Test Method for Transverse Properties of SiC Fiber Reinforced Titanium Matrix Composite Integral Bladed Rings

Abstract

The present invention relates to the field of performance testing of SiC fiber reinforced titanium matrix composite integral blisks, and specifically relates to a method for testing the transverse performance of SiC fiber reinforced titanium matrix composite integral blisks. This method uses a high-temperature transverse tensile specimen with a cruciform structure having the same curvature as the integral blisk structure, the same composite core cross-sectional dimensions, the same installation edge arc angle, and the same jacket thickness to test the high-temperature transverse tensile performance of the SiC fiber reinforced titanium matrix composite integral blisk, ensuring the consistency of the specimen and the integral blisk structural characteristics to the greatest extent, effectively avoiding the influence of surface fiber exposure edge effect and residual stress, and finally obtaining the accurate high-temperature transverse tensile performance of the SiC fiber reinforced titanium matrix composite integral blisk, avoiding fracture and failure due to not reaching the longitudinal performance design index of the integral blisk, and providing an effective analysis method for the performance optimization design of SiC fiber reinforced titanium matrix composite integral blisks.

Description

Technical Field

[0001] The present invention relates to the field of performance testing of SiC fiber reinforced titanium matrix (titanium alloy matrix) composite integral blisks, and specifically relates to a method for testing the transverse performance of SiC fiber reinforced titanium matrix composite integral blisks. Background Art

[0002] Compared with traditional titanium alloys, SiC fiber reinforced titanium matrix composites (SiC f / Ti) have higher specific strength and specific stiffness in the longitudinal direction (fiber direction), can withstand higher temperatures, and the suitable matrix types include TC4, TC17, TC25G, Ti60, Ti2AlNb, etc., almost covering the entire titanium alloy system. Because the mechanical properties of SiC fibers can remain unchanged at 800 °C, and with the increase of the test temperature, the strengthening effect becomes more obvious. They are widely used in unidirectionally reinforced parts in the fields of aerospace, etc. The most typical application is the integral blisk structure on aircraft engines. This annular structure mainly bears rotational loads. Winding the SiC fiber reinforced titanium matrix composite regularly inside its annular structure can make full use of the characteristics of unidirectional reinforcement of continuous SiC fiber reinforced titanium matrix composites, significantly improve its load-bearing capacity, and is more than 30% lighter than traditional titanium alloy blisks. However, structures such as integral blisks made of SiC fiber reinforced titanium matrix composites will inevitably be subjected to some transverse (perpendicular to the fiber direction) loads during service, causing radial delamination failure dominated by transverse loads in the SiC fiber reinforced titanium matrix composite integral blisk structure, resulting in the most advantageous longitudinal performance of the SiC fiber reinforced titanium matrix composite integral blisk structure not being fully exerted, not reaching the design index of the load-bearing capacity of the SiC fiber reinforced titanium matrix composite integral blisk, and causing the design failure of the SiC fiber reinforced titanium matrix composite integral blisk. Therefore, obtaining accurate transverse performance of SiC fiber reinforced titanium matrix composite integral blisks is crucial for their design and application.

[0003] The high-temperature (200 °C) transverse tensile property test of SiC fiber-reinforced titanium matrix composites is affected by factors such as the sample preparation process, service temperature, and the designability of the composite core and jacket. The test is difficult, and it is hard to determine a representative tensile specimen shape and performance. There is no unified tensile property test standard in China. Generally, thin plate-shaped tensile specimens are used, and it is unknown whether they are representative in the high-temperature transverse property test of the integral blisk. For the high-temperature transverse tensile property test of the SiC fiber-reinforced titanium matrix composite integral blisk, on the basis of the influencing factors of the high-temperature transverse tensile property test of the SiC fiber-reinforced titanium matrix composite, it is also affected by the problem that the residual stress in the preparation process of the large block structure is extremely likely to cause cracking of the composite core during the specimen processing, the integral blisk curvature, the arc angle of the installation edge, the position fixation of the composite core, and the exposure of the cross-section. In summary, it is more difficult to implement the high-temperature transverse tensile property test of the SiC fiber-reinforced titanium matrix composite integral blisk, and there is no relevant report on the high-temperature transverse tensile property test method of the SiC fiber-reinforced titanium matrix composite integral blisk at present. Summary of the Invention

[0004] In view of the problems existing in the prior art, the purpose of the present invention is to provide a method for testing the transverse properties of an SiC fiber-reinforced titanium matrix composite integral blisk. Using the method of the present invention, the high-temperature transverse properties of the SiC fiber-reinforced titanium matrix composite integral blisk can be effectively measured, and technical support is provided for the optimal design of the high-temperature transverse properties of the SiC fiber-reinforced titanium matrix composite integral blisk.

