CN-119871935-B - Silicon carbide fiber turbine rotor blade preform and preparation method thereof

CN119871935BCN 119871935 BCN119871935 BCN 119871935BCN-119871935-B

Abstract

The invention discloses a silicon carbide fiber turbine rotor blade preform and a preparation method thereof, belonging to the field of material science and engineering. The method comprises the steps of adopting the low-buckling silicon carbide fiber cloth to prepare, dividing the turbine rotor blade into an inner core and an outer layer, adopting an integral layering forming method for the inner core and the outer layer, enabling a blade body and a tenon in the inner core to be integral, greatly improving the bearing capacity and stability of the blade, enabling the low-buckling silicon carbide fiber cloth to have lower buckling property and good in-plane performance, enabling yarns to be easier to deform and keeping the original mechanical performance of the fiber in the forming process of the blade, and enabling the blade formed by combining the satin silicon carbide fiber cloth and the integral layering to have better oxidation resistance, creep resistance, damage tolerance and energy absorption performance compared with the blade prepared by the traditional method.

Inventors

ZHANG DIANTANG
WANG YUSEN
WANG LING
XU HAO
SUN JIN

Assignees

江南大学

Dates

Publication Date: 20260508
Application Date: 20250103

Claims (6)

1. A method of preparing a silicon carbide fiber turbine rotor blade preform, the method comprising: measuring a turbine rotor blade model, and counting parameters of the blade; step2, selecting a silicon carbide fiber cloth and a layering structure; Step 3, designing an inner core layer of a turbine rotor blade prefabricated body; step 4, outer layer unfolding and layering design of the turbine rotor blade preform; Step 5, cutting the silicon carbide fiber cloth according to the layering design of the step 3 and the step 4; step 6, performing overall layering according to the layering designs in the step 3 and the step 4, sewing the outer layers after layering, and twisting the blade body to obtain the turbine rotor blade; the step 2 comprises the following steps: The selected fiber cloth is low-buckling silicon carbide fiber cloth, the low-buckling silicon carbide fiber cloth is woven by wrapping yarns obtained by wrapping silicon carbide fiber bundles with aramid yarns, and the layering structure is a 2D integral layering mode of alternating layering along the height direction of the blade by 0/90 degrees; The step 3 comprises the following steps: s1, paving an inner core blade body of a turbine rotor blade preform: Designing structural parameters of a main fiber layer according to thickness distribution parameters of the blade body, and adopting a ply-descending method to realize uniform change of longitudinal and transverse thicknesses of the blade preform; s2, paving a tenon of a turbine rotor blade prefabricated body: The method comprises the steps of forming a main layer of a tenon part by fiber cloth extending out of a main fiber layer of a blade body, determining the number of initial warp layers and the number of columns according to the thickness and the width size of an equal-thickness area at the joint of a flange plate and the tenon, bending downwards to the dovetail neck, and expanding towards the bottom of the tenon at the same angle difference at two sides; In the step S2: all the intercalation layers between two adjacent main fiber layers are in a group, each group of intercalation adopts a ply-decreasing structure, each intercalation layer is named as 1,2,3, 4, 5 and n according to the descending order of the intercalation height, and the laying sequence is adjusted to be 1, 3, 5, 7 and n, n-1, n-3 and 6, 4 and 2, wherein the number 1 ply layer is close to one side of the outer surface; The main fiber layer with the thickness of 3mm at the tip part of the inner core of the blade body penetrates through the whole blade.
2. The method according to claim 1, wherein the step 4 comprises: Extracting the outer surface of the outer layer of the blade body, and flattening the outer surface to obtain the required shape and size parameters of the outer layer of the blade body, wherein the flattened outer layer can be approximately spliced into two trapezoids, so that the layering scheme is designed according to the trapezoids; The edge plate is formed by buckling and overlapping reserved part of fabrics on the outer layer of the blade body.
3. The method according to claim 2, wherein the step 1 comprises: The method comprises the steps of measuring the dimensions of a turbine rotor blade to obtain overall dimension parameters of a blade body, tenons and edge plates, wherein the height of the blade body is 120mm, and performing cross section analysis every 6mm to obtain thickness distribution parameters of cross sections under different blade body heights; the maximum thickness of the blade body is uniformly reduced from 12mm to 6mm, wherein the maximum thickness of the main fiber layer of the inner core blade body is uniformly reduced from 9mm to 3mm, the thickness of the outer layer of the blade body is 1.5mm, the circumference of the section of the maximum thickness is uniformly reduced from 151mm to 108mm, the length of the flange plate is 74mm, the width of the flange plate is 32mm, the thickness of the flange plate is 3mm, the length of the tenon is 50mm, the maximum width of the tenon is 15.5mm, the minimum width of the tenon is 6mm, and the height of the tenon is 13mm.
4. A method according to claim 3, wherein the length and width of the fabric of the outer reserved portion of the blade body are determined by the dimensions of the flattened outer surfaces of the flange plate and the tenon.
5. A silicon carbide fiber turbine rotor blade preform, characterized in that it is produced on the basis of the method according to any one of claims 1-4.
6. The preform of claim 5, wherein the preform is used in an aeroengine.

