CN114483207A - Ceramic matrix composite turbine outer ring preform, shaping mold and using method thereof - Google Patents
Ceramic matrix composite turbine outer ring preform, shaping mold and using method thereof Download PDFInfo
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- CN114483207A CN114483207A CN202111642776.XA CN202111642776A CN114483207A CN 114483207 A CN114483207 A CN 114483207A CN 202111642776 A CN202111642776 A CN 202111642776A CN 114483207 A CN114483207 A CN 114483207A
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- 238000007493 shaping process Methods 0.000 title claims abstract description 38
- 239000011153 ceramic matrix composite Substances 0.000 title claims abstract description 37
- 238000000034 method Methods 0.000 title claims abstract description 16
- 239000000835 fiber Substances 0.000 claims abstract description 47
- 239000004744 fabric Substances 0.000 claims description 51
- 238000009958 sewing Methods 0.000 claims description 34
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 15
- 239000004917 carbon fiber Substances 0.000 claims description 15
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 15
- 230000003014 reinforcing effect Effects 0.000 claims description 15
- HBMJWWWQQXIZIP-UHFFFAOYSA-N silicon carbide Chemical compound [Si+]#[C-] HBMJWWWQQXIZIP-UHFFFAOYSA-N 0.000 claims description 15
- 229910010271 silicon carbide Inorganic materials 0.000 claims description 15
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 12
- 239000000945 filler Substances 0.000 claims description 10
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 claims description 9
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 claims description 6
- 229910052799 carbon Inorganic materials 0.000 claims description 6
- 229910002804 graphite Inorganic materials 0.000 claims description 6
- 239000010439 graphite Substances 0.000 claims description 6
- 238000004804 winding Methods 0.000 claims description 3
- 238000003825 pressing Methods 0.000 claims description 2
- 238000004513 sizing Methods 0.000 claims 3
- 230000007547 defect Effects 0.000 abstract description 3
- 230000002349 favourable effect Effects 0.000 abstract 1
- 239000000463 material Substances 0.000 description 7
- 239000002131 composite material Substances 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 229910045601 alloy Inorganic materials 0.000 description 2
- 239000000919 ceramic Substances 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 239000000758 substrate Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 229910017052 cobalt Inorganic materials 0.000 description 1
- 239000010941 cobalt Substances 0.000 description 1
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000012467 final product Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 229910052759 nickel Inorganic materials 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- 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
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a ceramic matrix composite turbine outer ring preform, a shaping mold and a use method thereof, which overcome the defects of high design difficulty of the ceramic matrix composite turbine outer ring fiber preform, poor mold sticking uniformity of the fiber preform and low protection on the fiber preform during demolding, wherein the preform comprises an omega-shaped cover plate preform, an arc-shaped pipe section preform and an arc-shaped plate preform; the structural design scheme is not only favorable for reducing the number of the prefabricated parts and the shaping difficulty of the prefabricated parts, but also greatly improves the die attaching uniformity and the bonding strength among the prefabricated parts. The shaping mold comprises an outer mold and an inner mold. The external contour of the prefabricated body is shaped in a mode of opening and closing the die, and the rectangular rotary cavity of the component is shaped through the internal die. The structure of the shaping mold is simplified, the fiber preform is protected highly, the mold closing and demolding efficiency is greatly improved, and the shaping difficulty is reduced.
Description
Technical Field
The invention relates to a ceramic matrix composite turbine outer ring, in particular to a structure form of a ceramic matrix turbine outer ring prefabricated body; the invention also relates to a high-temperature shaping mold of the ceramic matrix composite turbine outer ring preform and a use method of the mold. The invention belongs to the technical field of structures of turbine parts of aircraft engines.
Background
The outer turbine ring (also called the turbine shroud ring) is the main structural component of the turbine stator, and the main function of the outer turbine ring is to constitute the high-temperature gas passage of the turbine component. With the continuous development of advanced aircraft engines, the requirements of higher temperature resistance, longer service life and lighter weight are put on the turbine outer ring component.