[0005] The technical solution of the present invention is as follows:

[0006] A method for testing the transverse properties of an SiC fiber-reinforced titanium matrix composite integral blisk, wherein the high-temperature transverse tensile specimen has the same geometric characteristics as the integral blisk, and the geometric characteristics are the cross-sectional size of the composite core, curvature, jacket thickness, and arc angle of the installation edge.

[0007] In the method for testing the transverse properties of the SiC fiber-reinforced titanium matrix composite integral blisk, the high-temperature transverse tensile specimen processes the large block structure according to the processing sequence.

[0008] In the method for testing the transverse properties of the SiC fiber-reinforced titanium matrix composite integral blisk, the high-temperature transverse tensile specimen is processed into a cruciform SiC fiber-reinforced titanium matrix composite integral blisk high-temperature transverse tensile specimen.

[0009] In the method for testing the transverse properties of the SiC fiber-reinforced titanium matrix composite integral blisk, before the tensile test, all surfaces of the high-temperature transverse tensile specimen are polished smoothly, and the exposed cross-section of the composite material is polished and corroded.

[0010] For the method for testing the transverse properties of the SiC fiber-reinforced titanium matrix composite integral blisk, a laser extensometer is used for the high-temperature transverse tensile specimen during high-temperature tensile testing.

[0011] For the method for testing the transverse properties of the SiC fiber-reinforced titanium matrix composite integral blisk, the high-temperature transverse tensile specimen is uniformly and continuously loaded during high-temperature tensile testing, and the loading rate is 1 mm / min.

[0012] For the method for testing the transverse properties of the SiC fiber-reinforced titanium matrix composite integral blisk, a cruciform high-temperature transverse tensile specimen with the same curvature as the integral blisk structure, the same composite core cross-sectional dimensions, the same installation edge arc angle, and the same cladding thickness is used to test the high-temperature transverse tensile properties of the SiC fiber-reinforced titanium matrix composite integral blisk.

[0013] The method for testing the transverse properties of the SiC fiber-reinforced titanium matrix composite integral blisk includes the following steps:

[0014] (1) Determine, in the structure of the measured SiC fiber-reinforced titanium matrix composite integral blisk, the composite core cross-sectional dimensions a×b, the inner diameter curvature ρ of the composite core, the cladding thickness t, the installation edge arc angle r1, the length l1 of the transverse property test specimen, the clamping end width w1, the height h, the hole diameter d at both ends, the clamping end width w2, the working section length l2, and the transition arc angle r2 between the transition section and the clamping end;

[0015] (2) Cut a transverse tensile sample from the large SiC fiber-reinforced titanium matrix composite structure with a curvature of ρ and composite core cross-sectional dimensions of a×b that has been prepared;

[0016] (3) The large SiC fiber-reinforced titanium matrix composite structure is subjected to the first wire cutting to remove the excess part on the upper surface;

[0017] (4) The pre-treated large SiC fiber-reinforced titanium matrix composite structure is subjected to the second wire cutting to remove the excess part on the lower surface;

[0018] (5) The pre-treated large SiC fiber-reinforced titanium matrix composite structure is subjected to the third wire cutting to remove the excess part in the length direction;

[0019] (6) The pre-treated large SiC fiber-reinforced titanium matrix composite structure is subjected to the fourth wire cutting to remove the excess part in the width direction, and a rectangular parallelepiped structure of the SiC fiber-reinforced titanium matrix composite integral blisk transverse tensile test specimen with a curvature of ρ, a length of l1, a width of w1, and a height of h is obtained;

