CN114483207B - Ceramic matrix composite turbine outer ring preform, shaping die and using method thereof - Google Patents
Ceramic matrix composite turbine outer ring preform, shaping die and using method thereof Download PDFInfo
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- CN114483207B CN114483207B CN202111642776.XA CN202111642776A CN114483207B CN 114483207 B CN114483207 B CN 114483207B CN 202111642776 A CN202111642776 A CN 202111642776A CN 114483207 B CN114483207 B CN 114483207B
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- 238000007493 shaping process Methods 0.000 title claims abstract description 40
- 239000011153 ceramic matrix composite Substances 0.000 title claims abstract description 37
- 238000000034 method Methods 0.000 title claims abstract description 14
- 239000000835 fiber Substances 0.000 claims abstract description 47
- 239000004744 fabric Substances 0.000 claims description 51
- 238000009958 sewing Methods 0.000 claims description 35
- 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
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 claims description 14
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 12
- 239000000945 filler Substances 0.000 claims description 9
- 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
- 238000004513 sizing Methods 0.000 claims 3
- 230000007547 defect Effects 0.000 abstract description 3
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 239000000463 material Substances 0.000 description 6
- 238000009417 prefabrication Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 239000011159 matrix material Substances 0.000 description 3
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 2
- 239000000919 ceramic Substances 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 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
- 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
- 238000003825 pressing Methods 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
- 239000011800 void material Substances 0.000 description 1
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
Abstract
The invention relates to a ceramic matrix composite turbine outer ring preform, a shaping mold and a using method thereof, which overcome the defects of high design difficulty of the ceramic matrix composite turbine outer ring fiber preform, poor mold attaching uniformity of the fiber preform and low protectiveness to 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 beneficial to reducing the number of the preformed bodies and reducing the shaping difficulty of the preformed bodies, but also greatly improves the die attaching uniformity and the bonding strength among the preformed body pieces. The shaping mould comprises an outer mould and an inner mould. 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 inner die. The shaping die structure is simplified, the protection to the fiber preform is high, the die 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 structural form of a ceramic matrix turbine outer ring preform; the invention also relates to a high-temperature shaping die of the ceramic matrix composite turbine outer ring preform and a using method of the die. The invention belongs to the technical field of structures of turbine components of aeroengines.
Background
The turbine outer ring (also known as the turbine shroud) is the primary structural component of the turbine stator, which primarily functions as the high temperature gas path that makes up the turbine component. With the continued development of advanced aircraft engines, a need has arisen for turbine outer ring components that are more resistant to higher temperatures, longer life, and lighter weight.
At present, the ceramic matrix composite is taken as a thermostructural 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, and is internationally recognized as one of the most potential materials for developing advanced engine high-temperature components. 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 superalloy to become the first-choice material for preparing the turbine outer ring.
The structure of the ceramic matrix composite member and the fiber preform thereof have the integrated design characteristic, the fiber is used as a reinforcement of the composite material and is a main bearing phase, and the structure and the performance of the fiber preform 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 characteristics, and general fiber preform structures are divided into 1D, 2D, 2.5D and 3D and combined connection structures, wherein the 2D carbon fiber cloth or silicon carbide fiber cloth or aluminum oxide fiber cloth preform structure is the simplest, the process realizability is good, and the ceramic matrix composite is suitable for forming thin-wall parts, but has larger difficulty in forming components with complex structures and large thickness sizes. The second process flow is the shaping of the fiber preform. The shaping of the fiber preform is realized by the die assembly operation of a shaping die, so that the multi-layer carbon fiber cloth or silicon carbide fiber cloth or aluminum oxide fiber cloth is attached and pressed on a preset rigid curved surface. However, the structures of the shaping dies are different due to the different structural forms of the prefabricated bodies of the outer rings of the ceramic-based turbines. In addition, the problems of low die sticking rate, uneven clamping force, difficult demoulding and the like easily occur in the shaping process, so that layering, void defects and out-of-tolerance of the profile size of the final product exist, and the structural strength of the member is affected. Therefore, technical optimization is required from the angles of the structural design of the preform, the design of the shaping die and the use of the die, and the manufacturability and convenience of shaping the outer ring component of the turbine are ensured.
