CN113909613A

CN113909613A - A kind of brazing method of SiCf/SiC ceramic matrix composite material and nickel-based superalloy

Info

Publication number: CN113909613A
Application number: CN202111307735.5A
Authority: CN
Inventors: 郭伟; 张瑜; 张宏强
Original assignee: Beihang University; Shenyang Aerospace University
Current assignee: Beihang University; Shenyang Aerospace University
Priority date: 2021-11-05
Filing date: 2021-11-05
Publication date: 2022-01-11

Abstract

The invention discloses a method for brazing SiC _f /SiC ceramic-based composite material and nickel-based superalloy, which specifically includes: pretreatment of nickel-based superalloy, brazing material foil, ceramic-based composite material and foam copper; Pretreated nickel-based superalloys, pretreated brazing filler metal foils, pretreated ceramic matrix composites, and pretreated foamed copper are obtained; The material foil and the pretreated SiC _f /SiC ceramic matrix composite material are stacked in sequence and then brazed to obtain the brazing material of the SiC _f /SiC ceramic matrix composite material and the nickel-based superalloy. The method disclosed in the invention significantly improves the mechanical properties of the brazed joint, so that the brazing material of the SiC _f /SiC ceramic matrix composite material with excellent performance and the nickel-based superalloy can be obtained.

Description

SiCf/Method for brazing SiC ceramic matrix composite and nickel-based superalloy

Technical Field

The present invention relates to SiC_fThe technical field of the/SiC ceramic matrix composite material, in particular to SiC ceramic matrix composite material_fA method for brazing the/SiC ceramic matrix composite material and the nickel-based superalloy.

Background

SiC_fThe SiC ceramic matrix composite is a novel material obtained by compounding SiC fibers and a SiC matrix through a special process means, has the outstanding characteristics of high temperature resistance, high strength, corrosion resistance, wear resistance and the like, and is widely applied to important industrial fields of aerospace, nuclear energy, electronics and the like. The composite addition of the silicon carbide fiber overcomes the defects of poor bending resistance and fracture toughness of the ceramic to a certain extent; and the silicon carbide fiber has better oxidation resistance and better compatibility with a silicon carbide matrix, so that the SiC_fthe/SiC ceramic matrix composite material still keeps good oxidation resistance even in high-temperature oxidizing atmosphere.

To realize SiC_fThe reliable connection of the two high-temperature materials of the SiC ceramic matrix composite material and the nickel-based high-temperature alloy, and the obtained welding joint with certain high-temperature strength is beneficial to obtaining a complex structural member with excellent performances of the SiC ceramic matrix composite material and the nickel-based high-temperature alloy, thereby widening the range of SiC ceramic matrix composite materials_fThe application range of the/SiC ceramic matrix composite material has wide application prospect and profound research significance. In the prior art, brazing has the advantages of small deformation, high reliability and the like, and is the most common method for connecting ceramics and metals.

However, the physical properties of the ceramic matrix composite are greatly different from those of the nickel-based superalloy, and the ceramic has special properties, so that the ceramic matrix composite is difficult to be connected with metal or the ceramic matrix composite. The difference in physical properties is mainly due to SiC_fThe thermal expansion coefficient and the elastic modulus of the/SiC ceramic matrix composite material are greatly different from those of the nickel-based GH536, and the linear expansion coefficient of the nickel-based GH536 is increased along with the increase of the temperature, so that the deformation degree of the/SiC ceramic matrix composite material and the deformation degree of the nickel-based GH536 in the welding heat cycle are increased to a non-matching degree, and a large residual stress exists at a joint, and the joint has a serious damage effect on the mechanical property of the joint. Thus, improving the weld product and distribution thereof, and reducing the residual stress of the joint, is to improve SiC_fThe brazing performance of the/SiC ceramic matrix composite and the nickel-based high-temperature alloy is critical.