At present, a ceramic matrix composite material is considered to be one of the most potential materials for developing advanced high-temperature components of engines by international public as a thermal structure function integrated material with the advantages of various materials such as low density, high temperature resistance, oxidation resistance, corrosion resistance, high toughness, high rigidity and the like. The comprehensive performance index of the alloy can well meet the use requirement of a high-performance turbine outer ring component, and gradually replaces the traditional nickel-based and cobalt-based high-temperature alloy to become a preferred material for preparing the turbine outer ring.
The structure of the ceramic matrix composite member and the fiber prefabricated body thereof have the integrated design characteristic, the fiber is used as the reinforcement of the composite material and is the main bearing phase of the composite material, and the structure and the performance of the fiber prefabricated body greatly influence the performance of the composite material and the member. When the ceramic matrix composite is used for preparing the turbine outer ring component, the first process flow is the structural design of the fiber preform. The ceramic matrix composite has strong designability characteristic, and the general fiber preform structure is divided into 1D, 2D, 2.5D and 3D and a combined connection structure, wherein the 2D carbon fiber cloth or silicon carbide fiber cloth or alumina fiber cloth preform structure is the simplest, the process realizability is good, the ceramic matrix composite is suitable for forming thin-wall parts, but the difficulty for forming components with complex structures and large thickness sizes is higher. The second process flow is the setting of the fiber preform. The shaping of the fiber preform is realized by attaching and pressing a plurality of layers of carbon fiber cloth or silicon carbide fiber cloth or aluminum oxide fiber cloth on a preset rigid curved surface through the mold closing operation of a shaping mold. However, the structures of the shaping molds are different due to different prefabricated body structural forms of the ceramic-based turbine outer ring. And the problems of low die attaching rate, uneven clamping force, difficult demoulding and the like easily occur in the shaping process, so that the final product has layering, pore defects and ultra-poor profile size, thereby influencing the structural strength of the component. Therefore, technical optimization is required from the perspective of preform structure design, shaping mold design and mold use, and manufacturability and convenience of shaping of the turbine outer ring member are guaranteed.
The design difficulty of the ceramic matrix composite turbine outer ring preform structure and the shaping mold is the preform structure design when the carbon fiber cloth or the silicon carbide fiber cloth or the aluminum oxide fiber cloth is used for preparing the turbine outer ring with a specific structure form, the fiber preform has poor mold sticking uniformity and low protection on the fiber preform during demolding.
Disclosure of Invention
In order to overcome the defects of high design difficulty, poor mold sticking uniformity of a fiber preform and low protection on the fiber preform during demolding of the fiber preform of the outer ring of the ceramic matrix composite turbine, the invention provides a preform, a mold and a use method of the mold of the outer ring of the ceramic matrix composite turbine. The method can be used for preparing and shaping the turbine outer ring preform with the structural characteristics.
The technical scheme of the invention is to provide a prefabricated body of a ceramic matrix composite turbine outer ring, which is characterized in that: the outer ring of the turbine comprises a turbine outer ring main body prefabricated body and a filler prefabricated body;
the turbine outer ring main body prefabricated body comprises an arc-shaped plate prefabricated body, an arc-shaped pipe section prefabricated body and an omega-shaped cover plate prefabricated body;
the arc-shaped plate prefabricated body is in an arc-shaped plate shape, and the inner surface of the arc-shaped plate prefabricated body is the inner surface of the outer ring of the turbine;
the bottom surface and the top surface of the arc-shaped pipe section prefabricated body are in arc plate shapes, are positioned on the outer surface of the arc-shaped plate prefabricated body and are concentric with the arc-shaped plate prefabricated body to form a cavity molded surface of the outer ring of the turbine;
the omega-shaped cover plate prefabricated body is omega-shaped along the radial section of the outer ring of the turbine and comprises flanges at two sides and a cavity formed in the middle; the shape of the cavity is matched with the shape of the arc-shaped pipe section prefabricated body; the omega-shaped cover plate prefabricated body is laid on the arc-shaped plate prefabricated body and the arc-shaped pipe section prefabricated body and used for connecting the arc-shaped pipe section prefabricated body and the arc-shaped plate prefabricated body to serve as the outer surface of the turbine outer ring component; the flanging of the omega-shaped cover plate prefabricated body is in contact with the exposed outer surface of the arc-shaped plate prefabricated body, and the inner wall surface of a cavity of the omega-shaped cover plate prefabricated body is in contact with the outer surface of the arc-shaped pipe section prefabricated body;
the filler prefabricated body is filled in a gap formed among the omega-shaped cover plate prefabricated body, the arc-shaped pipe section prefabricated body and the arc-shaped plate prefabricated body.