[0020] (7) The cuboid structure of the SiC fiber-reinforced titanium matrix composite integral blisk transverse tensile test specimen after pre-treatment is subjected to the fifth and sixth wire cuttings. Sheaths are formed by symmetrically cutting grooves on both sides of the composite core to obtain a SiC fiber-reinforced titanium matrix composite integral blisk transverse tensile test specimen structure with a curvature of ρ, a length of l1, a width of w1, a height of h, a sheath thickness of t, a working section length of l2, and an installation edge arc angle of r1;

[0021] (8) The SiC fiber-reinforced titanium matrix composite integral blisk transverse tensile test specimen structure after pre-treatment is subjected to the seventh and eighth wire cuttings. Clamping holes are respectively opened at the two clamping ends of the transverse tensile specimen to obtain a SiC fiber-reinforced titanium matrix composite integral blisk transverse tensile test specimen structure with a curvature of ρ, a length of l1, a width of w1, a height of h, a sheath thickness of t, a working section length of l2, an installation edge arc angle of r1, and a hole diameter of d;

[0022] (9) The SiC fiber-reinforced titanium matrix composite integral blisk transverse tensile test specimen structure after pre-treatment is subjected to the ninth and tenth wire cuttings to make the widths of the two clamping ends of the transverse tensile specimen meet the requirements, and a cruciform SiC fiber-reinforced titanium matrix composite integral blisk transverse tensile test specimen with a curvature of ρ, a length of l1, a width of w1, a height of h, a sheath thickness of t, a working section length of l2, an installation edge arc angle of r1, a hole diameter of d, and a clamping end width of w2 is obtained;

[0023] (10) All surfaces of the cruciform SiC fiber-reinforced titanium matrix composite integral blisk transverse tensile test specimen after pre-treatment are polished;

[0024] (11) The exposed surfaces of the composite of the cruciform SiC fiber-reinforced titanium matrix composite integral blisk high-temperature transverse tensile test specimen after pre-treatment are polished;

[0025] (12) The cruciform SiC fiber-reinforced titanium matrix composite integral blisk high-temperature transverse tensile test specimen after pre-treatment is subjected to corrosion treatment;

[0026] (13) A transfer fixture is machined for the cruciform SiC fiber-reinforced titanium matrix composite integral blisk high-temperature transverse tensile test specimen. One end of the transfer fixture matches the opening diameters and positions at both ends of the transverse tensile test specimen, and the other end of the transfer fixture matches the chuck on the tensile testing machine;

[0027] (14) Fixing pins are machined for the cruciform SiC fiber-reinforced titanium matrix composite integral blisk high-temperature transverse tensile test specimen and the transfer fixture, and the diameter of the fixing pins is made to match the openings on the transverse tensile test specimen and the transfer fixture;

[0028] (15) Mount the cruciform SiC fiber reinforced titanium matrix composite integral blisk high-temperature transverse tensile test specimen on the tensile testing machine through an adapter fixture and a fixing pin.

[0029] (16) Install a high-temperature heating furnace so that the cross-section of the cruciform SiC fiber reinforced titanium matrix composite integral blisk high-temperature transverse tensile test specimen where the composite material is located is aligned with the reserved extensometer gap of the high-temperature heating furnace.

[0030] (17) Install a laser extensometer, and project two beams of laser of the laser extensometer onto the surface of the cruciform SiC fiber reinforced titanium matrix composite integral blisk high-temperature transverse tensile test specimen.

[0031] (18) Operate the tensile testing machine, apply uniform and continuous loading to the cruciform SiC fiber reinforced titanium matrix composite integral blisk high-temperature transverse tensile test specimen at a loading rate of 1 mm / min, and record the load value and the corresponding deformation value.

[0032] In the described transverse property testing method of the SiC fiber reinforced titanium matrix composite integral blisk, the transverse tensile test specimen includes a titanium alloy matrix and a composite material core. The titanium alloy matrix is an integral structure with transition sections and clamping ends symmetrically arranged at both ends of the working section in sequence. Both sides of the working section are symmetric groove structures, and the composite material core is located between the two symmetric groove structures. A clamping hole 1 is opened on each clamping end.