Thus, a novel SiC is provided_fThe method for brazing the/SiC ceramic matrix composite and the nickel-based superalloy is a problem which needs to be solved by the technical personnel in the field.

Disclosure of Invention

In view of the above, the present invention provides a SiC_fIn the method for brazing the/SiC ceramic matrix composite and the nickel-based high-temperature alloy, the foamy copper is added as the middle layer in various methods for relieving the residual stress of the joint, so that the problem can be effectively solved, and Si-C is avoided_fThe continuous brittle compound reaction layer is generated in the process of brazing the/SiC ceramic matrix composite material, and meanwhile, the SiC can be avoided_fThe problem of larger joint residual stress caused by large difference of thermal expansion coefficients of the SiC ceramic matrix composite and the nickel-based superalloy.

In order to achieve the purpose, the invention adopts the following technical scheme:

SiC_fThe method for brazing the/SiC ceramic matrix composite and the nickel-based superalloy specifically comprises the following steps:

(1) polishing the nickel-based high-temperature alloy and the brazing filler metal foil, and then adding the nickel-based high-temperature alloy and the brazing filler metal foil into acetone for ultrasonic pretreatment to obtain a pretreated nickel-based high-temperature alloy and a pretreated brazing filler metal foil;

(2) polishing the ceramic matrix composite material, adding the polished ceramic matrix composite material into acetone, and performing ultrasonic pretreatment 1 to obtain a pretreated ceramic matrix composite material;

(3) adding the foamy copper into acetone for ultrasonic pretreatment to obtain pretreated foamy copper;

(4) the pretreated nickel-based superalloy, the pretreated brazing filler metal foil, the pretreated foamy copper, the pretreated brazing filler metal foil and the pretreated SiC removal alloy are subjected to_fSequentially stacking the/SiC ceramic matrix composite materials to obtain a piece to be welded;

(5) taking the part to be welded for brazing to obtain SiC_fThe material for brazing the/SiC ceramic matrix composite and the nickel-based superalloy.

The beneficial effects of the preferred technical scheme are as follows: the invention discloses SiC_fMethod for brazing/SiC ceramic matrix composite and nickel-based superalloy by adding foam copperThe intermediate layer can promote the diffusion of elements by utilizing the three-dimensional structure of the foam Cu, so that reaction products at the welding seam are uniformly dispersed and distributed, the residual stress at the welding seam can be effectively relieved, the mechanical property of a soldered joint is obviously improved, and the SiC with excellent service performance can be obtained_fThe material for brazing the/SiC ceramic matrix composite and the nickel-based superalloy.

The basic principle on which the invention is based: the foam Cu can optimize the distribution of an interface compound formed in a welding seam due to a unique three-dimensional structure; the foam Cu can consume active element Ti from the brazing filler metal, and effectively inhibit the reaction of the ceramic matrix composite material and the Ti element from forming continuous brittle compounds on the side of the ceramic matrix composite material; in-situ fine Ti-Cu intermetallic compounds generated in the brazing process are in dispersion distribution, have obvious strengthening effect, can relieve the residual stress of the joint and form good stress transition in the joint; after brazing, due to the strong interaction between Cu and Ni and the mutual interference of reaction phases generated in a brazed joint, more solid solution Cu (s, s) structures are preferentially generated on the side of the nickel-based alloy and in brazing seams, and the existence of the larger bulk Cu (s, s) phases reduces the residual stress in the joint.

Preferably, the nickel-base superalloy in the step (1) is a GH536 alloy; the brazing filler metal foil is AgCuTi brazing filler metal foil or AgCu brazing filler metal foil;

the polishing is performed by sequentially using 200-mesh, 400-mesh, 600-mesh and 800-mesh sand paper; 300ml of acetone; the ultrasonic pretreatment time is 10min-20min, and the frequency is 40 KHz.