Further, the circumferential section of the arc-shaped pipe section prefabricated body is rectangular.
Further, both the turbine outer ring main body preform and the filler preform can be prepared by adopting 2D carbon fiber cloth or silicon carbide fiber cloth or alumina fiber cloth.
The invention also provides a shaping mold of the ceramic matrix composite turbine outer ring preform, which is characterized in that: comprises an external mold, an internal mold and a positioning pin;
the outer die comprises a first outer die and a second outer die;
the inner surface of the first outer mold is a using molded surface, and the surface shape of the inner surface of the first outer mold is matched with the outer surface of the omega-shaped cover plate; arranging a sewing hole on the first outer mold and arranging a positioning pin hole at the position of the non-use molded surface; during shaping, the positioning pin is fastened with the second outer die mold and is attached to and pressed against the upper surface and the side surface of the prefabricated body;
the upper surface of the second outer die is a using molded surface, and the surface type of the upper surface of the second outer die is matched with the inner surface of the arc-shaped plate prefabricated body; forming a sewing hole on the second outer die and forming a positioning pin hole at the position of the non-use molded surface; during shaping, the positioning pin is fastened with the first external mold, and is attached to and pressed against the lower surface of the prefabricated body;
the outer surface of the inner die is a using molded surface, and the surface shape of the inner die is matched with the inner surface of the prefabricated body of the arc-shaped pipe section; sewing holes are formed in the inner die, and positioning pin holes are formed in the positions of the non-use molded surfaces; and during shaping, the positioning pin is fastened with the second outer die mold for forming the arc-shaped pipe section prefabricated body.
Furthermore, the shaping mold of the ceramic matrix composite turbine outer ring preform further comprises a reinforcing frame and a wedge block, and the first outer mold and the second outer mold are compressed and fixed by the reinforcing frame and the wedge block.
Furthermore, the outer mold, the inner mold, the positioning pin, the reinforcing frame and the wedge block can be made of high-temperature materials, such as electrode graphite, high-purity graphite and the like.
The invention also provides a use method of the shaping mold of the ceramic matrix composite turbine outer ring preform, which is characterized by comprising the following steps of:
step 1, fixing a second outer die on an operation table to prevent the workpiece from rotating and translating in the subsequent operation process.
step 3, winding a certain number of layers of carbon fiber cloth or silicon carbide fiber cloth or aluminum oxide fiber cloth on the inner die mold to serve as an arc-shaped pipe section prefabricated body, and performing local simple sewing through sewing holes in the inner die mold;
step 4, assembling the inner mold die and the second outer mold die, and installing and positioning through the first positioning pin;
step 5, paving a filling part prefabricated body at the included angle position of the arc-shaped plate prefabricated body and the arc-shaped pipe section prefabricated body;
and 9, compressing and fixing the first outer die and the second outer die by using the reinforcing frame and the wedge block.
The invention has the advantages and beneficial effects that:
firstly, the outer ring structure of the ceramic matrix composite turbine provided by the invention adopts a prefabricated body structure design without hangers or mounting flanges, so that the structure is optimized, the number of prefabricated bodies is reduced, the shaping difficulty of the prefabricated bodies is reduced, and the die sticking uniformity and the bonding strength among all prefabricated bodies are greatly improved.
