities is avoided from the design source, so that the cooling effect of the component is improved.
Drawings
FIG. 1 is a schematic illustration of a method for shaping a ceramic matrix composite guide vane airfoil having 2 cooling cavities;
FIG. 2 is a schematic view of a ceramic matrix composite guide vane airfoil having 2 cooling cavities;
FIG. 3 is an exploded view of the blade profile of the blade;
FIG. 4 is a perspective view of a body of a cooling cavity-containing ceramic matrix composite guide vane prepared in example 1.
Wherein, 1, cooling cavity; 2. leaf back; 3. leaf basin; 4. a core mold; 5. a first outer mold; 6. a second outer mold; 7. a vent hole; 8. a blade body integral fiber preform; 9. and (4) sewing.
Detailed Description
The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention. The examples, in which specific conditions are not specified, were carried out according to conventional conditions or conditions recommended by the manufacturer. The reagents or instruments used are conventional products which are not indicated by manufacturers and are commercially available.
Example 1:
a method for shaping a blade body of a ceramic matrix composite turbine guide blade with a cooling cavity comprises the following steps:
(1) respectively preparing a core mold 4 by taking each cooling cavity 1 of the blade body as a reference, preparing an outer mold I5 with the wall thickness of 5mm by taking the blade back 2 as a reference, and preparing an outer mold II 6 with the wall thickness of 5mm by taking the blade basin 3 as a reference; the core mold 4, the outer mold I5 and the outer mold II 6 are all provided with a plurality of vent holes 7 which are vertical to the molded surface and have the diameter of 2.5mm, and the core mold 4, the outer mold I5 and the outer mold II 6 are all made of high-purity graphite;
(2) winding two-dimensional carbon fiber woven cloth along the core mold 4 of each cooling cavity 1, wherein the winding thickness is 0.52 times of the thickness of the blade body to form a single-cavity fiber prefabricated body, splicing according to a design drawing to form a spliced fiber prefabricated body, rolling the two-dimensional carbon fiber woven cloth into a rod shape, filling holes left at a corner during splicing, winding the two-dimensional carbon fiber woven cloth along the periphery of the spliced fiber prefabricated body, and forming a blade body integral fiber prefabricated body 8, wherein the winding thickness is 0.7 times of the thickness of the blade body;
(3) clamping the blade body integral fiber prefabricated body 8 among the outer mold I5, the outer mold II 6 and the core mold 4, and fixing the outer mold I5 and the outer mold II 6 by using bolts/nuts made of high-purity graphite;
(4) and (3) taking the vent hole 7 as a sewing path, and sewing the outer die I5, the outer die II 6, the blade body integral fiber prefabricated body 8 and the core die 4 into a whole by adopting a carbon fiber bundle sewing line 9 to finish the blade body shaping of the blade.
Example 2:
a method for shaping a blade body of a ceramic matrix composite turbine guide blade with a cooling cavity comprises the following steps:
(1) respectively preparing a core mold 4 by taking each cooling cavity 1 of the blade body as a reference, preparing an outer mold I5 with the wall thickness of 3mm by taking the blade back 2 as a reference, and preparing an outer mold II 6 with the wall thickness of 3mm by taking the blade basin 3 as a reference; the core mold 4, the outer mold I5 and the outer mold II 6 are all provided with a plurality of vent holes 7 which are vertical to the molded surface and have the diameter of 2mm, and the core mold 4, the outer mold I5 and the outer mold II 6 are all made of electrode graphite;
(2) winding 2.5-dimensional silicon carbide fiber woven cloth along the core mold 4 of each cooling cavity 1, wherein the winding thickness is 0.5 time of the thickness of the blade body to form a single-cavity fiber prefabricated body, splicing according to a design drawing to form a spliced fiber prefabricated body, rolling the 2.5-dimensional silicon carbide fiber woven cloth into a rod shape, filling holes left at a corner during splicing, and then winding the 2.5-dimensional silicon carbide fiber woven cloth along the periphery of the spliced fiber prefabricated body, wherein the winding thickness is 0.6 time of the thickness of the blade body to form a blade body integral fiber prefabricated body 8;
(3) clamping the blade body integral fiber prefabricated body 8 among the outer mold I5, the outer mold II 6 and the core mold 4, and fixing the outer mold I5 and the outer mold II 6 by bolts/nuts made of electrode graphite;
(4) and (3) taking the vent hole 7 as a sewing path, and sewing the outer die I5, the outer die II 6, the blade body integral fiber prefabricated body 8 and the core die 4 into a whole by adopting a silicon carbide fiber bundle sewing line 9 to finish the blade body shaping of the blade.