The beneficial effects of the preferred technical scheme are as follows: according to the invention, impurities on the surface of the nickel-based superalloy can be removed through the step (1), and impurities on the surface of the brazing filler metal foil can be removed, so that brazing is facilitated, and the brazing material with stable performance can be obtained.

Preferably, the ceramic matrix composite material in step (2) comprises SiC_fSiC ceramic matrix composite material, C_fa/C ceramic matrix composite;

the polishing is performed by using 800-mesh sand paper; the ultrasonic pretreatment time is 10min-20min, and the frequency is 40 KHz.

The beneficial effects of the preferred technical scheme are as follows: the SiC can be removed by grinding in the step (2)_fImpurities are arranged on the surface of the/SiC ceramic matrix composite material, so that the brazing operation is facilitated, and the brazing material with stable performance is further facilitated to be obtained.

Preferably, the thickness of the copper foam in the step (3) is 50-200 μm; the ultrasonic pretreatment time is 10min-20min, and the frequency is 40 KHz.

Preferably, the pressure of the brazing in the step (5) is 4 × 10^-3Pa, the temperature of 850-910 ℃, the heat preservation time of 5-20min, and then cooling to room temperature.

Preferably, the piece to be welded is placed in a vacuum brazing furnace for brazing operation.

Preferably, the brazing temperature in the step (5) is 850 ℃ to 870 ℃.

The beneficial effects of the preferred technical scheme are as follows: according to the invention, the best brazing effect can be obtained by performing brazing experiments in the different temperature environments.

Preferably, the brazing temperature in the step (5) is 870-890 ℃.

The beneficial effects of the preferred technical scheme are as follows: by performing the brazing experiment in the different temperature environments, the optimum brazing effect can be obtained.

Preferably, the brazing temperature in the step (5) is 890-910 ℃.

Preferably, the heat preservation time in the step (5) is 5-10 min.

The beneficial effects of the preferred technical scheme are as follows: and carrying out brazing experiments under different heat preservation times to obtain the optimal brazing temperature process parameters.

Preferably, the heat preservation time in the step (5) is 10-15 min.

The beneficial effects of the preferred technical scheme are as follows: the best brazing effect can be obtained by performing brazing experiments in the different temperature environments.

According to the technical scheme, compared with the prior art, the SiC provided by the invention_fThe method for brazing the/SiC ceramic matrix composite and the nickel-based superalloy has the following beneficial effects that:

(1) according to the invention, the three-dimensional structure of the foam Cu is utilized to promote the diffusion of elements, so that reaction products at the welding seam are uniformly dispersed and distributed, the residual stress at the welding seam can be effectively relieved, and the mechanical property of a soldered joint is obviously improved;

(2) the invention takes the foam copper as the intermediate layer, and the proportion of the copper element is changed in the brazing process due to the addition of the copper element, so that the combination of the Ti element and the Cu element is promoted, the Ti element is consumed, and the generation of brittle Ti compounds is reduced;

(3) the method disclosed by the invention only adds the foamy copper intermediate layer simply, has simple operation, high efficiency and low cost, is convenient for industrial production, and can be used for preparing SiC_fThe soldering method has good application prospect in the field of soldering of the/SiC ceramic matrix composite material and the nickel-based superalloy.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.

Fig. 1 is a schematic structural diagram of a part to be welded according to an embodiment of the invention.

In the figure: 1 is pretreated SiC_fThe SiC ceramic matrix composite material comprises 2 pretreated brazing filler metal foils, 3 pretreated foamy copper and 4 pretreated nickel-based high-temperature alloy.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

The embodiment of the invention discloses SiC_fThe method for brazing the/SiC ceramic matrix composite and the nickel-based superalloy specifically comprises the following steps:

(1) sequentially polishing the nickel-based high-temperature alloy and the brazing filler metal foil by using 200-mesh, 400-mesh, 600-mesh and 800-mesh abrasive paper, then adding the polished nickel-based high-temperature alloy and the brazing filler metal foil into acetone for ultrasonic pretreatment for 10-20 min, and removing surface impurities to obtain a pretreated nickel-based high-temperature alloy and a pretreated brazing filler metal foil; wherein the ultrasonic pretreatment frequency is 40 KHz;