Secondly, the invention provides a ceramic matrix composite turbine outer ring preform shaping mold and a use method thereof. The prefabricated body shaping mold mainly comprises an outer mold, an inner mold and related components. And the external profile of the prefabricated part is shaped by adopting an upper and lower die assembly, and the square cavity of the component is shaped by an inner die. The structural design of the upper and lower die assembly and the arc inner die is adopted, so that the structure of the shaping die is simplified, the protection performance of the fiber preform is high, and the die assembly and demolding efficiency of the die is also improved.
Drawings
FIG. 1 is a schematic view of a ceramic matrix composite turbine outer ring preform according to example 1;
FIG. 2 is a schematic view of an outer ring arc-shaped plate preform of a ceramic matrix composite turbine in example 1;
FIG. 3 is a schematic view of a preform of an outer ring arc-shaped pipe section of the ceramic matrix composite turbine in example 1;
FIG. 4 is a schematic view of an omega-type cover plate preform of the outer ring of the ceramic matrix composite turbine in embodiment 1;
FIG. 5 is a schematic view showing the assembled form of the forming mold in example 2;
FIG. 6 is a schematic structural view of a first outer mold in example 2;
FIG. 7 is a schematic structural view of a second outer mold in example 2;
FIG. 8 is a schematic structural view of an inner mold in embodiment 2;
FIG. 9 is a schematic view of an embodiment of a reinforcing frame;
FIG. 10 is a schematic view of a first positioning pin in embodiment 2;
FIG. 11 is a schematic view of a second dowel of example 2;
FIG. 12 is a schematic view of a wedge in example 2;
FIG. 13 is a schematic view showing the arrangement of the arc plate preform in example 3;
FIG. 14 is a schematic view showing the formation of a preform for an arcuate tube segment in example 3;
FIG. 15 is a schematic view of an assembled inner mold and second outer mold of example 3;
FIG. 16 is a schematic view of the filler preform in example 3 after it is padded;
FIG. 17 is a schematic view of the omega type decking preform lay-up of example 3;
fig. 18 is a schematic diagram of the first outer mold, the second outer mold and the inner mold in example 3 after closing;
fig. 19 is a schematic view showing the first outer mold and the second outer mold being compressed and fixed by the reinforcing frame and the wedge in example 3;
the reference numbers in the figures are:
11-an arc-shaped plate prefabricated body, 12-an arc-shaped pipe section prefabricated body and 13-an omega-shaped cover plate prefabricated body;
111-the inner surface of the arc-shaped plate prefabricated body, 112-the outer surface of the arc-shaped plate prefabricated body; 121-the bottom surface of the arc-shaped pipe section preform, 122-the top surface of the arc-shaped pipe section preform; 131-flanging, 132-cavity; 1321 — inner wall surface of cavity;
2-a filler preform;
31-a first outer mould, 32-a second outer mould, 33-an inner mould;
311-the inner surface of the first outer mold, 321-the upper surface of the second outer mold, 322-the positioning structure, 3221-the groove, 3222-the boss, 3223-the spacing groove;
41-a first positioning pin, 42-a second positioning pin;
5-reinforcing frame, 6-wedge block, 7-sewing hole and 8-positioning pin hole.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, specific embodiments accompanied with figures are described in detail below, and it is apparent that the described embodiments are a part of the embodiments of the present invention, not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without making creative efforts based on the embodiments of the present invention, shall fall within the protection scope of the present invention.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, but the present invention may be practiced in other ways than those specifically described and will be readily apparent to those of ordinary skill in the art without departing from the spirit of the present invention, and therefore the present invention is not limited to the specific embodiments disclosed below.
Furthermore, reference herein to "one embodiment" or "an embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one implementation of the invention. The appearances of the phrase "in other embodiments" in various places in the specification are not necessarily all referring to the same embodiment, nor are separate or alternative embodiments mutually exclusive of other embodiments.
Furthermore, the present invention is described in detail with reference to the drawings, and in the detailed description of the embodiments of the present invention, the cross-sectional view illustrating the structure of the device is not enlarged partially according to the general scale for convenience of illustration, and the drawings are only exemplary and should not be construed as limiting the scope of the present invention. In addition, the three-dimensional dimensions of length, width and depth should be included in the actual fabrication.