Example 3:
a method for shaping a blade body of a ceramic matrix composite turbine guide blade with a cooling cavity comprises the following steps:
(1) respectively preparing a core mold 4 by taking each cooling cavity 1 of the blade body as a reference, preparing an outer mold I5 with the wall thickness of 10mm by taking the blade back 2 as a reference, and preparing an outer mold II 6 with the wall thickness of 10mm by taking the blade basin 3 as a reference; the core mold 4, the outer mold I5 and the outer mold II 6 are all provided with a plurality of vent holes 7 which are vertical to the molded surface and have the diameter of 5mm, and the core mold 4, the outer mold I5 and the outer mold II 6 are all made of electrode graphite;
(2) winding the carbon fiber unidirectional tape along the core mold 4 of each cooling cavity 1, wherein the winding thickness is 0.6 times of the thickness of the blade body to form a single-cavity fiber prefabricated body, splicing according to a design drawing to form a spliced fiber prefabricated body, rolling the carbon fiber unidirectional tape into a rod shape, filling holes left at a corner during splicing, and winding the carbon fiber unidirectional tape along the periphery of the spliced fiber prefabricated body, wherein the winding thickness is 0.8 times of the thickness of the blade body to form an integral fiber prefabricated body 8 of the blade body;
(3) clamping the blade body integral fiber prefabricated body 8 among the outer mold I5, the outer mold II 6 and the core mold 4, and fixing the outer mold I5 and the outer mold II 6 by bolts/nuts made of electrode graphite;
(4) and (3) taking the vent hole 7 as a sewing path, and sewing the outer die I5, the outer die II 6, the blade body integral fiber prefabricated body 8 and the core die 4 into a whole by adopting a carbon fiber bundle sewing line 9 to finish the blade body shaping of the blade.
Effect verification
The blade body of the cooling cavity-containing ceramic matrix composite turbine guide blade prepared by the shaping method of the embodiment 1-3 is subjected to effect verification, and the specific verification method comprises the following steps: according to GJB 150.16A-2009 military equipment laboratory environmental test method part 16: vibration test, the verification result is as follows: 25g of total root mean square acceleration in the frequency band of 10-2000Hz rms Under the condition, the blade body structure is complete after the test, and abnormal phenomena such as cracking, layering, block falling and the like do not occur, which shows that the sizing method of the invention can improveHigh reliability of the structure of the component and cooling effect.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and should not be taken as limiting the scope of the present invention, which is intended to cover any modifications, equivalents, improvements, etc. within the spirit and scope of the present invention.
Claims (8)
1. A blade body shaping method of a ceramic matrix composite turbine guide blade with a cooling cavity is characterized by comprising the following steps:
(1) respectively preparing a core mold (4) by taking each cooling cavity (1) of the blade body as a reference, preparing an outer mold I (5) by taking the blade back (2) as a reference, and preparing an outer mold II (6) by taking the blade basin (3) as a reference; the core mold (4), the outer mold I (5) and the outer mold II (6) are all provided with a plurality of vent holes (7) vertical to the molded surface, and the core mold (4), the outer mold I (5) and the outer mold II (6) are all made of high-temperature-resistant materials;
(2) winding fiber cloth along the core mold (4) of each cooling cavity (1) to form a single-cavity fiber preform, splicing according to a design drawing to form a spliced fiber preform, and winding the same fiber cloth along the periphery of the spliced fiber preform to form a blade body integral fiber preform (8);
(3) clamping the blade body integral fiber prefabricated body (8) among the outer die I (5), the outer die II (6) and the core die (4), and fixing the outer die I (5) and the outer die II (6);
(4) taking the vent hole (7) as a sewing path, and sewing the outer die I (5), the outer die II (6), the blade body integral prefabricated body (8) and the core die (4) into a whole by adopting a sewing line (9) to finish the blade body shaping of the blade;
wherein, the raw material of the fiber cloth in the step (2) is carbon fiber and/or silicon carbide fiber;
and (3) after the spliced fiber preform is formed in the step (2), filling holes left at the corner during splicing by adopting fiber cloth which is the same as the single-cavity fiber preform, and then winding the same fiber cloth along the periphery of the spliced fiber preform.