(2) polishing the ceramic matrix composite material by adopting 800-mesh sand paper, adding the polished ceramic matrix composite material into acetone, performing ultrasonic pretreatment for 10-20 min, and removing surface impurities to obtain a pretreated ceramic matrix composite material; wherein the ultrasonic pretreatment frequency is 40 KHz;

(3) adding the foamy copper into acetone, carrying out ultrasonic pretreatment for 10-20 min, and removing surface impurities to obtain pretreated foamy copper; the ultrasonic pretreatment frequency is 40 KHz; the thickness of the foam copper is 50-200 μm;

(4) sequentially stacking the pretreated nickel-based superalloy, the pretreated brazing filler metal foil, the pretreated foamy copper, the pretreated brazing filler metal foil and the pretreated ceramic-based composite material to obtain a workpiece to be welded as shown in figure 1;

(5) taking a part to be welded at 4 x 10^-3And (3) keeping the temperature of 850-910 ℃ for 5-20min under the Pa pressure for brazing, and then cooling to room temperature to obtain the ceramic matrix composite and nickel-based high-temperature alloy brazing material.

In order to further optimize the technical scheme, the ceramic matrix composite material in the step (2) is SiC_fSiC ceramic matrix composite material, C_fa/C ceramic matrix composite.

In order to further optimize the technical scheme, the brazing filler metal foil in the step (1) is AgCuTi brazing filler metal foil or AgCu brazing filler metal foil.

For further optimization of the technical scheme, the thickness of the copper foam in the step (3) is 50 μm.

For further optimization of the technical scheme, the thickness of the copper foam in the step (3) is 100 μm.

For further optimization of the technical scheme, the thickness of the copper foam in the step (3) is 200 μm.

For further optimization, the pressure in step (5) is 4 × 10^-3Pa, the temperature is 850-870 ℃, and the temperature is kept for 5-20 min.

For further optimization, the pressure in step (5) is 4 × 10^-3Keeping the temperature for 5-20min under the conditions that the Pa and the temperature are 870-890 ℃.

For further optimization, the pressure in step (5) is 4 × 10^-3Keeping the temperature for 5-20min under the conditions of Pa and the temperature of 890-910 ℃.

For further optimization, the pressure in step (5) is 4 × 10^-3Pa, at 890-910 deg.C, and keeping the temperature for 5-10 min.

For further optimization, the pressure in step (5) is 4 × 10^-3Pa, and the temperature is 890-910 ℃, and the temperature is kept for 10-15 min.

Example 1

The embodiment 1 of the invention discloses SiC_fThe method for brazing the/SiC ceramic matrix composite and the nickel-based superalloy specifically comprises the following steps:

the nickel-based high-temperature alloy is GH536 alloy, and the size of the nickel-based high-temperature alloy is 5mm multiplied by 7mm multiplied by 2 mm;

the brazing filler metal foil is an AgCuTi brazing filler metal foil, the thickness of the brazing filler metal foil is 50 mu m, and the size of the brazing filler metal foil is 5mm multiplied by 4 mm;

(2) polishing the ceramic matrix composite material by adopting 800-mesh sand paper, adding the polished ceramic matrix composite material into acetone, performing ultrasonic pretreatment for 10min, and removing surface impurities to obtain a pretreated ceramic matrix composite material; wherein the ultrasonic pretreatment frequency is 40 KHz;

the ceramic matrix composite is SiC_fThe size of the/SiC ceramic matrix composite material is 5mm multiplied by 4 mm;

(3) adding the foamy copper into acetone, carrying out ultrasonic pretreatment for 10min, and removing surface impurities to obtain pretreated foamy copper; the ultrasonic pretreatment frequency is 40 KHz; the thickness of the foam copper is 100 mu m;

