SiCf / Ti2AlNb heterogeneous core material reinforced TC17 composite material and preparation method

Abstract

The application relates to a continuous silicon carbide fiber reinforced titanium-based composite material and the composite material field, in particular to a continuous SiC fiber reinforced Ti2AlNb (SiC f / Ti2AlNb) heterogeneous core material reinforced TC17 composite material and a preparation method. A continuous SiC fiber reinforced Ti2AlNb-based composite material is selected as a heterogeneous core material, TC17 alloy is selected as a sheath, and the TC17 alloy is reinforced by the heterogeneous core material SiC f / Ti2AlNb composite material. A hot isostatic pressing process is adopted to realize good combination of the SiC f / Ti2AlNb heterogeneous core material and the TC17 sheath, and the obtained SiC f / Ti2AlNb / TC17 composite material has a room temperature strength of 1690 MPa and a 450 DEG C high-temperature strength of 1850 MPa. The application effectively improves the high-temperature strength of the TC17 and SiC f / TC17 material, and the high-temperature strength is increased by about 500-1100 MPa.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of continuous silicon carbide fiber reinforced titanium-based composite materials and composite materials, in particular to a SiC f / Ti2AlNb hetero-core material reinforced TC17 composite material and a preparation method thereof. BACKGROUND

[0002] TC17 high-temperature-resistant titanium alloy has a good combination of low density, fatigue resistance, high strength, wear resistance and oxidation resistance, and becomes a candidate material for aircraft engines, compressor blades and fly discs with a thrust-to-weight ratio greater than 10. The maximum use temperature of TC17 alloy is 427℃. In order to improve the high-temperature performance of TC17 material, a composite material is usually used to improve the high-temperature performance of TC17 alloy. The current effective method for improving the high-temperature performance of TC17 alloy is to reinforce TC17 alloy with continuous SiC fibers to prepare SiC f / TC17 composite material. The tensile strength of SiC f / TC17 prepared at a high temperature of 400-500℃ is about 1300MPa, and the tensile strength of TC17 alloy at a high temperature of 400-500℃ is about 600MPa. Obviously, the high-temperature strength of TC17 alloy reinforced by SiC fibers is significantly improved.

[0003] In recent years, with the development of the global aerospace field, the service requirements for TC17 alloy are more stringent, especially the high-temperature strength. The current method for improving the high-temperature performance of TC17 is to increase the volume fraction of SiC fibers. However, this method will greatly increase the cost of the material and increase the brittleness of the material, so this method is generally not used.

[0004] According to the above, how to improve the high-temperature strength of TC17 or SiC f / TC17 at low cost will become the key to widening the application range and use field of TC17 material. SUMMARY

[0005] The present application aims to provide a SiC f / Ti2AlNb hetero-core material reinforced TC17 composite material and a preparation method thereof, which solves the problem of low strength of TC17 or SiC f / TC17 material at high temperature, effectively improves the high-temperature use strength of TC17 and SiC f / TC17, and has low cost.

[0006] The technical solution of the present application is realized by the following way:

[0007] A SiC fTi2AlNb heterogenous core material reinforced TC17 composite material, SiC f Ti2AlNb composite material is a heterogenous core material, TC17 alloy is selected as a cladding, and SiC f Ti2AlNb composite material reinforced TC17 alloy is prepared into SiC f Ti2AlNb / TC17 composite material.

[0008] The SiC f Ti2AlNb heterogenous core material reinforced TC17 composite material, the volume fraction of SiC fiber accounts for 40-55% of the total volume fraction of SiC f Ti2AlNb heterogenous core material reinforced TC17 composite material accounts for 40-55% of the total volume fraction of SiC

[0009] The SiC f Ti2AlNb heterogenous core material reinforced TC17 composite material, the Ti2AlNb alloy composition accounts for 22-25% of Al, 24-26% of Nb, and the balance of Ti in terms of atomic percentage.

[0010] The SiC f Ti2AlNb heterogenous core material reinforced TC17 composite material, the TC17 alloy cladding organization is a basket organization, the cladding outer diameter is 3-4 mm, the thickness is 0.3-0.65 mm, and the pore size is 2.4-2.7 mm.

[0011] The SiC f Ti2AlNb heterogenous core material reinforced TC17 composite material, the Ti2AlNb alloy is sputtered onto the SiC fiber by a magnetron sputtering method to prepare a precursor wire, the precursor wire is cut to a length shorter than the cladding length by 4-6 mm, and is loaded into the TC17 alloy cladding, and the precursor wire is in close contact with the TC17 alloy cladding, and a hot isostatic pressing process is used to realize SiC f Ti2AlNb heterogenous core material and the cladding are well combined.

[0012] The SiC f Ti2AlNb heterogenous core material reinforced TC17 composite material, the hot isostatic pressing process is as follows: the internal pressure of the hot isostatic pressing equipment is reduced to below 2x10 -2 MPa, the temperature is raised to 900-940 DEG C at a temperature rise rate of 4-7 DEG C per minute, the temperature is kept constant at 130-150 MPa for 3-5 h, then the temperature is cooled to 280-320 DEG C at 130-150 MPa for 0-2 h, and then the temperature is cooled to room temperature.