Meanwhile, in the description of the present invention, it should be noted that the terms "upper, lower, inner and outer" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation and operate, and thus, cannot be construed as limiting the present invention. Furthermore, the terms "first or second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Example 1
The structure of the ceramic matrix composite turbine outer ring preform in the embodiment is shown in fig. 1, and comprises a turbine outer ring main body preform and a filler preform 2, wherein a plurality of ceramic matrix composite turbine outer ring preforms can be spliced end to form an annular ceramic matrix composite turbine outer ring substrate; the turbine outer ring main body prefabricated body and the filling part prefabricated body 2 can be prepared by adopting 2D carbon fiber cloth or silicon carbide fiber cloth or alumina fiber cloth. The prefabricated body of the outer ring main body of the turbine consists of three parts, namely an arc-shaped plate prefabricated body 11 positioned at the bottommost layer, an arc-shaped pipe section prefabricated body 12 positioned in the middle and an omega-shaped cover plate prefabricated body 13 positioned at the uppermost layer. The filler preform 2 is filled in a gap formed among the omega-type cover plate preform 13, the arc pipe section preform 12 and the arc plate preform 11.
Referring to fig. 2, it can be seen that the arc plate preform 11 is in an arc plate shape as a whole, and the inner surface 111 of the arc plate preform is the inner surface of the outer ring substrate of the turbine.
Referring to fig. 3, it can be seen that the bottom surface 121 of the arc-shaped pipe segment preform and the top surface 122 of the arc-shaped pipe segment preform are arc-plate-shaped, and the circumferential cross section is rectangular, but in other embodiments, the circumferential cross section may have other shapes. The arc-shaped pipe section prefabricated body 12 is positioned on the outer surface 112 of the arc-shaped plate prefabricated body and is concentric with the arc-shaped plate prefabricated body 11 to form a cavity molded surface of the outer ring matrix of the turbine, and the cavity molded surface is used for mounting components and an air flow channel.
With reference to fig. 4, it can be seen that the omega-type cover plate preform 13 is omega-shaped along the radial section of the turbine outer ring, and includes flanges 131 on both sides and a cavity 132 formed in the middle; the shape of the cavity 132 is matched with the shape of the arc-shaped pipe section prefabricated body 12; the omega-shaped cover plate prefabricated body 13 is laid on the arc-shaped plate prefabricated body 11 and the arc-shaped pipe section prefabricated body 12 and used for connecting the arc-shaped pipe section prefabricated body 11 and the arc-shaped plate prefabricated body 12 to serve as the outer surface of the outer ring base body of the turbine; as can be seen from fig. 1, the flange 131 of the omega-type cover preform 13 is in contact with the exposed outer surface of the arc-shaped plate preform 11, and the inner wall surface 1321 of the cavity of the omega-type cover preform 13 is in contact with the outer surface of the arc-shaped pipe section preform 12.
Example 2
The present embodiment is a shaping mold for a ceramic matrix composite turbine outer ring preform according to embodiment 1, and as can be seen from fig. 5, the shaping mold comprises an outer mold, an inner mold 33, a positioning pin, a reinforcing frame 5 and a wedge 6; the outer mold, the inner mold 33, the positioning pin, the reinforcing frame 5 and the wedge 6 can be made of high-temperature materials, such as electrode graphite, high-purity graphite and the like. The outer mold comprises a first outer mold 31 and a second outer mold 32; the positioning pins include a first positioning pin 41 and a second positioning pin 42, as shown in fig. 10 and 11, the length of the first positioning pin 41 is greater than the length of the second positioning pin 42, the first positioning pin 41 is used for positioning the first outer mold 31 and the second outer mold 32, and the second positioning pin 42 is used for positioning the inner mold 33 and the second outer mold 32.