(4) stacking the pretreated nickel-based superalloy, the pretreated brazing filler metal foil, the pretreated foamy copper, the pretreated brazing filler metal foil and the pretreated ceramic matrix composite material in sequence to obtain a to-be-welded part as shown in figure 1;

(5) placing the piece to be welded in a brazing furnace at 4 x 10^-3Keeping the temperature at 890 ℃ for 10min under Pa pressure for brazing, and then cooling to room temperature to obtain SiC_fthe/SiC ceramic matrix composite material-GH 536 alloy brazing material.

Effect testing

Evaluation of room temperature shear strength test was conducted using a thermal simulation tester (Gleeble-1500D) (test speed 0.5mm/min), and the SiC prepared in example 1 was obtained_fThe maximum shear strength of the/SiC ceramic matrix composite-GH 536 alloy brazed joint is 76Mpa, and the addition of the metal foam intermediate layer relieves the SiC_fThe residual stress of the/SiC ceramic matrix composite and the nickel-based high-temperature alloy joint improves the performance of the joint.

Example 2

Embodiment 2 of the invention discloses a compound C_fThe method for brazing the/C ceramic matrix composite and the nickel-based superalloy specifically comprises the following steps:

(1) sequentially polishing the nickel-based high-temperature alloy and the brazing filler metal foil by using 200-mesh, 400-mesh, 600-mesh and 800-mesh abrasive paper, then adding the polished nickel-based high-temperature alloy and the brazing filler metal foil into acetone for ultrasonic pretreatment for 10min, and removing surface impurities to obtain a pretreated nickel-based high-temperature alloy and a pretreated brazing filler metal foil; wherein the ultrasonic pretreatment frequency is 40 KHz;

the ceramic matrix composite is C_fThe size of the/C ceramic matrix composite material is 5mm multiplied by 4 mm;

(5) placing the piece to be welded in a brazing furnace at 4 x 10^-3Keeping the temperature of 870 ℃ for 10min under Pa pressure for brazing, and then cooling to room temperature to obtain C_fthe/C ceramic matrix composite material-GH 536 alloy brazing material.

Effect testing

Evaluation of room temperature shear Strength test was conducted using a thermal simulation tester (Gleeble-1500D) (test speed 0.5mm/min), C prepared in example 2_fThe maximum shear strength of a/C ceramic matrix composite-GH 536 alloy brazing joint is 36Mpa, and the addition of the metal foam intermediate layer relieves the C_fThe residual stress of the/C ceramic matrix composite and the nickel-based high-temperature alloy joint improves the performance of the joint.

Example 3

Embodiment 3 of the invention discloses SiC_fThe method for brazing the/SiC ceramic matrix composite and the nickel-based superalloy specifically comprises the following steps:

(3) adding the foamy copper into acetone, carrying out ultrasonic pretreatment for 10min, and removing surface impurities to obtain pretreated foamy copper; the ultrasonic pretreatment frequency is 40 KHz; the thickness of the foam copper is 50 μm;

Effect testing

Evaluation of room temperature shear strength test was conducted using a thermal simulation tester (Gleeble-1500D) (test speed 0.5mm/min), and the SiC prepared in example 1 was obtained_fThe maximum shear strength of the soldering joint of the/SiC ceramic matrix composite-GH 536 alloy is 42MPa, and the thickness of the foam copper applied in the embodiment has poor effect compared with the embodiment 1.

Example 4

Embodiment 4 of the invention discloses SiC_fThe method for brazing the/SiC ceramic matrix composite and the nickel-based superalloy specifically comprises the following steps:

(3) adding the foamy copper into acetone, carrying out ultrasonic pretreatment for 10min, and removing surface impurities to obtain pretreated foamy copper; the ultrasonic pretreatment frequency is 40 KHz; the thickness of the foam copper is 200 mu m;

Effect testing

Evaluation of room temperature shear strength test was conducted using a thermal simulation tester (Gleeble-1500D) (test speed 0.5mm/min), and the SiC prepared in example 1 was obtained_fThe maximum shear strength of the soldering joint of the/SiC ceramic matrix composite-GH 536 alloy is 23MPa, and the thickness of the foam copper applied in the embodiment has poor effect compared with the embodiment 1.