The design difficulty of the ceramic matrix composite turbine outer ring preform structure and the shaping mold is that the preform structure design when the turbine outer ring with a specific structural form is prepared by using carbon fiber cloth or silicon carbide fiber cloth or aluminum oxide fiber cloth, the uniformity of the fiber preform sticking mold is poor, and the protection of the fiber preform during demolding is low.
Disclosure of Invention
In order to overcome the defects of high design difficulty, poor uniformity of fiber preform die attachment and low protection to the fiber preform during demolding of the fiber preform, the invention provides a preform, a die and a using method of the die of the ceramic matrix composite turbine outer ring. 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: comprises a turbine outer ring main body prefabricated body and a filling piece 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 preform is in an arc shape, and the inner surface of the arc-shaped plate preform is the inner surface of the outer ring of the turbine;
the bottom surface and the top surface of the arc pipe section preform are arc-shaped and are positioned on the outer surface of the arc plate preform and concentric with the arc plate preform to form a turbine outer ring cavity molded surface;
the radial section of the omega-shaped cover plate preform along the outer ring of the turbine is omega-shaped, and the omega-shaped cover plate preform 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 pipe section preform; the omega-shaped cover plate prefabricated body is paved on the arc-shaped plate prefabricated body and the arc-shaped pipe section prefabricated body and is 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 flange of the omega-shaped cover plate preform is contacted with the exposed outer surface of the arc-shaped plate preform, and the inner wall surface of the cavity of the omega-shaped cover plate preform is contacted with the outer surface of the arc-shaped pipe section preform;
the filler preform is filled in a gap formed among the omega-shaped cover plate preform, the arc-shaped pipe section preform and the arc-shaped plate preform.
Further, the circumferential section of the arc-shaped pipe section preform is rectangular.
Further, the turbine outer ring main body prefabricated body and the filling piece prefabricated body can be prepared by adopting 2D carbon fiber cloth or silicon carbide fiber cloth or aluminum oxide fiber cloth.
The invention also provides a shaping die of the ceramic matrix composite turbine outer ring preform, which is characterized in that: comprises an outer die, an inner die and a positioning pin;
the outer die comprises a first outer die and a second outer die;
the inner surface of the first outer die is a use molded surface, and the surface type of the first outer die is matched with the outer surface of the omega-shaped cover plate; a sewing hole is formed in the first outer die and a positioning pin hole is formed in a position where the molded surface is not used; during shaping, the positioning pins are used for fastening with the second outer die, and are attached to and pressed against the upper surface and the side surface of the preform;
the upper surface of the second outer die is a use molded surface, and the surface of the second outer die is matched with the inner surface of the arc-shaped plate preform; a sewing hole is formed in the second outer die and a positioning pin hole is formed in a position where the molded surface is not used; during shaping, the positioning pin is used for fastening with the first outer die and is attached to and pressed against the lower surface of the preform;
the outer surface of the inner die is a use molded surface, and the surface is matched with the inner surface of the arc pipe section preform; a sewing hole is formed in the inner die and a positioning pin hole is formed in a position where the molded surface is not used; during shaping, the positioning pins are used for fastening the second outer die and forming the arc pipe section prefabricated body.
Furthermore, the shaping die of the ceramic matrix composite turbine outer ring preform further comprises a reinforcing frame and a wedge block, and the reinforcing frame and the wedge block are used for compressing and fixing the first outer die and the second outer die.
Furthermore, the outer die, the inner die, the positioning pins, the reinforcing frame and the wedge block can be prepared from high-temperature materials, such as electrode graphite, high-purity graphite and the like.
The invention also provides a using method of the shaping mold of the ceramic matrix composite turbine outer ring preform, which is characterized by comprising the following steps of:
and step 1, fixing a second outer die onto an operation table to prevent the workpiece from rotating and translating in the subsequent operation process.