[0033] In the described transverse property testing method of the SiC fiber reinforced titanium matrix composite integral blisk, the transverse tensile test specimen adapter fixture includes a clamping groove, a clamping hole 2, and a connecting head. The specific structure is as follows: One end of the adapter fixture is provided with a clamping groove corresponding to and inserted and fitted with the clamping end of the transverse tensile specimen. The clamping hole 2 is vertically and oppositely penetrated through the clamping groove, and the clamping hole 2 corresponds to the clamping hole 1 of the clamping end of the transverse tensile specimen. The adapter fixture is connected and fixed to the clamping end of the transverse tensile specimen by passing a fixing pin through the clamping hole 2 and the clamping hole 1. A connecting head is provided at the other end of the adapter fixture, and the connecting head is a columnar structure with an external thread.

[0034] The design concept of the present invention is:

[0035] First, prepare a ring-shaped large block structure with the same size as the blank of the SiC fiber reinforced titanium matrix composite integral blisk by the same process to ensure that the residual stress before processing of the transverse tensile specimen, the curvature and size of the composite material core are the same as those of the integral blisk. Secondly, adjust the cutting sequence to avoid the problem of internal cracking of the composite material core during the cutting of the transverse tensile specimen caused by residual stress; Finally, keep the thickness of the sleeve outside the composite material core of the transverse tensile specimen and the size of the installation edge arc angle the same as those of the integral blisk.

[0036] The present invention has the following advantages and beneficial effects:

[0037] (1) The present invention effectively reduces the influence of residual stress caused during the preparation of a large-sized structure of a SiC fiber reinforced titanium matrix composite on the transverse tensile property test specimen.

[0038] (2) The present invention reduces the influence of the exposure of the composite core cross-section on the high-temperature transverse tensile property of the overall impeller ring of the SiC fiber reinforced titanium matrix composite.

[0039] (3) The present invention ensures the consistency of the characteristic dimensions such as the composite core cross-section size, curvature, cladding thickness, and installation edge arc angle between the transverse tensile specimen of the overall impeller ring of the SiC fiber reinforced titanium matrix composite and the overall impeller ring of the SiC fiber reinforced titanium matrix composite, effectively improving the accuracy of the test results. Description of the Drawings

[0040] Figure 1 is the cutting sequence diagram of a transverse tensile specimen obtained by cutting a section along the circumferential direction of the overall impeller ring of the SiC fiber reinforced titanium matrix composite of the present invention; in the figure, the reference numerals: 1, titanium alloy matrix; 2, composite core, and the composite core 2 penetrates through the overall impeller ring in a ring shape along the circumferential direction, and R represents the inner diameter of the overall impeller ring.

[0041] Figures 2(a)-2(c) is the transverse tensile specimen diagram of the overall impeller ring of the SiC fiber reinforced titanium matrix composite of the present invention. Fig. 2(a) is the front view, Fig. 2(b) is the top view, and Fig. 2(c) is the three-dimensional view; in the figure, the reference numerals: 1, titanium alloy matrix; 11, working section; 12, clamping end; 13, first clamping hole; 14, transition section; 2, composite core.

[0042] Figures 3(a)-3(c) is the adapter fixture diagram of the transverse tensile test specimen of the overall impeller ring of the SiC fiber reinforced titanium matrix composite of the present invention. Fig. 3(a) is the front view, Fig. 3(b) is the side view, and Fig. 3(c) is the three-dimensional view; in the figure, the reference numerals: 3, adapter fixture; 31, clamping groove; 32, second clamping hole; 33, connecting head. Detailed Embodiments

[0043] In the specific implementation process, the method for testing the transverse property of the overall impeller ring of the SiC fiber reinforced titanium matrix composite of the present invention uses a cruciform high-temperature transverse tensile specimen with the same curvature, the same composite core cross-section size, the same installation edge arc angle, and the same cladding thickness as the overall impeller ring structure to test the high-temperature transverse tensile property of the overall impeller ring of the SiC fiber reinforced titanium matrix composite.

[0044] Among them, the same curvature means that the inner and outer diameter curvatures of the composite material core of the high-temperature transverse tensile specimen of the present invention are the same as those of the inner and outer diameters of the composite material core of the integral blade ring; the same installation edge arc angle means that the installation edge arc angle at r1 is the same. The installation edge arc angle is the arc of the connection part between the installation edge structure of the integral blade ring jacket and the composite material core of the blade ring body (because it will generate a radial force during the rotation of the blade ring, so special attention needs to be paid to keeping it consistent). The same jacket thickness means that the jacket thickness t on the upper and lower surfaces of the composite material core is the same.