[0013] The SiC fThe preferred method for preparing the / Ti2AlNb heterostructure reinforced TC17 composite material is a hot isostatic pressing process, wherein the process involves evacuating the equipment to reduce the internal pressure to below 2 × 10⁻⁶. -2 The furnace is heated to 920℃ at a rate of 4-7℃ per minute, held at 130-150MPa for 4 hours, then cooled to 300℃ and held at 130-150MPa for 1 hour, and then cooled to room temperature.

[0014] The SiC f The preparation method of / Ti2AlNb heterostructure reinforced TC17 composite material involves welding the cladding riser with a vacuum electron beam. Both the cladding riser material and the cladding material are TC17 alloy with a basket mesh structure.

[0015] The design concept of this invention is:

[0016] This invention selects SiC that is resistant to high temperatures and has high strength. f / Ti2AlNb heterostructure core material is used as the reinforcement of TC17 alloy, and a basket-structured TC17 cladding and a suitable hot isostatic pressing process are selected to achieve good bonding strength and appropriate degree of reaction between the composite material and the cladding, so as to obtain a composite material with medium strength at room temperature and high strength at high temperature.

[0017] Specifically, the main design concept of this invention is that the composite material possesses the low density, fatigue resistance, wear resistance, and oxidation resistance of TC17, while also having the properties of SiC. f The high-temperature strength characteristics of the / Ti2AlNb heterostructure were observed. To ensure the bonding of the two materials, a suitable heat treatment regime was explored. This heat treatment regime achieved the desired high strength of SiC. f The moderate bonding strength at the interface between the Ti2AlNb heterostructure core and the TC17 cladding hinders crack propagation. Furthermore, this heat treatment process achieves optimal SiC... f The Ti2AlNb heterogeneous core material contains Ti2AlNb with high temperature resistance and good plasticity, and B2 and O structures, while the TC17 sheath has a basket structure with high temperature resistance and fatigue resistance.

[0018] The advantages and beneficial effects of this invention are:

[0019] 1. The high-temperature strength of the composite material obtained by this invention is significantly improved, SiC f The / Ti2AlNb / TC17 composite material can achieve a strength of 1850MPa at 450℃.

[0020] 2. The composite material obtained by this invention exhibits excellent room temperature strength, SiC f / Ti2AlNb / TC17 has a room temperature strength of up to 1696 MPa.

[0021] 3. The SiC f Compared with the method of improving the high temperature strength of TC17 alloy by increasing the volume fraction of SiC fiber, the cost of / Ti2AlNb / TC17 is significantly reduced.

[0022] 4. The composite material can be more widely used in aerospace and transportation industry. BRIEF DESCRIPTION OF DRAWINGS

[0023] Figure 1 It is a size drawing of rod-shaped tensile specimen.

[0024] Figure 2 It is an interface morphology drawing of TC17 cladding and Ti2AlNb matrix.

[0025] Figure 3 It is a drawing of the thickness of carbon layer and Ti2AlNb matrix reaction layer and the microstructure of Ti2AlNb.

[0026] Figure 4 It is a drawing of SiC f / Ti2AlNb / TC17 room temperature tensile curve. In the drawing, the horizontal coordinate Engineering strain represents engineering strain (%), and the vertical coordinate Engineering stress represents engineering stress (MPa).

[0027] Figure 5 It is a drawing of SiC f / Ti2AlNb / TC17 high temperature tensile curve at 450℃. In the drawing, the horizontal coordinate Engineering strain represents engineering strain (%), and the vertical coordinate Engineering stress represents engineering stress (MPa). DETAILED DESCRIPTION

[0028] Hereinafter, the present application is further described in detail through examples and drawings.

[0029] Example 1

[0030] In this embodiment, Ti2AlNb alloy is sputtered onto SiC fiber by magnetron sputtering method to prepare a precursor wire. The composition of Ti2AlNb alloy is Al: 23%, Nb: 25%, Ti: balance in atomic percentage. The total diameter of the selected precursor wire is 145±10μm, wherein: the thickness of the carbon layer between the SiC fiber and the Ti2AlNb alloy layer is about 1.5μm, the diameter of the SiC fiber is about 100μm, the tensile strength is about 3800MPa, and the elastic modulus is about 400GPa.

[0031] In this embodiment, the sheath selected is a TC17 alloy sheath, and the structure is a basket weave structure. The outer diameter of the sheath is 3.5 mm, the thickness is 0.5 mm, and the pore size is 2.5 mm. The precursor wire is cut to a length of about 6 mm shorter than the length of the sheath, loaded into the TC17 alloy sheath, and the SiC f The Ti2AlNb hetero-core material is in close contact with the TC17 alloy sheath, and the volume fraction of the SiC fiber is about 40% of the total volume fraction. Subsequently, vacuum is drawn to make the internal pressure of the material 1 × 10 -2 MPa, and the sheath riser is welded by a vacuum electron beam, and the sheath riser material and the sheath material are both TC17 alloy with a basket weave structure.