Step 2, paving 1 layer of 1K carbon cloth and carbon fiber cloth or silicon carbide fiber cloth or aluminum oxide fiber cloth with a set layer number as arc plate prefabricated parts on a second outer die in sequence from bottom to top by using the molded surface, and locally and simply sewing;
step 3, winding carbon fiber cloth or silicon carbide fiber cloth or aluminum oxide fiber cloth with a certain layer number on the inner die as an arc-shaped pipe section prefabricated body, and carrying out local simple sewing through sewing holes on the inner die;
step 4, assembling the inner die and the second outer die, and installing and positioning through a first positioning pin;
step 5, laying a filler prefabricated body at the position of the included angle between the arc-shaped plate prefabricated body and the arc-shaped pipe section prefabricated body;
step 6, sequentially paving 1 layer of 1K carbon cloth and carbon fiber cloth or silicon carbide fiber cloth or aluminum oxide fiber cloth with a set layer number on the first outer die as an omega type cover plate preform, and carrying out local simple sewing through sewing holes on the die;
step 7, mounting and fixing the first outer die on the second outer die, and mounting and positioning the first outer die through a second positioning pin, wherein the inner die is positioned at the cavity part of the first outer die;
step 8, integrally sewing all the prefabricated bodies through sewing holes on the die;
and 9, compacting and fixing the first outer die and the second outer die by using the reinforcing frame and the wedge blocks.
The invention has the advantages and beneficial effects that:
firstly, the ceramic matrix composite turbine outer ring structure provided by the invention adopts a prefabricated body structure design without hanging lugs 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 meanwhile, the die attaching uniformity and the bonding strength among the prefabricated bodies are greatly improved.
Secondly, the invention provides a shaping die for an outer ring preform of a ceramic matrix composite turbine and a using method. The preform shaping mold mainly comprises an outer mold, an inner mold and related components. And the outer contour of the prefabricated body is shaped by adopting an upper die and a lower die, and the square cavity of the component is shaped by an inner die. The structural design of the upper and lower die closing and the arc-shaped inner die is adopted, so that the die closing and demolding efficiency of the die is improved while the protective performance on the fiber preform is higher.
Drawings
FIG. 1 is a schematic view of an outer ring preform of a ceramic matrix composite turbine in example 1;
FIG. 2 is a schematic view of an outer ring arcuate plate preform of a ceramic matrix composite turbine in example 1;
FIG. 3 is a schematic view of a ceramic matrix composite outer ring arcuate tube segment preform of example 1;
FIG. 4 is a schematic view of an outer ring omega-type cover plate preform for a ceramic matrix composite turbine in example 1;
FIG. 5 is a schematic diagram showing the assembly of the shaping 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 view of the internal mold in example 2;
FIG. 9 is a schematic view of a reinforcing frame in an embodiment;
fig. 10 is a schematic view of a first positioning pin in embodiment 2;
FIG. 11 is a schematic view of a second positioning pin in embodiment 2;
FIG. 12 is a schematic view of the wedge of example 2;
FIG. 13 is a schematic view of the laying 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 diagram showing the assembly of the inner mold and the second outer mold in example 3;
FIG. 16 is a schematic view of example 3 after laying a mat filler preform;
FIG. 17 is a schematic diagram showing the laying of omega-type deck preform in example 3;
FIG. 18 is a schematic diagram of the embodiment 3 after the first outer mold, the second outer mold and the inner mold are closed;
FIG. 19 is a schematic view showing the pressing and fixing of the first outer mold and the second outer mold by using the reinforcing frame and the wedge in example 3;
the reference numerals in the drawings are:
11-arc plate prefabricated body, 12-arc pipe section prefabricated body and 13-omega type cover plate prefabricated body;
111-the inner surface of the arc-shaped plate preform, 112-the outer surface of the arc-shaped plate preform; 121-a bottom surface of the arcuate tube segment preform, 122-a top surface of the arcuate tube segment preform; 131-flanging and 132-forming a cavity; 1321-inner wall surface of cavity;
2-filler preform;
31-a first outer die, 32-a second outer die, 33-an inner die;
311-the inner surface of the first outer die, 321-the upper surface of the second outer die, 322-the positioning structure, 3221-the groove, 3222-the boss and 3223-the limit groove;
41-a first locating pin, 42-a second locating pin;
5-reinforcing frame, 6-wedge block, 7-sewing hole and 8-positioning pin hole.