[0045] Next, the present invention will be further described through embodiments in conjunction with the accompanying drawings.

[0046] Embodiment

[0047] As Figure 1 、 Figures 2(a)-2(c) 、 Figures 3(a)-3(c) shown, the method for testing the transverse performance of the integral blade ring of the SiC fiber-reinforced titanium matrix composite material of the present invention includes the following steps:

[0048] (1) Determine the cross-sectional dimensions a×b of the composite material core, the inner diameter curvature ρ of the composite material core, the jacket thickness t, the installation edge arc angle r1, the length l1 of the transverse performance test specimen, the clamping end width w1, the height h, the opening diameter d at both ends, the clamping end width w2, the working section length l2, and the transition arc angle r2 between the transition section 14 and the clamping end 12 in the structure of the integral blade ring of the SiC fiber-reinforced titanium matrix composite material to be measured;

[0049] In this embodiment, a = 11 mm, b = 43 mm, the inner diameter curvature ρ of the composite material core = 1 / 131, the jacket thickness t = 1.5 mm, the installation edge arc angle r1 = 4 mm, the opening diameter d at both ends = 13 mm, the length l1 of the transverse performance test specimen = 97.2 mm, the height h = 25 mm, the clamping end width w1 = 8 mm, the width w2 = 25 mm, the working section length l2 = 32 mm, and the transition arc angle r2 = 3.5 mm.

[0050] Among them, the composite material composition of the composite material core 2 is: SiC fibers and TC17 titanium alloy matrix, and the volume of the SiC fiber reinforcement phase accounts for 50%.

[0051] (2) Cut a transverse tensile sample on the large-sized structure of the SiC fiber-reinforced titanium matrix composite material with a curvature of ρ and a cross-sectional dimension of a×b of the composite material core, as shown in Figure 1 ;

[0052] (3) The large-sized structure of the SiC fiber-reinforced titanium matrix composite material is subjected to the first wire cutting to remove the redundant part on the upper surface, as shown in Figure 1 ① in;

[0053] (4) The pre-treated large-sized SiC fiber reinforced titanium matrix composite structure is subjected to a second wire cutting to remove the excess part on the lower surface, as shown in Figure 1 ② in

[0054] (5) The pre-treated large-sized SiC fiber reinforced titanium matrix composite structure is subjected to a third wire cutting to remove the excess part in the length direction, as shown in Figure 1 ③ in

[0055] (6) The pre-treated large-sized SiC fiber reinforced titanium matrix composite structure is subjected to a fourth wire cutting to remove the excess part in the width direction, obtaining a cuboid structure of the SiC fiber reinforced titanium matrix composite integral vane ring transverse tensile test specimen with a curvature of ρ, a length of l1, a width of w1, and a height of h, as shown in Figure 1 ④ in

[0056] (7) The cuboid structure of the pre-treated SiC fiber reinforced titanium matrix composite integral vane ring transverse tensile test specimen is subjected to a fifth and sixth wire cutting to form a jacket by symmetrically cutting grooves on both sides of the composite core, obtaining a SiC fiber reinforced titanium matrix composite integral vane ring transverse tensile test specimen structure with a curvature of ρ, a length of l1, a width of w1, a height of h, a jacket thickness of t, a working section length of l2, and a mounting edge arc angle of r1, as shown in Figure 1 ⑤ and ⑥ in

[0057] (8) The structure of the pre-treated SiC fiber reinforced titanium matrix composite integral vane ring transverse tensile test specimen is subjected to a seventh and eighth wire cutting to respectively open clamping holes at the two clamping ends of the transverse tensile specimen, obtaining a SiC fiber reinforced titanium matrix composite integral vane ring transverse tensile test specimen structure with a curvature of ρ, a length of l1, a width of w1, a height of h, a jacket thickness of t, a working section length of l2, a mounting edge arc angle of r1, and a hole diameter of d, as shown in Figure 1 ⑦ and ⑧ in

[0058] (9) The structure of the pre-treated SiC fiber reinforced titanium matrix composite integral vane ring transverse tensile test specimen is subjected to a ninth and tenth wire cutting to make the widths of the two clamping ends of the transverse tensile specimen meet the requirements, obtaining a cruciform SiC fiber reinforced titanium matrix composite integral vane ring transverse tensile test specimen with a curvature of ρ, a length of l1, a width of w1, a height of h, a jacket thickness of t, a working section length of l2, a mounting edge arc angle of r1, a hole diameter of d, and a clamping end width of w2, as shown in Figure 1 ⑨ and ⑩ in

[0059] (10) All surfaces of the pre-treated cruciform SiC fiber reinforced titanium matrix composite integral vane ring transverse tensile test specimen are polished to ensure that all surfaces are smooth and there is no large stress concentration.

