Additive manufacturing method of short fiber reinforced ceramic composite aircraft engine swirler

Abstract

The invention provides an additive manufacturing method of a short fiber reinforced ceramic composite aircraft engine swirler, which comprises the following manufacturing steps: performing interface preparation on the fiber surface to obtain composite powder, and mixing the powder with silicon carbide powder and resin to obtain mixed powder; carrying out selective laser sintering printing molding on the mixed powder to obtain a ceramic green body, and carrying out degreasing treatment to obtain an intermediate; performing two-step impregnation and cracking on the intermediate through a ceramic precursor and resin to obtain a preform 2, performing gas / liquid phase reaction sintering treatment on the preform 2 to obtain Cf / SiC ceramic, depositing silicon carbide on Cf / SiC through a chemical vapor infiltration method, and performing abrasive flow grinding and polishing to obtain a finished product. The short fiber reinforced silicon carbide powder precise printing forming swirler is achieved, fiber, silicon carbide and resin powder are subjected to composite granulation, fiber agglomeration is weakened, the powder density is increased, the cohesive force between carbon fibers is increased, and therefore the biscuit density is increased; and structure accurate forming and surface quality control of the swirler with the complex structure are facilitated.

Description

Technical Field

[0001] The present invention belongs to the technical field of manufacturing high-temperature components of aircraft engines, and in particular relates to an additive manufacturing method for a short fiber reinforced ceramic composite aircraft engine vortex finder. Background Art

[0002] Silicon carbide ceramics have excellent properties such as high temperature resistance, high strength and stiffness, relatively light weight, and corrosion resistance. However, their fatal weakness is brittleness. When under stress, they will crack or even break, leading to material failure. Using high-strength, high-elastic modulus fibers to composite with a matrix and using the fibers to prevent crack propagation is an effective way to improve the toughness and reliability of ceramics. Currently, the continuous fiber weaving-chemical vapor infiltration-subtractive precision machining process has successfully achieved the preparation of fiber-reinforced silicon carbide ceramic matrix composites for liquid rocket engine nozzles, missile antenna covers, space shuttle nose cones, aircraft brake discs, and high-end automobile brake discs. However, the manufacturing cycle is long, the processing is difficult, and the cost is high. Faced with the demand for rapid manufacturing of high-temperature vortex generators with precise and complex nested structures, the process has low applicability.

[0003] Additive manufacturing, or 3D printing, refers to the process of automatically building solid structures by adding materials using 3D model data. Essentially, 3D printing is a bottom-up manufacturing process that can build materials into structural entities of arbitrary geometric shapes, eliminating the multiple tools and steps required by traditional machining processes. This offers new opportunities for the fabrication of complex, nested, and high-temperature components. Selective laser sintering (SLS), a type of 3D printing, uses a high-energy laser beam to melt or solidify layers of material powder, building an object layer by layer. First, a thin layer of material powder is laid on a worktable. A computer-controlled system then guides the laser beam across the surface of the layer, following a predetermined contour. When the laser beam is focused on the material surface, the temperature in that localized area rises rapidly, causing the material to melt or solidify instantly. After printing a slice layer, the worktable descends a certain distance to cover a new layer of material, and the laser beam continues scanning, repeating the process. Through layer-by-layer sintering, the desired object is ultimately formed.

[0004] Vortex finders have a highly complex nested structure, are small in size, and have thin walls. Short fibers and nanoparticles in the powder easily agglomerate, resulting in uneven mixing with the binder. After bonding, the thin-walled green body has high porosity and low strength, making it difficult to support post-processing. Vortex finders typically have dozens of vanes evenly distributed within them. Aeroengine vortex finders require extremely high structural precision. Ceramic sintering easily deforms, resulting in inadequate pore penetration in the green body and difficulty increasing the overall material density. Reactive sintering easily damages fibers, reducing their content and weakening their toughening effects. Technical challenges for ceramic-based composite aeroengine vortex finders include incorporating high fiber content into the raw materials and controlling their shape and properties during printing and sintering.