Example 5

Embodiment 5 of the invention discloses SiC_fThe method for brazing the/SiC ceramic matrix composite and the nickel-based superalloy specifically comprises the following steps:

(5) placing the piece to be welded in a brazing furnace at 4 x 10^-3Keeping the temperature at 850 ℃ under Pa pressure for 10min for brazing, and then cooling to room temperature to obtain SiC_fthe/SiC ceramic matrix composite material-GH 536 alloy brazing material.

Effect testing

Evaluation of room temperature shear Strength test was conducted using a thermal simulation tester (Gleeble-1500D) (test speed 0.5mm/min), and SiC prepared in example 5_fThe maximum shear strength of the soldering joint of the/SiC ceramic matrix composite-GH 536 alloy is 33MPa, and the soldering temperature in the embodiment has poor effect compared with the embodiment 1.

Example 6

Embodiment 6 of the invention discloses SiC_fThe method for brazing the/SiC ceramic matrix composite and the nickel-based superalloy specifically comprisesThe method comprises the following steps:

(5) placing the piece to be welded in a brazing furnace at 4 x 10^-3Keeping the temperature at 910 ℃ under Pa pressure for 10min for brazing, and then cooling to room temperature to obtain SiC_fthe/SiC ceramic matrix composite material-GH 536 alloy brazing material.

Effect testing

Evaluation of room temperature shear strength test was conducted using a thermal simulation tester (Gleeble-1500D) (test speed 0.5mm/min), and SiC prepared in example 6 was obtained_fThe maximum shear strength of the soldering joint of the/SiC ceramic matrix composite-GH 536 alloy is 21MPa, and the soldering temperature in the embodiment has poor effect compared with the embodiment 1.

Example 7

Hair brushMing embodiment 7 discloses SiC_fThe method for brazing the/SiC ceramic matrix composite and the nickel-based superalloy specifically comprises the following steps:

(5) placing the piece to be welded in a brazing furnace at 4 x 10^-3Keeping the temperature at 890 ℃ for 5min under Pa pressure for brazing, and then cooling to room temperature to obtain SiC_fthe/SiC ceramic matrix composite material-GH 536 alloy brazing material.

Effect testing

Evaluation of room temperature shear Strength test was conducted using a thermal simulation tester (Gleeble-1500D) (test speed 0.5mm/min), and SiC prepared in example 7_fThe maximum shear strength of the soldering joint of the/SiC ceramic matrix composite-GH 536 alloy is 38MPa, and the heat preservation time in the embodiment is compared with that in the embodimentExample 1 is not effective.

Example 8

Embodiment 8 of the invention discloses SiC_fThe method for brazing the/SiC ceramic matrix composite and the nickel-based superalloy specifically comprises the following steps:

(5) placing the piece to be welded in a brazing furnace at 4 x 10^-3Keeping the temperature at 890 ℃ for 20min under Pa pressure for brazing, and then cooling to room temperature to obtain SiC_fthe/SiC ceramic matrix composite material-GH 536 alloy brazing material.

Effect testing

Evaluation of room temperature shear Strength test was conducted using a thermal simulation tester (Gleeble-1500D) (test speed 0.5mm/min), and SiC prepared in example 8 was obtained_fThe maximum shear strength of the soldering joint of the/SiC ceramic matrix composite-GH 536 alloy is 18MPa, and the effect of the heat preservation time in the embodiment is poor compared with that in the embodiment 1.