[0060] (11) The exposed surface of the cross-shaped SiC fiber-reinforced titanium matrix composite integral impeller high-temperature transverse tensile test specimen after pretreatment is polished;

[0061] (12) The cross-shaped SiC fiber-reinforced titanium matrix composite integral impeller high-temperature transverse tensile test specimen after pretreatment is corroded;

[0062] As Figures 2(a)-2(c) shown, the transverse tensile test specimen includes a titanium alloy matrix 1 and a composite core 2. The titanium alloy matrix 1 is an integral structure with transition sections 14 and clamping ends 12 symmetrically arranged at both ends of the working section 11 in sequence. The two sides of the working section 11 are symmetric groove structures. The composite core 2 is located between the two symmetric groove structures. A clamping hole one 13 is opened on each clamping end 12.

[0063] (13) A transfer fixture 3 is machined for the cross-shaped SiC fiber-reinforced titanium matrix composite integral impeller high-temperature transverse tensile test specimen. One end of the transfer fixture 3 matches the opening diameters and positions at both ends of the transverse tensile test specimen, and the other end of the transfer fixture 3 matches the chuck on the tensile testing machine;

[0064] (14) Fixing pins are machined for the cross-shaped SiC fiber-reinforced titanium matrix composite integral impeller high-temperature transverse tensile test specimen and the transfer fixture. The diameter of the fixing pins is made to match the openings on the transverse tensile test specimen and the transfer fixture;

[0065] (15) The cross-shaped SiC fiber-reinforced titanium matrix composite integral impeller high-temperature transverse tensile test specimen is clamped on the tensile testing machine through the transfer fixture and the fixing pins;

[0066] As Figures 3(a)-3(c) shown, the transfer fixture 3 of the transverse tensile test specimen includes a clamping groove 31, a clamping hole two 32, and a connecting head 33. The specific structure is as follows: A clamping groove 31 corresponding to and inserted and fitted with the clamping end 12 of the transverse tensile specimen is opened at one end of the transfer fixture 3. Clamping holes two 32 are vertically and oppositely opened through the clamping groove 31. The clamping holes two 32 correspond to the clamping hole one 13 of the clamping end 12 of the transverse tensile specimen. The transfer fixture 3 is connected and fixed to the clamping end 12 of the transverse tensile specimen by passing a fixing pin through the clamping hole two 32 and the clamping hole one 13. A connecting head 33 is provided at the other end of the transfer fixture 3. The connecting head 33 is a columnar structure with an external thread.

[0067] (16) A high-temperature heating furnace is installed so that the cross-section where the composite material of the cross-shaped SiC fiber-reinforced titanium matrix composite integral impeller high-temperature transverse tensile test specimen is located faces the reserved extensometer gap of the high-temperature heating furnace.

[0068] (17) Install a laser extensometer, project two beams of laser of the laser extensometer onto the surface of the composite material of the cruciform SiC fiber reinforced titanium matrix composite integral blisk high-temperature transverse tensile test specimen, and control the temperature of the transverse tensile test specimen to be 200 °C.

[0069] (18) Operate the tensile testing machine, apply uniform and continuous loading to the cruciform SiC fiber reinforced titanium matrix composite integral blisk high-temperature transverse tensile test specimen, with a loading rate of 1 mm / min, and record the load value and the corresponding deformation value.

[0070] The results of the examples show that the present invention maximally ensures the consistency of the structural characteristics of the specimen and the integral blisk, effectively avoids the influence of the fiber exposed edge effect and residual stress on the surface of the sample, and finally obtains the accurate high-temperature transverse tensile properties of the cruciform SiC fiber reinforced titanium matrix composite integral blisk, avoiding fracture and failure due to not reaching the longitudinal performance design index of the integral blisk, and providing an effective analysis method for the performance optimization design of the cruciform SiC fiber reinforced titanium matrix composite integral blisk.