[0005] The short fiber reinforced ceramic-based composite vortex finder manufactured using additive manufacturing technology has the characteristics of high toughness and vibration resistance, long-term oxidation resistance and high assembly precision. It is expected to replace high-temperature alloy vortex finders, increase the operating temperature, promote full mixing of oil and gas, optimize air intake, prevent surge, and improve engine combustion efficiency. Summary of the Invention

[0006] In view of the shortcomings of the existing technology, the purpose of the present invention is to provide an additive manufacturing method for short fiber reinforced silicon carbide aero-engine vortex finders, so as to solve the problems faced by the current additive manufacturing process of silicon carbide composites in the preparation of aero-engine vortex finders, such as easy agglomeration of composite powder fibers, low strength of the formed blanks, and easy deformation during densification sintering.

[0007] To achieve the above object, the present invention is implemented through the following technical solutions: A method for additive manufacturing of a short fiber reinforced ceramic composite aeroengine vortex finder, comprising the following steps: S1. Prepare the interface on the fiber surface by mixing short carbon fiber powder with nano-sized silicon carbide powder and a binder and spray granulating the mixture to obtain a composite granulated powder; the granulated powder is mixed with micron-sized silicon carbide powder and a resin to obtain a mixed powder suitable for selective laser sintering; S2. The mixed powder is printed by selective laser sintering (SLS) to obtain a ceramic body, which is then degreased to obtain an intermediate. S3. The first polymer impregnation pyrolysis process (PIP) is performed, wherein the intermediate is immersed in a ceramic precursor impregnation solution, impregnated and removed, and then pyrolyzed to obtain a preform 1; S4 secondary polymer impregnation cracking process (PIP) treatment, the preform 1 obtained in step S3 is placed in the resin impregnation solution and removed, dried and pyrolyzed to obtain a preform 2; S5. The preform 2 is placed in a crucible and subjected to gas / liquid phase reaction sintering (RMI) treatment to obtain the C f / SiC ceramics; S6. The C f / SiC ceramics are placed in a hot alkaline solution to corrode the residual silicon on the surface, then taken out, cleaned and dried. Silicon carbide is deposited on the surface of the material by chemical vapor infiltration (CVI), and the finished product is obtained after abrasive flow polishing.

[0008] Preferably, in step S1, the fibers comprise carbon fibers and / or silicon carbide fibers; the fiber surface interface comprises a gradient interface of one or more of pyrolytic carbon, silicon carbide, or boron nitride; the binder in the spray mixture comprises one or more of polyvinyl alcohol, polyurethane, or phenolic resin; and the resin blended with the granulation powder comprises one or more of epoxy resin, phenolic resin, and polyimide. Preferably, in step S1, the fibers are chopped and then pulverized, with the resulting fibers having a diameter of 1-20 μm and an average length of 50-500 μm.

[0009] Preferably, in the granulation slurry of step S1, the particle size of the nano-silicon carbide powder is in the range of 0.1-1 um, and the rest is short fibers and binder, and the mass ratio of the three is 1:0.1-0.5:0.1-0.5.

[0010] Preferably, the solid content of the spray mixture in step S1 is 10% to 70%, and the spray outlet temperature is 100 to 200°C.

[0011] Preferably, the binder content in the spray mixture in step S1 is 1% to 20%.

[0012] Preferably, the average particle size of the granulated powder screened in step S1 is 1-100 um.

[0013] Preferably, the particle size range of the micron-sized SiC powder in step S1 is 1-100 um.

[0014] Preferably, the ratio of the granulated powder, micron-sized silicon carbide powder and resin in step S1 is 1:0.1-0.5:0.1-0.5.

[0015] Preferably, in step S2, the powder is evenly spread on the printing platform and selective laser sintering is used for forming.