Detailed Description
So that the manner in which the above recited objects, features and advantages of the present invention can be understood in detail, a more particular description of the invention, briefly summarized above, may be had by reference to the embodiments, some of which are illustrated in the appended drawings. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments of the present invention without making any inventive effort, shall fall within the 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 other than those described herein, and persons skilled in the art will readily appreciate that the present invention is not limited to the specific embodiments disclosed below.
Further, reference herein to "one embodiment" or "an embodiment" means that a particular feature, structure, or characteristic can be 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.
Further, in describing the embodiments of the present invention in detail, the cross-sectional view of the device structure is not partially enlarged to a general scale for convenience of description, and the schematic is only an example, which should not limit the scope of protection of the present invention. In addition, the three-dimensional dimensions of length, width and depth should be included in actual fabrication.
Also in the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "upper, lower, inner and outer", etc. are based on the orientation or positional relationship shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not 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 this embodiment is shown in fig. 1, and the ceramic matrix composite turbine outer ring preform comprises a turbine outer ring main body preform and a filler preform 2, and a plurality of ceramic matrix composite turbine outer ring preforms can form an annular ceramic matrix composite turbine outer ring matrix after being spliced end to end; the turbine outer ring main body prefabricated body and the filling piece prefabricated body 2 can be prepared by adopting 2D carbon fiber cloth or silicon carbide fiber cloth or aluminum oxide fiber cloth. The turbine outer ring body prefabricated body 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 the gap formed among the omega-type cover-plate preform 13, the arcuate tube segment preform 12, and the arcuate plate preform 11.
Referring to fig. 2, it can be seen that the arcuate plate preform 11 has an overall arcuate plate shape, and the inner surface 111 of the arcuate plate preform is the inner surface of the turbine outer ring matrix.
Referring to fig. 3, it can be seen that the bottom surface 121 of the arcuate tube segment preform and the top surface 122 of the arcuate tube segment preform have an arcuate plate shape, and the circumferential cross section is rectangular, and in other embodiments, the circumferential cross section may have other shapes. The arcuate tube segment preform 12 is positioned on the arcuate plate preform outer surface 112 concentric with the arcuate plate preform 11 to form a turbine outer ring base cavity profile for mounting the assembly and the air flow passages.
Referring to fig. 4, it can be seen that the omega-shaped cover-plate preform 13 has an omega-shaped radial cross section along 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 adapted to the shape of the arcuate tube segment preform 12; omega type cover plate prefabrication body 13 is laid on arcuate plate prefabrication body 11 and arcuate tube segment prefabrication body 12, is used for connecting arcuate tube segment prefabrication body 11 and arcuate plate prefabrication body 12, as the outer surface of the outer ring basal body of the turbine; as can be seen from fig. 1, the flange 131 of the omega-shaped cover-plate preform 13 is in contact with the exposed outer surface of the arcuate-shaped plate preform 11, and the cavity inner wall surface 1321 of the omega-shaped cover-plate preform 13 is in contact with the outer surface of the arcuate-shaped tube segment preform 12.
Example 2
This example is a shaping mold for an outer ring preform of a ceramic matrix composite turbine of example 1, which, as can be seen from fig. 5, includes an outer mold, an inner mold 33, positioning pins, a reinforcing frame 5 and a wedge 6; the outer mold, the inner mold 33, the positioning pins, 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, and as shown in fig. 10 and 11, the length of the first positioning pin 41 is longer than that 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 connection with fig. 6, the inner surface 311 of the first outer mold is adapted to the outer surface of the omega-shaped cover plate as a use profile; the first outer mold 31 is provided with a plurality of sewing holes 7, and as can be seen from the figure, the sewing holes 7 are positioned at the position of the use molded surface, and the plurality of sewing holes 7 are uniformly distributed along the circumferential direction. A positioning pin hole 8 is formed at the non-use molded surface of the first outer mold 31; during shaping, the first positioning pins 41 are fastened with the second outer die 32, and are attached to the upper surface and the side surfaces of the preform and pressed.