Description

Silicon carbide fiber turbine rotor blade preform and preparation method thereof Technical Field The invention relates to a prefabricated body of a silicon carbide fiber turbine rotor blade and a preparation method thereof, belonging to the fields of material science and engineering. Background Turbine rotor blades are a typical heat section component in an aeroengine, and by converting heat energy and pressure potential energy in high-temperature and high-pressure fuel gas into mechanical energy, the turbine rotor blades are subjected to extremely high temperature and huge centrifugal force caused by high-speed rotation during the operation of the aeroengine, and extremely high requirements are placed on heat resistance, light weight and bearing performance of the turbine rotor blades. The traditional mode adopts the nickel-based superalloy turbine blade, but the force-heat performance of the traditional nickel-based superalloy has reached the use limit, and can not meet the use requirements of high temperature resistance, high bearing capacity and light weight, while the silicon carbide fiber reinforced silicon carbide based composite material has the characteristics of low density, high specific strength, high temperature resistance, oxidation resistance, corrosion resistance and the like, and compared with the nickel-based superalloy, the nickel-based superalloy turbine blade has stronger temperature bearing capacity, lighter weight, lower thermal expansion coefficient, higher material anisotropy and higher designability and is an ideal material for preparing the turbine rotor blade of the advanced aeroengine. In the prior art, the turbine rotor silicon carbide fiber preform structure mainly comprises a 2D layering, 2.5D weaving and 3D weaving, and compared with the 2D layering preform, the silicon carbide fiber reinforced silicon carbide based composite material obtained by compounding the 2.5D and 3D weaving structure has insufficient in-plane tensile property, and the material performance can not be fully utilized under the action of huge centrifugal force caused by high-speed rotation of the turbine rotor. In order to solve the problems, chinese patent publication No. CN108897931A discloses a design method of a ceramic-based turbine rotor blade preform, and the preparation of the turbine rotor blade preform is realized by adopting a 2D layering method, but the layering method is to divide the whole blade into various modules for layering, and interlayer stitching is carried out at key parts, so that the interlayer strength is improved to a certain extent, but the whole performance of the blade is poor. In addition, the 2D silicon carbide fiber reinforced silicon carbide based composite material is generally prepared by mainly selecting silicon carbide fiber plain cloth, but the silicon carbide fiber has high modulus and poor weaving property, and plain weave interweaving points are more, the yarns are subjected to concentrated stress and larger friction force on the points, so that the yarns are damaged greatly, and the silicon carbide fiber has high price and can cause huge waste of cost. Meanwhile, as a complex thin-wall curved surface part, the prefabricated body of the silicon carbide fiber reinforced silicon carbide based composite material turbine rotor blade can generate torsional deformation in the manufacturing process, and yarn damage is increased. Disclosure of Invention In order to solve at least one of the problems, the application provides a silicon carbide fiber turbine rotor blade preform and a preparation method thereof, wherein a silicon carbide fiber bundle is used as a core layer, aramid yarns are wrapped on the outer layer of the silicon carbide fiber bundle to form wrapping yarns, and the yarns are used for weaving a low-buckling silicon carbide fiber fabric. The method comprises the steps of integrally layering a turbine rotor blade preform in a low-buckling silicon carbide fiber fabric 2D layering mode, and manufacturing the silicon carbide fiber turbine rotor blade preform into an inner core and an outer layer, wherein the inner core penetrates through the whole blade and comprises a blade body inner layer and a tenon inner layer. The outer layer is a whole piece of fabric covering the blade, and the edge plate is formed by buckling and overlapping the outer layer fabric. Compared with 2.5D and 3D woven preforms, the fiber preform of the 2D layering structure has stronger tensile strength and larger damage tolerance, and can meet the requirements of complex geometric shapes of different products, and the preform structure adopts a low-buckling fabric layering, so that compared with plain fabrics, the fiber preform of the 2D layering structure has fewer interweaving points, and the damage to yarns due to fiber buckling, stress concentration and friction can be effectively reduced. The aramid yarn has high strength and good wear resistance, and the silicon carbide fiber bundle