[0016] Preferably, the SLS printing parameters in step S2 are: laser power 5-20 W, scanning speed 1000-6000 mm / s, scanning spacing 0.05-0.2 mm, layer thickness 0.1-0.5 mm, and ambient temperature adjusted to 20-90°C.

[0017] Preferably, in step S2, the degreasing treatment conditions are: heating at a uniform speed or in stages under an inert protective atmosphere or in vacuum, and cooling after a certain holding time.

[0018] Preferably, the degreasing treatment conditions in step S2 are: in an inert protective atmosphere / vacuum, heating from room temperature to a certain temperature (300-600°C, depending on the resin) at a heating rate of 1-5°C / min, keeping warm for 1-5 hours, then heating to above 600-1200°C at a heating rate of 1-5°C / min, keeping warm for 1-5 hours, and cooling to room temperature with the furnace.

[0019] Preferably, in step S3, the ceramic precursor selected for the ceramic precursor impregnation liquid is one or more of polysiloxane, polymethylsilsesquioxane, polycarbosilane or polysilazane, and the number of impregnation and cracking is 1 or more, preferably 1 to 10 times; preferably, the mass ratio of the ceramic precursor to the solvent is 1:1 to 1:1.5.

[0020] Preferably, the drying treatment condition in step S3 is: drying at 50-350° C. for 1-2 h.

[0021] Preferably, the pyrolysis treatment conditions in step S3 are: in a protective atmosphere or vacuum, heating from room temperature to 1100-1300°C at a heating rate of 2°C / min, keeping the temperature for 2-3 hours, and then cooling to room temperature with the furnace.

[0022] Preferably, in step S4, the resin impregnation liquid for impregnating the preform 1 includes one or more of an epoxy resin solution, a phenolic resin solution, a polyimide solution or a furfural resin solution, the resin impregnation liquid is prepared by mixing a resin and anhydrous ethanol in a certain proportion, the impregnation and cracking times are 1 or more, preferably, the impregnation and cracking times are 1 to 10 times; preferably, the resin solution for impregnating the preform 1 (i.e., the resin impregnation liquid) is prepared by mixing a resin and anhydrous ethanol in a mass ratio of 1:0.5 to 1:2.

[0023] Preferably, the drying treatment condition in step S4 is: drying at 50-350° C. for 1-2 h.

[0024] Preferably, the pyrolysis treatment conditions in step S4 are to increase the temperature from room temperature to 800-1000°C at a heating rate of 2°C / min under a protective atmosphere or vacuum, keep the temperature for 1-3 hours, and then cool to room temperature with the furnace.

[0025] Preferably, in step S5, the RMI treatment condition of the preform 2 is vapor phase siliconization or liquid phase siliconization, and the silicon raw material is one or more of high-purity silicon powder, high-purity silicon block or silicon block after high-purity silicon powder is bonded.

[0026] Preferably, the siliconizing treatment conditions in step S5 are: first, heating from room temperature to above 1100°C at a heating rate of 1-10°C / min, keeping warm for 0.5-3 h, then heating to 1400-1700°C at a heating rate of 1-10°C / min, keeping warm for 0.5-3 h, then cooling to 1300°C at a rate of 1-5°C / min, and then cooling to room temperature with the furnace.

[0027] Preferably, in step S6, the hot alkaline solution is an inorganic alkaline aqueous solution, the inorganic alkaline includes potassium hydroxide and / or sodium hydroxide, and the deposition number of chemical vapor infiltration deposition of silicon carbide is 2 to 10.

[0028] Preferably, the hot alkaline solution in step S6 has a concentration in a supersaturated state (1 mol / L) and is boiled for 1 to 48 hours.