Claims

1. A testing method for the transverse properties of an integrally bladed ring made of SiC fiber reinforced titanium matrix composite, characterized in that, The high-temperature transverse tensile specimen has the same geometric features as the integral blisk, and the geometric features are the cross-sectional size, curvature, sheath thickness, and installation edge arc angle of the composite core; The method for testing the transverse properties of the SiC fiber-reinforced titanium matrix composite integral blisk includes the following steps: (1) Determine the cross-sectional size a×b of the composite core, the inner diameter curvature ρ of the composite core, the sheath thickness t, the installation edge arc angle r1, the length l1 of the transverse property test specimen, the clamping end width w1, the height h, the hole diameter d at both ends, the clamping end width w2, the working section length l2, and the transition arc angle r2 between the transition section and the clamping end in the structure of the SiC fiber-reinforced titanium matrix composite integral blisk to be measured; (2) Cut a transverse tensile sample from the large SiC fiber-reinforced titanium matrix composite structure with a curvature of ρ and a composite core cross-sectional size of a×b that has been prepared; (3) The large SiC fiber-reinforced titanium matrix composite structure is subjected to the first wire cutting to remove the excess part on the upper surface; (4) The pre-treated large SiC fiber-reinforced titanium matrix composite structure is subjected to the second wire cutting to remove the excess part on the lower surface; (5) The pre-treated large SiC fiber-reinforced titanium matrix composite structure is subjected to the third wire cutting to remove the excess part in the length direction; (6) The pre-treated large SiC fiber-reinforced titanium matrix composite structure is subjected to the fourth wire cutting to remove the excess part in the width direction, and a cuboid structure of the SiC fiber-reinforced titanium matrix composite integral blisk transverse tensile test specimen with a curvature of ρ, a length of l1, a width of w1, and a height of h is obtained; (7) The cuboid structure of the pre-treated SiC fiber-reinforced titanium matrix composite integral blisk transverse tensile test specimen is subjected to the fifth and sixth wire cuttings, and sheaths are formed by symmetrically cutting grooves on both sides of the composite core, and a SiC fiber-reinforced titanium matrix composite integral blisk transverse tensile test specimen structure with a curvature of ρ, a length of l1, a width of w1, a height of h, a sheath thickness of t, a working section length of l2, and an installation edge arc angle of r1 is obtained; (8) The pre-treated SiC fiber-reinforced titanium matrix composite integral blisk transverse tensile test specimen structure is subjected to the seventh and eighth wire cuttings, and clamping holes are respectively opened at the two clamping ends of the transverse tensile specimen, and a SiC fiber-reinforced titanium matrix composite integral blisk transverse tensile test specimen structure with a curvature of ρ, a length of l1, a width of w1, a height of h, a sheath thickness of t, a working section length of l2, an installation edge arc angle of r1, and a hole diameter of d is obtained; (9) The pre-treated SiC fiber-reinforced titanium matrix composite integral blisk transverse tensile test specimen structure is subjected to the ninth and tenth wire cuttings to make the widths of the two clamping ends of the transverse tensile specimen meet the requirements, and a cruciform SiC fiber-reinforced titanium matrix composite integral blisk transverse tensile test specimen with a curvature of ρ, a length of l1, a width of w1, a height of h, a sheath thickness of t, a working section length of l2, an installation edge arc angle of r1, a hole diameter of d, and a clamping end width of w2 is obtained; (10) Grind the surfaces of the cross-shaped SiC fiber reinforced titanium matrix composite integral blisk transverse tensile test specimen after pretreatment. (11) Polish the exposed surface of the cross-shaped SiC fiber reinforced titanium matrix composite integral blisk high-temperature transverse tensile test specimen after pretreatment. (12) Corrode the cross-shaped SiC fiber reinforced titanium matrix composite integral blisk high-temperature transverse tensile test specimen after pretreatment. (13) Machine a transfer fixture for the cross-shaped SiC fiber reinforced titanium matrix composite integral blisk high-temperature transverse tensile test specimen. One end of the transfer fixture matches the opening diameters and positions at both ends of the transverse tensile test specimen, and the other end of the transfer fixture matches the chuck on the tensile testing machine. (14) Machine fixing pins for the cross-shaped SiC fiber reinforced titanium matrix composite integral blisk high-temperature transverse tensile test specimen and the transfer fixture. The diameter of the fixing pin is made to match the openings on the transverse tensile test specimen and the transfer fixture. (15) Mount the cross-shaped SiC fiber reinforced titanium matrix composite integral blisk high-temperature transverse tensile test specimen on the tensile testing machine through the transfer fixture and the fixing pins. (16) Install a high-temperature heating furnace so that the cross-section where the composite material of the cross-shaped SiC fiber reinforced titanium matrix composite integral blisk high-temperature transverse tensile test specimen is located is directly opposite the reserved extensometer gap of the high-temperature heating furnace. (17) Install a laser extensometer, and project two beams of laser of the laser extensometer onto the surface of the composite material of the cross-shaped SiC fiber reinforced titanium matrix composite integral blisk high-temperature transverse tensile test specimen. (18) Operate the tensile testing machine, apply uniform and continuous loading to the cross-shaped SiC fiber reinforced titanium matrix composite integral blisk high-temperature transverse tensile test specimen at a loading rate of 1 mm / min, and record the load value and the corresponding deformation value.