As can be seen in fig. 6, the profile of the inner surface 311 of the first outer mold is matched with the profile of the outer surface of the omega-type cover plate, and is used as a use profile; a plurality of sewing holes 7 are formed in the first outer mold 31, and as can be seen from the figure, the sewing holes 7 are located at the position of the use molded surface, and the sewing holes 7 are uniformly distributed along the circumferential direction. A positioning pin hole 8 is formed in the non-use molded surface of the first external mold 31; and during shaping, the first positioning pin 41 is fastened with the second outer mold 32, and is attached to and pressed against the upper surface and the side surface of the prefabricated body.
As can be seen in fig. 7, the upper surface 321 of the second outer mold is a using profile, and the profile of the upper surface is matched with the inner surface 111 of the arc-shaped plate preform; meanwhile, in order to realize positioning with the inner mold 33, positioning structures 322 are arranged at two ends of the second outer mold 32, and as can be seen from the figure, the positioning structures 322 comprise grooves 3221 which are arranged at two ends of the upper surface 321 of the second outer mold, the grooves 3221 extend along the axial direction of the second outer mold 32, and demolding can be realized quickly through the grooves; the positioning structure further comprises a boss 3222 arranged on the groove wall at the outer side of the groove, and a limiting groove 3223 is further formed on the boss, and is matched with two ends of the inner mold 33 for limiting the inner mold 33. A plurality of sewing holes 7 are formed in the second outer mold 32, positioning pin holes 8 are formed in the non-use molded surface, and the sewing holes 7 are uniformly distributed in the circumferential direction. During shaping, the first positioning pin 41 is fastened with the first external mold 31, and is attached to and pressed against the lower surface of the preform.
As can be seen from fig. 8, the inner mold 33 is an arc-shaped plate with a rectangular circumferential cross section, and the outer surface of the inner mold is a use-type surface which is matched with the inner surface of the arc-shaped pipe segment preform 12; a plurality of sewing holes 7 are formed in the inner mould, and positioning pin holes 8 are formed in the positions of the non-use molded surfaces; the plurality of sewing holes 7 are uniformly distributed in the circumferential direction. And in the shaping process, the second positioning pin 42 is fastened with the second outer die mold 32 and is used for forming the arc-shaped pipe section preform 12.
As can be seen from fig. 9, the reinforcing frame of the present embodiment is a rectangular frame, and the first outer mold and the second outer mold can be compressed and fixed by using the reinforcing frame and the wedge.
Example 3
The embodiment is a use method of the mold for shaping the ceramic matrix composite turbine outer ring preform in embodiment 2, and the method can be used for shaping the ceramic matrix composite turbine outer ring preform in embodiment 1, and specifically includes the following steps:
step 1, fixing the second outer die 32 on the operation table to prevent the workpiece from rotating and translating in the subsequent operation process.
step 3, as shown in fig. 14, winding a certain number of layers of carbon fiber cloth or silicon carbide fiber cloth or alumina fiber cloth on the inner mold die 33 as the arc-shaped pipe segment preform 12, and performing local simple sewing through the sewing holes 7 on the inner mold die 33;
step 4, as shown in fig. 15, assembling the inner mold 33 and the second outer mold 32, clamping the two ends of the inner mold 33 into the limiting grooves 3223 at the two ends of the second outer mold 32, and installing and positioning through the first positioning pins 41;
step 5, as shown in fig. 16, padding the filler preform 2 at an included angle position between the arc-shaped plate preform 11 and the arc-shaped pipe section preform 12 (the included angle position can also be described as a chamfer position of the bottom surface and the side surface of the arc-shaped pipe section preform, as shown by reference numeral 2 in fig. 1);
step 9, as shown in fig. 19, the first outer mold 31 and the second outer mold 32 are pressed and fixed by using the reinforcing frame 5 and the wedge 6.