[0029] Preferably, the conditions for chemical vapor infiltration deposition of silicon carbide in step S6 are: SiCl4 as the silicon source, CH4 as the carbon source, H2 as the carrier gas, the deposition temperature is 1000-1500°C, the deposition pressure is 3-10 kPa, and the deposition time lasts for several days; the flow rate of the silicon source gas is 100-300 sccm, the flow rate of the hydrogen is 100-500 sccm, the carbon-silicon molar ratio of the reaction gas is 0.5-1.5; and the deposition is performed for 1-5 furnaces.

[0030] Preferably, the abrasive used in the abrasive flow polishing in step S6 is diamond or silicon carbide, the sand grain size is between 0.005 mm and 1.5 mm, the abrasive temperature is 30-500° C., the processing pressure range is between 2 MPa and 50 MPa, and the polishing time is 0.5-5 h.

[0031] The present invention also provides a short fiber reinforced ceramic-based composite aeroengine vortex finder prepared according to the above method.

[0032] Beneficial effects The method of the present invention is based on a selective laser sintering 3D printing method, utilizing fiber interface preparation, spray granulation powder production, laser selective sintering, polymer impregnation cracking, and reactive infiltration processes to produce aeroengine vortex finders. The advantages of the method of the present invention are: The precise printing and forming of vortex finders using short fiber reinforced silicon carbide powder has been achieved: short fibers and nano-silicon carbide powder are spray granulated and then compounded with silicon carbide powder and resin powder to weaken fiber agglomeration, increase powder density, and increase the bonding force between carbon fibers, thereby enhancing the density of the blank. The short fibers are spheroidized, further weakening the adverse effects on blank forming caused by differences in geometric characteristics between fibers and powder, such as poor dispersion effect, inability to flatten, and excessive burrs on the edges of the printed layer. This is beneficial to the precise structural forming and surface quality control of vortex finders with complex structures.

[0033] Double impregnation liquid impregnation cracking and surface dense silicon carbide layer treatment: by impregnating two impregnation liquids (ceramic precursor impregnation liquid and resin impregnation liquid) and performing gas / liquid phase silicon infiltration, the carbon content in the green body is increased and the internal fibers are further protected, preventing a large number of fibers from being eroded by silicon, thereby ensuring C f The density and toughness of the SiC composite are improved. After hot alkali etching of the residual silicon on the surface, a dense silicon carbide layer is deposited to strengthen the bonding strength of the deposited layer. Then, abrasive flow polishing is performed to make the inner and outer surfaces of the vortex finder uniform and dense silicon carbide.

[0034] In the present invention, C is prepared by selective laser sintering combined with polymer impregnation cracking, reactive sintering and chemical vapor infiltration. f / SiC vortex flow device, open porosity: 0.5%~3%; elastic modulus: 280~320 GPa; density: 2.75~2.95g / cm 3 ; Bending strength: 260~320 Mpa, preferably 300~320 Gpa; Material toughness ≥3.5 MPa / m 1 / 2 , the surface silicon carbide purity is >99%, and the deviation between the component size and the model is within 0.05 mm. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 This is a process flow chart of the additive manufacturing method of the ceramic-based composite aero-engine vortex finder of the present invention; Figure 2 It is a three-dimensional model diagram, actual diagram and structural contour precision scan diagram of the ceramic-based composite aero-engine eddy current generator. DETAILED DESCRIPTION

[0036] The embodiments described below with reference to the accompanying drawings are exemplary and are intended to explain the present invention, but should not be construed as limiting the present invention.