2. The method for testing the transverse properties of the SiC fiber reinforced titanium matrix composite integral blisk according to claim 1, wherein Machine the large block structure of the high-temperature transverse tensile specimen in the processing order.

3. The method for testing the transverse properties of the SiC fiber reinforced titanium matrix composite integral blisk according to claim 2, wherein Machine the high-temperature transverse tensile specimen into a cross-shaped SiC fiber reinforced titanium matrix composite integral blisk high-temperature transverse tensile specimen.

4. The method for testing the transverse properties of the SiC fiber reinforced titanium matrix composite integral impeller ring according to claim 3, characterized in that, Before the tensile test, grind all the surfaces of the high-temperature transverse tensile specimen smoothly, and polish and corrode the exposed cross-section of the composite material.

5. The test method for the transverse properties of the SiC fiber reinforced titanium matrix composite integral blisk according to claim 4, wherein Adopt a laser extensometer during the high-temperature tensile test of the high-temperature transverse tensile specimen.

6. The method for testing the transverse properties of the SiC fiber reinforced titanium matrix composite integral blisk according to claim 5, characterized in that, Apply uniform and continuous loading during the high-temperature tensile test of the high-temperature transverse tensile specimen at a loading rate of 1 mm / min.

7. The method for testing the transverse properties of the SiC fiber reinforced titanium matrix composite integral blisk according to claim 1, wherein This method uses a cross-shaped structure high-temperature transverse tensile specimen with the same curvature, the same composite material core cross-section size, the same installation edge arc angle, and the same cladding thickness as the integral blisk structure to test the high-temperature transverse tensile performance of the SiC fiber reinforced titanium matrix composite integral blisk.

8. The method for testing the transverse properties of the SiC fiber reinforced titanium matrix composite integral impeller ring according to claim 1, characterized in that, The transverse tensile test specimen includes a titanium alloy matrix and a composite material core. The titanium alloy matrix is an integral structure with transition sections and clamping ends symmetrically arranged at both ends of the working section in sequence. Both sides of the working section are symmetric groove structures. The composite material core is located between the two symmetric groove structures, and a clamping hole 1 is opened on each clamping end.

9. The method for testing the transverse properties of the SiC fiber reinforced titanium matrix composite integral impeller ring according to claim 1, characterized in that, The transverse tensile test sample adapter fixture includes a clamping groove, a second clamping hole, and a connector. The specific structure is as follows: One end of the adapter fixture is provided with a clamping groove corresponding to the clamping end of the transverse tensile sample and inserted and fitted therewith. The second clamping holes are vertically and oppositely penetrated through the clamping groove. The second clamping holes correspond to the first clamping holes at the clamping end of the transverse tensile sample. The adapter fixture is connected and fixed to the clamping end of the transverse tensile sample by fixing pins passing through the second clamping holes and the first clamping holes. A connector is provided at the other end of the adapter fixture. The connector is a columnar structure with an external thread.

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