2. The method for shaping the blade body of the cooling cavity-containing ceramic matrix composite turbine guide blade according to claim 1, wherein the diameter of the vent hole (7) in the step (1) is 2-5 mm.
3. The method for shaping the blade body of the cooling cavity-containing ceramic matrix composite turbine guide blade according to claim 1, wherein the high-temperature-resistant material in the step (1) is electrode graphite or high-purity graphite.
4. The method for shaping the blade body of the cooling cavity-containing ceramic matrix composite turbine guide blade according to claim 1, wherein in the step (2), the fiber cloth is wound along the core mold (4) to a thickness of 0.5 to 0.6 times of the thickness of the blade body.
5. The method for shaping the blade body of the cooling cavity-containing ceramic matrix composite turbine guide blade according to claim 1, wherein the fiber cloth is wound along the periphery of the split fiber preform in the step (2) to a thickness of 0.6 to 0.8 times the thickness of the blade body.
6. The method for shaping the blade body of the cooling cavity-containing ceramic matrix composite turbine guide blade according to claim 1, wherein in the step (3), the first outer die (5) and the second outer die (6) are fixed by bolts/nuts, and the materials of the bolts/nuts are the same as those of the first outer die (5) and the second outer die (6).
7. The method for shaping the airfoil of a cooling cavity-containing ceramic matrix composite turbine vane according to claim 1, wherein the stitches (9) in step (4) are carbon fiber bundles or silicon carbide fiber bundles.
8. The blade body of the cooling cavity (1) -containing ceramic matrix composite turbine guide blade formed by the blade body forming method of the cooling cavity-containing ceramic matrix composite turbine guide blade according to any one of claims 1 to 7.
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| CN202111391815.3A CN114105663B (en) | 2021-11-19 | 2021-11-19 | Blade body shaping method of ceramic matrix composite turbine guide blade with cooling cavity |
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| CN202111391815.3A CN114105663B (en) | 2021-11-19 | 2021-11-19 | Blade body shaping method of ceramic matrix composite turbine guide blade with cooling cavity |
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| CN115093231B (en) * | 2022-06-23 | 2023-09-01 | 西安鑫垚陶瓷复合材料有限公司 | Ceramic matrix composite guide vane with trailing edge split joint and preparation method thereof |
| EP4357114A1 (en) * | 2022-10-21 | 2024-04-24 | RTX Corporation | Floating tooling assembly for chemical vapor infiltration |
| CN115872760A (en) * | 2022-10-24 | 2023-03-31 | 西安鑫垚陶瓷复合材料股份有限公司 | Filling method of strip holes in ceramic matrix composite prefabricated body |
| CN117823234A (en) * | 2024-03-05 | 2024-04-05 | 西北工业大学 | Ceramic fiber laminated double-cavity air-cooled turbine rotor blade structure |
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| US6627019B2 (en) * | 2000-12-18 | 2003-09-30 | David C. Jarmon | Process for making ceramic matrix composite parts with cooling channels |
| US9663404B2 (en) * | 2012-01-03 | 2017-05-30 | General Electric Company | Method of forming a ceramic matrix composite and a ceramic matrix component |
| CN103113123B (en) * | 2013-02-04 | 2014-03-12 | 西安交通大学 | Preparation method of SiCf/SiC ceramic matrix composite turbine blades |
| FR3012064B1 (en) * | 2013-10-23 | 2016-07-29 | Snecma | FIBROUS PREFORMS FOR TURBOMACHINE HOLLOW DREAM |
| CN204622394U (en) * | 2015-03-16 | 2015-09-09 | 天津工业大学 | A kind of carbon fiber cell type prefabricated component is made and is used shaper |
| CN106278335B (en) * | 2016-08-05 | 2019-02-05 | 西安交通大学 | A kind of manufacturing method of fiber alignment toughening ceramic based composites turbo blade |
| US10480108B2 (en) * | 2017-03-01 | 2019-11-19 | Rolls-Royce Corporation | Ceramic matrix composite components reinforced for managing multi-axial stresses and methods for fabricating the same |
| US11040915B2 (en) * | 2018-09-11 | 2021-06-22 | General Electric Company | Method of forming CMC component cooling cavities |
| CN210026378U (en) * | 2019-05-31 | 2020-02-07 | 洛阳北玻台信风机技术有限责任公司 | Large industrial fan made of carbon fiber |
| GB201913394D0 (en) * | 2019-09-17 | 2019-10-30 | Rolls Royce Plc | A vane |
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