[0037] Example 1 S1. Nano-silicon carbide powder, phenolic resin, and surface-coated short carbon fiber powder were mixed in water at a mass ratio of 1:0.1:0.2, with a solids content of 25%. The mixture was spray-granulated at an outlet temperature of 110°C. The granulated powder was then blended with micron-sized silicon carbide powder and phenolic resin at a mass ratio of 1:0.1:0.1. S2. The mixed powder was printed by selective laser sintering (SLS) to obtain a vortex finder blank. The printing parameters were: laser power 7 W, scanning speed 3000 mm / s, scanning pitch 0.15 mm, layer thickness 0.1 mm, and contour optimization scanning mode. The blank was placed in a crucible and placed in a tube furnace. Under a nitrogen atmosphere, the temperature was increased from room temperature to 600°C at a rate of 2°C / min, held for 2 h, then increased to 1100°C at a rate of 2°C / min, held for 2 h, and then cooled to room temperature in the furnace to obtain an intermediate. S3. The intermediate was immersed in a polycarbosilane solution, first under vacuum for 1 hour and then under pressure for 1 hour. After removal, the sample was dried. The sample was placed in a tube furnace under a nitrogen atmosphere and heated from room temperature to 1200°C at a rate of 2°C / min. The temperature was maintained for 2.5 hours, and then the sample was cooled to room temperature in the furnace to obtain preform 1. S4. Preform 1 is then placed in a phenolic resin solution (phenolic resin and anhydrous ethanol in a mass ratio of 0.4:0.6). Vacuum impregnation is performed for 1 hour, followed by pressure impregnation for 1 hour. After removal, the sample is dried. The sample is placed in a tube furnace and heated from room temperature to 800°C at a rate of 2°C / min under a nitrogen atmosphere. The temperature is then maintained for 1 hour, followed by cooling to room temperature. This yields preform 2. S5. Place the preform 2 in a graphite crucible, spread a layer of silicon powder on the top and bottom of the preform, and place it in a siliconizing furnace. First, heat it from room temperature to 1100°C at a rate of 5°C / min, then heat it to 1420°C at a rate of 2°C / min, hold it for 0.5-1 h, then cool it to 1300°C at a rate of 1-3°C / min, and then cool it to room temperature. Take out the C f / SiC ceramics; S6. C f The SiC ceramic was placed in a supersaturated hot alkaline solution and boiled for 12 hours. The solution was then removed, cleaned, and dried. Two cycles of silicon carbide were deposited using chemical vapor infiltration. The deposition conditions were: a temperature of 1200°C, a pressure of 5 kPa, and a deposition time of 3 days. The silicon source gas flow rate was 100 sccm, the hydrogen flow rate was 300 sccm, and the carbon-silicon molar ratio of the reaction gas was 0.8. The silicon carbide was then polished using abrasive flow milling with a grit size of 0.005 mm for 1 hour to obtain the finished product.

[0038] Example 2 S1. Nano-silicon carbide powder, phenolic resin, and surface-coated short carbon fiber powder were mixed in water at a mass ratio of 1:0.1:0.5, with a solids content of 45%. The mixture was spray-granulated at an outlet temperature of 110°C. The granulated powder was then blended with micron-sized silicon carbide powder and epoxy resin at a ratio of 1:0.1:0.1. S2. The mixed powder was printed by selective laser sintering (SLS) to obtain a vortex flow device blank. The printing parameters were: laser power 7 W, scanning speed 3500 mm / s, scanning pitch 0.15 mm, layer thickness 0.1 mm, and contour optimization scanning mode. The blank was placed in a crucible and placed in a tube furnace. Under a nitrogen atmosphere, the temperature was increased from room temperature to 600°C at a rate of 2°C / min, held for 2 h, then increased to 1100°C at a rate of 2°C / min, held for 2 h, and then cooled to room temperature in the furnace to obtain an intermediate. S3. The intermediate was immersed in a polycarbosilane solution, first under vacuum for 1 hour and then under pressure for 1 hour. After removal, the sample was dried. The sample was placed in a tube furnace under a nitrogen atmosphere and heated from room temperature to 1200°C at a rate of 2°C / min. The temperature was maintained for 2.5 hours, and then the sample was cooled to room temperature in the furnace to obtain preform 1. S4. Preform 1 is then placed in a furfural resin solution (furfural resin and anhydrous ethanol in a mass ratio of 0.4:0.6). Vacuum impregnation is performed for 1 hour, followed by pressure impregnation for 1 hour. After removal, the sample is dried. The sample is placed in a tubular furnace and heated from room temperature to 800°C at a rate of 2°C / min under a nitrogen atmosphere. The temperature is maintained for 1 hour, followed by cooling to room temperature. This yields preform 2. S5. Place the preform 2 in a graphite crucible, spread a layer of silicon powder on the top and bottom of the preform, and place it in a siliconizing furnace. First, heat it from room temperature to 1100°C at a rate of 5°C / min, then heat it to 1420°C at a rate of 2°C / min, hold it for 0.5-1 h, then cool it to 1300°C at a rate of 1-3°C / min, and then cool it to room temperature. Take out the C f / SiC ceramics; S6. C f The SiC ceramic was placed in a supersaturated hot alkaline solution and boiled for 12 hours. The solution was then removed, cleaned, and dried. Two cycles of silicon carbide were deposited using chemical vapor infiltration. The deposition conditions were: a temperature of 1200°C, a pressure of 5 kPa, and a deposition time of 3 days. The silicon source gas flow rate was 100 sccm, the hydrogen flow rate was 300 sccm, and the carbon-silicon molar ratio of the reaction gas was 0.8. The silicon carbide was then polished using abrasive flow milling with a grit size of 0.005 mm for 1 hour to obtain the finished product.