[0032] The hot isostatic pressing process is used to realize good combination of the SiC f / Ti2AlNb hetero-core material and the sheath. The hot isostatic pressing process is as follows: the sample is heated to 900℃ at a heating rate of 5℃ per minute, and then isothermal and pressure holding is performed at 140 MPa for 4 h, and then is cooled to 300℃ in the furnace, and isothermal and pressure holding is performed at 140 MPa for about 1 h, and then is cooled to room temperature in the furnace.

[0033] As shown in Figure 3 , the Ti2AlNb structure after the heat treatment control is fine O phase and high-temperature-resistant B2 phase, and the thickness of the carbon layer and the Ti2AlNb substrate reaction layer is less than 1 μm (about 0.8 μm), and the TC17 alloy sheath with a basket weave structure and the hetero-core material SiC f / Ti2AlNb have no obvious reaction at the interface, as shown in Figure 2 .

[0034] As shown in Figure 1 , the sample after the hot isostatic pressing is processed into a rod-shaped sample, the sample length L1 = 52 mm, the gauge section length L2 = 21 mm, and the diameter of the clamping section is M6 screw head, and the diameter of the clamping section is M6 screw head, and the diameter of the clamping section is M6 screw head, and the diameter

[0035] of the clamping section is M6 screw head, and the diameter Figure 4 of the clamping section is M6 screw head, and the diameter Figure 5 of the clamping section is M6 screw head, and the diameter of the clamping section is M6 screw head, and the diameter

[0036] of the clamping section is M6 screw head, and the diameter Material Tensile Condition Breaking Strength (MPa) Remark SiC f / Ti2AlNb / TC17]]> Room Temperature 1696 Tensile Measured (Engineering) SiC f / Ti2AlNb / TC17 450℃ 1850 Tensile Measured (Engineering)

[0037] As shown in Table 1, the prepared composite material has extremely high room temperature strength and high temperature strength.

[0038] The implementation result shows that the application effectively improves the TC17 and SiC f The high temperature strength of the TC17 material is about 500-1100 MPa. The composite material prepared by the application has high high temperature strength and low cost, and has good application prospect.

[0039] The above examples are only for illustrating the technical concept and characteristics of the application, and the purpose is to enable those skilled in the art to understand the content of the application and implement it, and cannot limit the protection scope of the application. Any equivalent changes or modifications made in accordance with the spirit and essence of the application shall be covered within the protection scope of the application.

Claims

1. A SiC f Method for manufacturing a TC17 composite material reinforced with a SiC SiC f / Ti2AlNb composite material is a heterogeneous core material, TC17 alloy is selected as a cladding, and the SiC f / Ti2AlNb composite material is selected as a heterogeneous core material, and TC17 alloy is selected as a cladding, and the SiC f / Ti2AlNb / TC17 composite material is prepared. The volume fraction of SiC fibers in SiC f / 40~55% of the total integral of Ti2AlNb heterostructure core-reinforced TC17 composite materials; The Ti2AlNb alloy composition in atomic percentage is Al: 22-25, Nb: 24-26, and Ti: balance; The TC17 alloy sleeve has a basket weave structure, an outer diameter of 3-4 mm, a thickness of 0.3-0.65 mm, and a pore diameter of 2.4-2.7 mm; The SiC f The preparation method of the Ti2AlNb heterogeneous core material reinforced TC17 composite material is as follows: Ti2AlNb alloy is sputtered on SiC fibers by a magnetron sputtering method to prepare a precursor filament; the precursor filament is cut to a length shorter than the length of a sheath by 4-6 mm, and is loaded into the TC17 alloy sheath, and the precursor filament is in close contact with the TC17 alloy sheath; and a hot isostatic pressing process is used to realize the good combination of the SiC f Ti2AlNb heterogeneous core material and the sheath. The hot isostatic pressing process is: vacuumizing to make the pressure inside the hot isostatic pressing equipment lower than 2×10 -2 MPa, heating to 900-940℃ at a heating rate of 4-7℃ per minute, keeping the temperature and pressure for 3-5h under 130-150MPa, then cooling in the furnace to 280-320℃, keeping the temperature and pressure for 0-2h under 130-150MPa, and then cooling in the furnace to room temperature.

2. The SiC of claim 1 f A method for preparing a TC17 composite material reinforced by a / Ti2AlNb hetero-core material, characterized in that, The hot isostatic pressing process is: vacuumizing to make the pressure inside the hot isostatic pressing equipment lower than 2×10 -2 MPa, heating to 920℃ at a heating rate of 4~7℃ per minute, keeping the temperature and pressure for 4h under 130~150MPa, then cooling to 300℃ with the furnace, keeping the temperature and pressure for 1h under 130~150MPa, and then cooling to room temperature with the furnace.

3. The SiC of claim 1 or 2 f A method for preparing a TC17 composite material reinforced by a / Ti2AlNb hetero-core material, characterized in that, The sleeve riser is welded by a vacuum electron beam, and the sleeve riser material and the sleeve material are both TC17 alloy having a basket weave structure.

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