As can be seen in connection with fig. 7, the upper surface 321 of the second outer mold is a use profile which is adapted to the inner surface 111 of the arcuate 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 formed 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 demoulding can be realized quickly through the grooves; the positioning structure further comprises a boss 3222 arranged on the outer side wall of the groove, and a limiting groove 3223 is further formed in the boss and 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 die 32, positioning pin holes 8 are formed in the position of the non-use molded surface, and the sewing holes 7 are uniformly distributed along the circumferential direction. During shaping, the first positioning pins 41 are fastened with the first outer die 31, and are attached to and pressed against the lower surface of the preform.
As can be seen in connection with fig. 8, the inner mold 33 is an arc-shaped plate with a rectangular circumferential cross section, the outer surface of the inner mold is a use molded surface, and the surface 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 die and positioning pin holes 8 are formed in positions where the molded surface is not used; the plurality of sewing holes 7 are uniformly distributed along the circumferential direction. During shaping, the second positioning pins 42 are used to fasten the second outer mold 32 for shaping the arcuate tube segment preform 12.
As can be seen from fig. 9, the reinforcing frame of this embodiment is a rectangular frame, and the first outer mold and the second outer mold can be pressed and fixed by using the reinforcing frame and the wedge block.
Example 3
The embodiment is a use method of the shaping mold for the ceramic matrix composite turbine outer ring preform in embodiment 2, by which shaping can be achieved for the ceramic matrix composite turbine outer ring preform in embodiment 1, and specifically includes the following steps:
step 1, the second outer die 32 is fixed on the operation table, so that the workpiece is prevented from rotating and translating during the subsequent operation.
Step 2, as shown in fig. 13, laying 1 layer of 1K carbon cloth and a carbon fiber cloth or silicon carbide fiber cloth or aluminum oxide fiber cloth with a set layer number in sequence from bottom to top as an arc plate preform 11 on a second outer die 32, and locally performing simple sewing;
step 3, as shown in fig. 14, winding carbon fiber cloth or silicon carbide fiber cloth or aluminum oxide fiber cloth with a certain layer number on an inner die 33 as an arc pipe section preform 12, and carrying out local simple sewing through sewing holes 7 on the inner die 33;
step 4, as shown in fig. 15, assembling the inner mold 33 and the second outer mold 32, wherein two ends of the inner mold 33 are clamped into limit grooves 3223 at two ends of the second outer mold 32, and are installed and positioned through first positioning pins 41;
step 5, as shown in fig. 16, laying the filler preform 2 at a position where the arc-shaped plate preform 11 forms an angle with the arc-shaped pipe segment preform 12 (this position can also be described as a position where the bottom surface and the side surface of the arc-shaped pipe segment preform are chamfered, as shown by reference numeral 2 in fig. 1);
step 6, as shown in fig. 17, paving 1 layer of 1K carbon cloth and a carbon fiber cloth or a silicon carbide fiber cloth or an alumina fiber cloth with a set layer number on a first outer mold 31 in sequence as an omega type cover plate preform 13, and performing local simple sewing through a sewing hole 7 on the mold;
step 7, as shown in fig. 18, the first outer mold 31 is mounted and fixed on the second outer mold 32, and is mounted and positioned by the second positioning pins 42, and the inner mold 33 is located at the cavity 132 of the first outer mold 31;
step 8, integrally sewing all the prefabricated bodies through sewing holes 7 on the die;
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. A ceramic matrix composite turbine outer ring preform, characterized by: comprises a turbine outer ring main body prefabricated body and a filling piece 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 type cover plate prefabricated body (13);
the arc-shaped plate prefabricated body (11) is in an arc 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 in an arc shape, 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) to form a turbine outer ring cavity molded surface;
the omega-shaped cover plate preform (13) is omega-shaped along the radial section of the outer ring of the turbine and comprises flanges (131) on 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-shaped cover plate prefabricated body (13) is paved on the arc-shaped plate prefabricated body (11) and the arc-shaped pipe section prefabricated body (12) and is used for connecting the arc-shaped pipe section prefabricated body (12) and the arc-shaped plate prefabricated body (11) to serve as the outer surface of the turbine outer ring component; the flange (131) of the omega-shaped cover plate 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-shaped cover plate preform (13) is in contact with the outer surface of the arc-shaped pipe section preform (12);
the filler preform (2) is filled in a gap formed among the omega-type cover plate preform (13), the arc-shaped pipe section preform and the arc-shaped plate preform (11).