[0039] Comparative Example 1 The preparation method is basically the same as that of Example 1, except that in step (1), no fiber and nano-silicon carbide granulation powder is used. Instead, micron-sized silicon carbide, phenolic resin, and short carbon fibers are directly mixed in a mass ratio of 1:0.1:0.1 to prepare the printing raw material.

[0040] The remaining steps are consistent with those in Example 1.

[0041] Comparative Example 2 The preparation method is basically the same as that of Example 1, except that the process of impregnating the intermediate with polycarbosilane impregnation solution in step (3) is omitted.

[0042] The remaining steps are consistent with those in Example 1.

[0043] Comparative Example 3 The method is basically the same as that in Example 1, except that the C in step (6) is omitted. f / The process of hot alkali treatment and deposition of silicon carbide on the surface of SiC ceramics is directly polished by abrasive flow.

[0044] The remaining steps are consistent with those in Example 1.

[0045] In order to more clearly demonstrate the beneficial effects of the method of the present invention, the material test results of the above examples and comparative examples are listed in Table 1: Table 1 shows the performance test results of the composite materials prepared in the examples and comparative examples.

[0046] As can be seen from the table above, comparing the material properties of the embodiments of the present invention and the comparative examples: the composite granulation of fiber and powder adds a protective layer to the fiber surface. The two-step impregnation and cracking process of the ceramic precursor and resin generates multiple layers of protection outside the blank, protecting the fiber from erosion during silicon infiltration, ensuring fiber content and fracture toughness, and increasing the residual carbon content within the blank. The material density after infiltration is relatively higher, and the bending strength is also improved. Before abrasive flow polishing, the residual silicon on the surface is corroded and chemically vapor deposited, further improving the elastic modulus. At the same time, the purity of the silicon carbide on the surface of the part is higher, and the silicon carbide deposited layer has a stronger bond with the part, which is beneficial for part assembly and service in extreme thermal environments.

[0047] The above-described embodiments merely illustrate the implementation methods of the present invention. While the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the patent. It should be noted that a person skilled in the art would be able to make various modifications and improvements without departing from the spirit of the present invention, all of which fall within the scope of protection of the present invention. Therefore, the scope of protection of the patent for this invention shall be determined by the appended claims.