Example 9

Embodiment 9 of the invention discloses a method for preparing a compound C_fThe method for brazing the/C ceramic matrix composite and the nickel-based superalloy specifically comprises the following steps:

Effect testing

Using a thermal simulation tester (Gleeble-1)500D) (test speed 0.5mm/min) evaluation of room temperature shear Strength test was conducted, C prepared in example 8_fThe maximum shear strength of the/C ceramic matrix composite-GH 536 alloy brazing joint is 22MPa, and the thickness of the copper foam applied in the embodiment has poor effect compared with the embodiment 1.

Example 10

Embodiment 10 of the invention discloses a compound C_fThe method for brazing the/C ceramic matrix composite and the nickel-based superalloy specifically comprises the following steps:

Effect testing

Evaluation of room temperature shear Strength test was conducted using a thermal simulation tester (Gleeble-1500D) (test speed 0.5mm/min), C prepared in example 10_fThe maximum shear strength of the/C ceramic matrix composite-GH 536 alloy brazed joint is 17MPa, and the thickness of the copper foam applied in the embodiment has poor effect compared with the embodiment 1.

Example 11

Embodiment 11 of the invention discloses a method for preparing a compound C_fThe method for brazing the/C ceramic matrix composite and the nickel-based superalloy specifically comprises the following steps:

(5) placing the piece to be welded in a brazing furnace at 4 x 10^-3Keeping the temperature at 850 ℃ for 10min under the pressure of PaSoldering, and cooling to room temperature to obtain the product C_fthe/C ceramic matrix composite material-GH 536 alloy brazing material.

Effect testing

Evaluation of room temperature shear Strength test was conducted using a thermal simulation tester (Gleeble-1500D) (test speed 0.5mm/min), C prepared in example 11_fThe maximum shear strength of the/C ceramic matrix composite-GH 536 alloy brazing joint is 29MPa, and the brazing temperature in the embodiment is poor compared with the embodiment 1.

Example 12

Embodiment 12 of the invention discloses a compound C_fThe method for brazing the/C ceramic matrix composite and the nickel-based superalloy specifically comprises the following steps:

(5) placing the piece to be welded in a brazing furnace at 4 x 10^-3Keeping the temperature at 910 ℃ under Pa pressure for 10min for brazing, and then cooling to room temperature to obtain C_fthe/C ceramic matrix composite material-GH 536 alloy brazing material.

Effect testing

Evaluation of room temperature shear Strength test was conducted using a thermal simulation tester (Gleeble-1500D) (test speed 0.5mm/min), C prepared in example 12_fThe maximum shear strength of the/C ceramic matrix composite-GH 536 alloy brazing joint is 16MPa, and the brazing temperature in the embodiment is poor compared with the embodiment 1.

Example 13

Embodiment 13 of the invention discloses a method for preparing a compound C_fThe method for brazing the/C ceramic matrix composite and the nickel-based superalloy specifically comprises the following steps:

(5) placing the piece to be welded in a brazing furnace at 4 x 10^-3Keeping the temperature of 870 ℃ for 5min under Pa pressure for brazing, and then cooling to room temperature to obtain C_fthe/C ceramic matrix composite material-GH 536 alloy brazing material.

Effect testing

Evaluation of room temperature shear Strength test was conducted using a thermal simulation tester (Gleeble-1500D) (test speed 0.5mm/min), C prepared in example 13_fThe maximum shear strength of the/C ceramic matrix composite-GH 536 alloy brazing joint is 24MPa, and the heat preservation time in the embodiment is poor compared with that in the embodiment 1.

Example 14

Embodiment 14 of the invention discloses a C_fThe method for brazing the/C ceramic matrix composite and the nickel-based superalloy specifically comprises the following steps:

(5) placing the piece to be welded in a brazing furnace at 4 x 10^-3Keeping the temperature of 870 ℃ under Pa pressure for 20min for brazing, and then cooling to room temperature to obtain C_fthe/C ceramic matrix composite material-GH 536 alloy brazing material.