2. The ceramic matrix composite turbine outer ring preform as defined in claim 1, wherein: the circumferential section of the arc-shaped pipe section preform (12) is rectangular.
3. The ceramic matrix composite turbine outer ring preform as claimed in claim 2, wherein: the turbine outer ring main body prefabricated body and the filling piece prefabricated body (2) can be prepared by adopting 2D carbon fiber cloth or silicon carbide fiber cloth or aluminum oxide fiber cloth.
4. A shaping die for an outer ring preform of a ceramic matrix composite turbine according to any one of claims 1 to 3, wherein: comprises an outer die, an inner die (33) and a positioning pin;
the outer mould tool comprises a first outer mould tool (31) and a second outer mould tool (32);
the inner surface (311) of the first outer die is a use molded surface, and the molded surface is matched with the outer surface of the omega-shaped cover plate; a sewing hole (7) is formed in the first outer die (31) and a positioning pin hole (8) is formed in a position where the molded surface is not used; during shaping, the positioning pins are fastened with a second outer die (32) and are bonded and pressed 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 use molded surface, and the molded surface is matched with the inner surface (111) of the arc-shaped plate prefabricated body; a sewing hole (7) is formed in the second outer die (32) and a positioning pin hole (8) is formed in a position where the molded surface is not used; during shaping, the positioning pin is fastened with the first outer die (31) and is bonded and pressed with the lower surface of the preform of the outer ring of the ceramic matrix composite turbine;
the outer surface of the inner die (33) is a use molded surface, and the surface is matched with the inner surface of the arc-shaped pipe section preform (12); the inner die (33) is provided with a sewing hole (7) and a positioning pin hole (8) at a position where the molded surface is not used; during shaping, the positioning pins are fastened with a second outer die (32) for shaping the arc-shaped pipe section prefabricated body (12).
5. The sizing die of claim 4, wherein: the novel die further comprises a reinforcing frame (5) and a wedge block (6), and the reinforcing frame (5) and the wedge block (6) are used for compressing and fixing the first outer die (31) and the second outer die (32).
6. The sizing die of claim 5, wherein: positioning structures (322) are arranged at two ends of the second outer die (32), the positioning structures (322) comprise grooves (3221) formed in two ends of the upper surface (321) of the second outer die, and the grooves (3221) extend along the axial direction of the second outer die (32); a boss (3222) is arranged on the outer side groove wall of the groove (3221), a limiting groove (3223) is formed in the boss, and the boss is matched with two ends of the inner die (33) and used for limiting the inner die (33).
7. The sizing die of claim 6, wherein: the outer die, the inner die (33), the locating pins, the reinforcing frame (5) and the wedge blocks (6) can be prepared from electrode graphite or high-purity graphite.