Claims (8)
1. The utility model provides a ceramic matrix composite turbine outer ring preform which characterized in that: the outer ring of the turbine comprises a turbine outer ring body prefabricated body and a filler prefabricated body (2);
the turbine outer ring main body prefabricated body comprises an arc-shaped plate prefabricated body (11), an arc-shaped pipe section prefabricated body (12) and an omega-shaped cover plate prefabricated body (13);
the arc-shaped plate prefabricated body (11) is in an arc plate shape, and the inner surface (111) of the arc-shaped plate prefabricated body is the inner surface of the outer ring of the turbine;
the bottom surface (121) of the arc-shaped pipe section prefabricated body and the top surface (122) of the arc-shaped pipe section prefabricated body are arc-shaped plates, are positioned on the outer surface (112) of the arc-shaped plate prefabricated body and are concentric with the arc-shaped plate prefabricated body (11), and a cavity molded surface of an outer ring of the turbine is formed;
the omega-type cover plate prefabricated body (13) is omega-shaped along the radial section of the outer ring of the turbine and comprises flanges (131) at two sides and a cavity (132) formed in the middle; the shape of the cavity (132) is matched with the shape of the arc-shaped pipe section prefabricated body (12); the omega-type cover plate prefabricated body (13) is laid on the arc-shaped plate prefabricated body (11) and the arc-shaped pipe section prefabricated body (12) and used for connecting the arc-shaped pipe section prefabricated body (12) and the arc-shaped plate prefabricated body (11) and used as the outer surface of the turbine outer ring component; the flanging (131) of the omega-type cover plate prefabricated body (13) is in contact with the exposed outer surface of the arc-shaped plate prefabricated body (11), and the inner wall surface (1321) of the cavity of the omega-type cover plate prefabricated body (13) is in contact with the outer surface of the arc-shaped pipe section prefabricated body (12);
the filler prefabricated body (2) is filled in a gap formed among the omega-shaped cover plate prefabricated body (13), the arc-shaped pipe section prefabricated body and the arc-shaped plate prefabricated body (11).
2. The ceramic matrix composite turbine outer ring preform of claim 1, wherein: the circumferential section of the arc-shaped pipe section prefabricated body (12) is rectangular.
3. The ceramic matrix composite turbine outer ring preform of claim 2, wherein: the turbine outer ring main body preform and the filling part preform (2) can be prepared by adopting 2D carbon fiber cloth or silicon carbide fiber cloth or alumina fiber cloth.
4. A shaping mold for the ceramic matrix composite turbine outer ring preform according to any one of claims 1-3, wherein: comprises an external mold, an internal mold (33) and a positioning pin;
the outer mould comprises a first outer mould (31) and a second outer mould (32);
the inner surface (311) of the first outer mold is a use molded surface, and the surface shape of the inner surface is matched with the outer surface of the omega-shaped cover plate; a sewing hole (7) is formed in the first outer mold (31), and a positioning pin hole (8) is formed in the non-use molded surface; during shaping, the positioning pin is fastened with a second outer die (32) and is attached to and pressed tightly with the upper surface and the side surface of the prefabricated body of the outer ring of the ceramic matrix composite turbine;
the upper surface (321) of the second outer die is a using molded surface, and the surface type of the upper surface is matched with the inner surface (111) of the arc-shaped plate prefabricated body; a second outer die mould (32) is provided with a sewing hole (7) and a positioning pin hole (8) at the position of the non-use molded surface; during shaping, the positioning pin is fastened with a first external mold (31) and is attached to and pressed tightly against the lower surface of the prefabricated body of the ceramic matrix composite turbine outer ring;
the outer surface of the inner die mold (33) is a using molded surface, and the surface shape of the inner die mold is matched with the inner surface of the arc-shaped pipe section prefabricated body (12); a sewing hole (7) is formed in the inner mould die (33), and a positioning pin hole (8) is formed in the non-use molded surface; and when in shaping, the pipe is fastened with a second outer die mould (32) by using positioning pins and is used for forming the arc-shaped pipe section prefabricated body (12).
5. The sizing die as recited in claim 4, wherein: the die further comprises a reinforcing frame (5) and a wedge block (6), and the first outer die (31) and the second outer die (32) are pressed and fixed by the reinforcing frame (5) and the wedge block (6).