Claims

1. A method for additive manufacturing of short fiber reinforced ceramic composite aeroengine vortex finders, characterized in that: The following steps are involved: S1. Prepare the interface on the fiber surface by mixing short carbon fiber powder with nano-sized silicon carbide powder and a binder and spray granulating the mixture to obtain a composite granulated powder; the granulated powder is mixed with micron-sized silicon carbide powder and a resin to obtain a mixed powder suitable for selective laser sintering; S2. The mixed powder is printed by selective laser sintering (SLS) to obtain a ceramic body, which is then degreased to obtain an intermediate. S3. The first polymer impregnation and cracking process PIP treatment, the intermediate is immersed in a ceramic precursor impregnation solution and removed, and then pyrolyzed to obtain a preform 1; S4 secondary polymer impregnation cracking process PIP treatment, the preform obtained in step S3 1 is placed in the resin impregnation solution and removed, dried and pyrolyzed to obtain a preform 2; S5. The preform 2 is placed in a crucible, subjected to gas / liquid phase reaction sintering RMI treatment to obtain the C f / SiC ceramics; S6. The C f / SiC ceramics are placed in a hot alkaline solution to corrode the residual silicon on the surface, then taken out, cleaned and dried. Silicon carbide is deposited on the surface of the material using the chemical vapor infiltration (CVI) method, and the finished product is obtained after abrasive flow polishing.

2. The additive manufacturing method for a short fiber reinforced ceramic composite aeroengine vortex finder according to claim 1, characterized in that: In step S1, the fibers include carbon fibers and / or silicon carbide fibers; the fiber surface interface includes a gradient interface of one or more components selected from pyrolytic carbon, silicon carbide, or boron nitride; the binder in the spray mixture includes one or more selected from polyvinyl alcohol, polyurethane, or phenolic resin; and the resin mixed with the granulated powder includes one or more selected from epoxy resin, phenolic resin, or polyimide.

3. The additive manufacturing method for a short fiber reinforced ceramic composite aeroengine vortex finder according to claim 1, characterized in that: In step S2, the powder is evenly spread on a printing platform and selective laser sintering is used for forming.

4. The additive manufacturing method for a short fiber reinforced ceramic composite aeroengine vortex finder according to claim 1, characterized in that: In step S2, the degreasing treatment conditions are: heating at a uniform speed or in stages under an inert protective atmosphere or in vacuum, and cooling after a certain holding time.

5. The additive manufacturing method for a short fiber reinforced ceramic composite aeroengine vortex finder according to claim 1, characterized in that: In step S3, the ceramic precursor selected from the ceramic precursor impregnation liquid is one or more of polysiloxane, polymethylsilsesquioxane, polycarbosilane or polysilazane, and the impregnation and cracking times are one or more times.

6. The additive manufacturing method for a short fiber reinforced ceramic composite aeroengine vortex finder according to claim 1, characterized in that: In step S4, the resin impregnation liquid used for impregnation of the preform 1 includes one or more of epoxy resin solution, phenolic resin solution, polyimide solution or furfural resin solution, and the resin impregnation liquid is prepared by mixing resin and anhydrous ethanol in a certain proportion, and the impregnation and cracking times are 1 or more.

7. The additive manufacturing method for a short fiber reinforced ceramic composite aeroengine vortex finder according to claim 1, characterized in that: In step S5, the RMI treatment conditions of the preform 2 are vapor phase siliconization or liquid phase siliconization, and the silicon raw material is one or more of high-purity silicon powder, high-purity silicon block or silicon block obtained by bonding high-purity silicon powder.

8. The additive manufacturing method for a short fiber reinforced ceramic composite aeroengine vortex finder according to claim 1, characterized in that: In step S6, the hot alkaline solution is an inorganic alkaline aqueous solution, the inorganic alkaline includes potassium hydroxide and / or sodium hydroxide, and the deposition number of chemical vapor infiltration deposition of silicon carbide is 2 to 10.

9. The additive manufacturing method for a short fiber reinforced ceramic composite aeroengine vortex finder according to claim 1, characterized in that: In step S6, the abrasive flow polishing is performed using diamond or silicon carbide as the abrasive material.

10. A short fiber reinforced ceramic-based composite aeroengine vortex finder manufactured according to the method of any one of claims 1 to 9.

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