8. A method of using the shaping mold for the outer ring preform of the ceramic matrix composite turbine in any one of claims 4 to 7, comprising the steps of:
step 1, fixing a second outer die (32) to an operation table;
step 2, paving 1 layer of 1K carbon cloth and carbon fiber cloth or silicon carbide fiber cloth or aluminum oxide fiber cloth with a set layer number in sequence from bottom to top on a second outer die (32) as an arc-shaped plate preform (11), and locally and simply sewing;
step 3, winding carbon fiber cloth or silicon carbide fiber cloth or aluminum oxide fiber cloth with a certain layer number on an inner die (33) as an arc-shaped pipe section preform (12), and carrying out local simple sewing through sewing holes (7) on the inner die (33);
step 4, assembling an inner die (33) and a second outer die (32), and installing and positioning through positioning pins;
step 5, laying a filler prefabricated body (2) at the position of an included angle between the arc-shaped plate prefabricated body (11) and the arc-shaped pipe section prefabricated body (12);
step 6, paving 1 layer of 1K carbon cloth and carbon fiber cloth or silicon carbide fiber cloth or aluminum oxide fiber cloth with set layers on a first outer die (31) in sequence to serve as an omega type cover plate prefabricated body (13), and carrying out local simple sewing through sewing holes (7) on the die;
step 7, mounting and fixing a first outer die (31) on a second outer die (32), and mounting and positioning through positioning pins, wherein an inner die (33) is positioned at the cavity (132) of the first outer die (31);
step 8, integrally sewing all the prefabricated bodies through sewing holes (7) on the die;
and 9, compacting 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 CN114483207A (en) | 2022-05-13 |
| CN114483207B true CN114483207B (en) | 2024-03-08 |
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| WO (1) | WO2023123861A1 (en) |
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| CN114483207B (en) * | 2021-12-29 | 2024-03-08 | 西安鑫垚陶瓷复合材料股份有限公司 | Ceramic matrix composite turbine outer ring preform, shaping die and using method thereof |
| 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 |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102933757A (en) * | 2010-03-02 | 2013-02-13 | 斯奈克玛 | Fibrous preform for turbine ring sector and method for manufacturing same |
| CN103796818A (en) * | 2011-09-07 | 2014-05-14 | 斯奈克玛 | Method for manufacturing a sector of a turbine nozzle or compressor stator vane made of a composite material for a turbine engine, and turbine or compressor including a nozzle or stator vane consisting of said sectors |
| CN112267917A (en) * | 2020-09-18 | 2021-01-26 | 中国航发四川燃气涡轮研究院 | Fiber preform and ceramic matrix composite turbine outer ring |
| CN113195873A (en) * | 2018-12-19 | 2021-07-30 | 赛峰航空器发动机 | Turbine ring assembly with indexing flange |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7335012B2 (en) * | 2004-12-22 | 2008-02-26 | General Electric Company | Apparatus for fabricating reinforced composite materials |
| US20090165945A1 (en) * | 2007-12-27 | 2009-07-02 | General Electric Company | Tool for use in the manufacture of turbine bucket shroud and related method |
| CN214395506U (en) * | 2020-12-17 | 2021-10-15 | 中航沈飞民用飞机有限责任公司 | Forming die for I-shaped parts made of composite materials |
| CN114483207B (en) * | 2021-12-29 | 2024-03-08 | 西安鑫垚陶瓷复合材料股份有限公司 | Ceramic matrix composite turbine outer ring preform, shaping die and using method thereof |
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- 2021-12-29 CN CN202111642776.XA patent/CN114483207B/en active Active
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- 2022-05-31 WO PCT/CN2022/096452 patent/WO2023123861A1/en unknown
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102933757A (en) * | 2010-03-02 | 2013-02-13 | 斯奈克玛 | Fibrous preform for turbine ring sector and method for manufacturing same |
| CN103796818A (en) * | 2011-09-07 | 2014-05-14 | 斯奈克玛 | Method for manufacturing a sector of a turbine nozzle or compressor stator vane made of a composite material for a turbine engine, and turbine or compressor including a nozzle or stator vane consisting of said sectors |
| CN113195873A (en) * | 2018-12-19 | 2021-07-30 | 赛峰航空器发动机 | Turbine ring assembly with indexing flange |
| CN112267917A (en) * | 2020-09-18 | 2021-01-26 | 中国航发四川燃气涡轮研究院 | Fiber preform and ceramic matrix composite turbine outer ring |
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| CN114483207A (en) | 2022-05-13 |
| WO2023123861A1 (en) | 2023-07-06 |
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