6. The sizing die as recited in claim 5, wherein: positioning structures (322) are arranged at two ends of the second outer die (32), each positioning structure (322) comprises a groove (3221) which is arranged at two ends of the upper surface (321) of the second outer die, and each groove (3221) extends along the axial direction of the second outer die (32); and a boss (3222) is arranged on the outer side groove wall of the groove (3221), and a limiting groove (3223) is formed in the boss and matched with two ends of the inner die (33) for limiting the inner die (33).
7. The sizing die as recited in claim 6, wherein: the outer die, the inner die (33), the positioning pins, the reinforcing frame (5) and the wedge blocks (6) can be prepared from electrode graphite or high-purity graphite.
8. A method for using a shaping mold for the ceramic matrix composite turbine outer ring preform according to any one of claims 4-7, comprising the steps of:
step 1, fixing a second outer die (32) on an operation table;
step 2, paving 1 layer of 1K carbon cloth and a set number of layers of carbon fiber cloth or silicon carbide fiber cloth or aluminum oxide fiber cloth as an arc-shaped plate prefabricated body (11) on the molded surface of a second outer mold die (32) from bottom to top in sequence, and locally performing simple sewing;
3, winding a certain number of layers of carbon fiber cloth or silicon carbide fiber cloth or alumina fiber cloth on the inner die (33) to serve as an arc-shaped pipe section prefabricated body (12), and performing local simple sewing through the sewing holes (7) in the inner die (33);
step 4, assembling the inner die (33) and the second outer die (32), and installing and positioning through positioning pins;
step 5, paving a filling part prefabricated body (2) at the included angle position of the arc-shaped plate prefabricated body (11) and the arc-shaped pipe section prefabricated body (12);
step 6, sequentially laying 1 layer of 1K carbon cloth and a set number of layers of carbon fiber cloth or silicon carbide fiber cloth or aluminum oxide fiber cloth on the molded surface of a first outer mold (31) to serve as an omega-shaped cover plate prefabricated body (13), and performing local simple sewing through sewing holes (7) in the mold;
step 7, mounting and fixing the first outer mold (31) on the second outer mold (32), and mounting and positioning through a positioning pin, wherein the inner mold (33) is positioned at the cavity (132) of the first outer mold (31);
step 8, integrally sewing all the prefabricated bodies through the sewing holes (7) on the die;
and 9, pressing and fixing the first outer die (31) and the second outer die (32) by using the reinforcing frame (5) and the wedge block (6).
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111642776.XA CN114483207B (en) | 2021-12-29 | 2021-12-29 | Ceramic matrix composite turbine outer ring preform, shaping die and using method thereof |
| PCT/CN2022/096452 WO2023123861A1 (en) | 2021-12-29 | 2022-05-31 | Ceramic-based composite material turbine outer ring preform, shaping mold, and use method therefor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111642776.XA CN114483207B (en) | 2021-12-29 | 2021-12-29 | Ceramic matrix composite turbine outer ring preform, shaping die and using method thereof |
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| CN114483207A true CN114483207A (en) | 2022-05-13 |
| CN114483207B CN114483207B (en) | 2024-03-08 |
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| WO (1) | WO2023123861A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115139393A (en) * | 2022-06-21 | 2022-10-04 | 西安鑫垚陶瓷复合材料有限公司 | 2.5D turbine outer ring prefabricated part shaping mold and using method thereof |
| WO2023123861A1 (en) * | 2021-12-29 | 2023-07-06 | 西安鑫垚陶瓷复合材料有限公司 | Ceramic-based composite material turbine outer ring preform, shaping mold, and use method therefor |
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| WO2023123861A1 (en) | 2023-07-06 |
| CN114483207B (en) | 2024-03-08 |
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Country or region after: China Address after: 710117 West Section 912 of Biyuan Road, Xi'an High-tech Zone, Shaanxi Province Applicant after: Xi'an Xinyao Ceramic Composite Co.,Ltd. Address before: 710117 West Section 912 of Biyuan Road, Xi'an High-tech Zone, Shaanxi Province Applicant before: XI'AN GOLDEN MOUNTAIN CERAMIC COMPOSITES CO.,LTD. Country or region before: China |
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