Effect testing

Evaluation of room temperature shear Strength test was conducted using a thermal simulation tester (Gleeble-1500D) (test speed 0.5mm/min), C prepared in example 14_fThe maximum shear strength of the/C ceramic matrix composite-GH 536 alloy brazing joint is 15MPa, and the heat preservation time in the embodiment is poor compared with that in the embodiment 1.

The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. The device disclosed by the embodiment corresponds to the method disclosed by the embodiment, so that the description is simple, and the relevant points can be referred to the method part for description.

The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. a method for SiC _f /SiC ceramic matrix composite material and nickel-based superalloy brazing, is characterized in that, specifically comprises the steps:

(1) grinding the nickel-based superalloy and the solder foil, and then adding acetone for ultrasonic pretreatment to obtain a pretreated nickel-based superalloy and a pretreated solder foil;

(2) grinding the ceramic matrix composite material, adding it to acetone, and performing ultrasonic pretreatment to obtain a pretreated ceramic matrix composite material;

(3) adding copper foam into acetone to carry out ultrasonic pretreatment to obtain pretreated copper foam;

(4) stacking the pretreated nickel-based superalloy, the pretreated solder foil, the pretreated copper foam, the pretreated solder foil and the pretreated ceramic matrix composite material in sequence, Get the parts to be welded;

(5) Brazing the to-be-welded parts to obtain the ceramic matrix composite material and the nickel-based superalloy brazing material.

2. the method for brazing SiC _f /SiC ceramic matrix composite material and nickel-based superalloy according to claim 1, is characterized in that, the nickel-based superalloy described in step (1) is GH536 alloy; Described brazing material foil The sheet is AgCuTi solder foil or AgCu solder foil;

The grinding is performed by using 200-mesh, 400-mesh, 600-mesh and 800-mesh sandpaper in sequence; the ultrasonic pretreatment time of 300ml of acetone is 10min-20min, and the frequency is 40KHz.

3. The method for brazing SiC _f /SiC ceramic matrix composite material and nickel-based superalloy according to claim 1, wherein the ceramic matrix composite material in step (2) comprises SiC _f /SiC ceramic matrix composite material , C _f /C ceramic matrix composite material or C _f /SiC ceramic matrix composite material;

The grinding is carried out with 800-mesh sandpaper; the ultrasonic pretreatment time is 10min-20min, and the frequency is 40KHz.

4. The method for brazing SiC _f /SiC ceramic matrix composite material and nickel-based superalloy according to claim 1, wherein the thickness of the foamed copper in step (3) is 50 μm-200 μm; The treatment time is 10min-20min, and the frequency is 40KHz.

5. the method for brazing SiC _f /SiC ceramic matrix composite material and nickel-based superalloy according to claim 1, is characterized in that, the pressure of brazing described in step (5) is 4 × 10 ^-3 Pa, temperature The temperature is 850℃-910℃, the holding time is 5-20min, and then cooled to room temperature.

6 . The method for brazing SiC _f /SiC ceramic matrix composite material and nickel-based superalloy according to claim 5 , wherein the brazing temperature in step (5) is 850° C.-870° C. 7 .

7 . The method for brazing SiC _f /SiC ceramic matrix composite material and nickel-based superalloy according to claim 5 , wherein the brazing temperature in step (5) is 870-890° C. 8 .

8 . The method for brazing SiC _f /SiC ceramic matrix composite material and nickel-based superalloy according to claim 5 , wherein the brazing temperature in step (5) is 890-910° C. 9 .

9. The method for brazing SiC _f /SiC ceramic matrix composite material and nickel-based superalloy according to any one of claims 5 to 8, wherein the holding time in step (5) is 5 to 10 min.

10. The method for brazing SiC _f /SiC ceramic matrix composite material and nickel-based superalloy according to any one of claims 5 to 8, wherein the holding time in step (5) is 10 to 15 min.