Titanium alloy integral blade disc with composite performance and fabricating method thereof

Abstract

The invention relates to a titanium alloy integral blade disc with composite performance and a fabricating method thereof. A hub and a spoke of the blade disc are made of titanium alloy, a rim and a blade are made of titanium-base composite materials (or the whole disk is made of titanium alloy, and the blade is made of titanium-base composite materials), and the point of the blade also contains one or more of Cr, V, Mo with higher content so as to have properties of resisting temperature, abrasion and combustion. The hub and the spoke as well as the rim and the blade are sequentially prepared by piling layer by layer through adopting titanium alloy powder, one or more of titanium powder, TiC, B4C, and Cr3C2, and mixture powder of particles of one or more of Cr, V and Mo, which are synchronously conveyed and molten and deposited by adopting laser, so as to obtain the near net-shape titanium alloy integral blade disc with composite performance. The rim and the blade of the blade disc are integer, the hub and the spoke of the disc have high room temperature plasticity and strength as well as low cycle fatigue property, and the rim and the blade have high high-temperature fracture toughness property and high creep resistance.

Description

technical field [0001] The invention relates to a titanium alloy integral blade disc with composite performance and a manufacturing method thereof, belonging to the field of metal matrix composite materials and manufacturing thereof. Background technique [0002] Titanium alloy has low density, high specific strength, high yield ratio, corrosion resistance and good high-temperature mechanical properties. It is used in the manufacture of compressor rotor parts (compressor discs and blades) in modern high thrust ratio aeroengines. In recent years, the adoption of the integral blade disc structure (the compressor disc and the blade are integrated, the original tongue-and-groove connection structure has been canceled, the number of parts has been greatly reduced, and the overall weight has been significantly reduced. At the same time, because the integral blade disc can eliminate the traditional blade, The loss caused by the airflow escaping in the tenon and tenon groove in the ...

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Problems solved by technology

The traditional method also has the disadvantages of complicated process, large reinforcement particles, poor distribution uniformity, interface reaction, low interface bonding strength and difficult part forming and processing in the preparation of particle-reinforced titanium matrix composites. Integration on

[0005] In addition, due to the shortcomings of titanium alloys such as low hardness, poor wear resistance, large friction coefficient and instability, at the same time when designing advanced engines, in order to achieve the highest efficiency, the gap between the titanium blades and the titanium casing should be reduced as much as possible, but Too small a gap will increase the possibility of titanium friction ignition, commonly known as "titanium fire", which also limits the wider application of titanium alloys

Aiming at the problem of poor wear resistance of titanium alloys, a variety of surface modification technologies for titanium alloys have been developed. The early technologies mainly include traditional surface technologies such as electroplating, thermal diffusion, thermal oxidation, PVD, and CVD. In recent years, with the development of new technologies Constantly emerging, modern surface technologies such as micro-arc oxidation, plasma spraying, supersonic spraying, ion implantation, electron beam deposition, laser nitriding, double-layer glow ion infiltration, and new technologies that combine various surface technologies and film structure design They are all applied to the surface modification of titanium alloys. These technologies have achieved remarkable results in improving the friction and wear properties of titanium alloys. The cladding is thin, or the impact resistance is poor, or it is weakly combined with the base material, etc.

In response to the "titanium fire" problem of titanium alloys, one is to develop flame-retardant titanium alloys, such as the Ti-V-Cr AlloyC flame-retardant titanium alloy developed in the United States, and the Ti-Cu-Al series BTT-1 and BTT-3 developed in Russia. Alloys, Ti-V-Cr series alloys have good flame retardancy and mechanical properties, but because they contain a large amount of expensive V elements and have poor forgeability, the cost is very high. Ti-Cu-Al series has relatively poor comprehensive mechanical properties. The current main development trend is to develop low-cost Ti-V-Cr series flame-retardant titanium alloys (see the article "Research and Development of Flame-Resistant Titanium Alloys" written by Lei Liming et al., published In "Materials Herald", 2003, Vol. 17, No. 5, pp. 21-23); the second is to develop a flame-retardant alloy layer, and some studies use double-layer glow plasma infiltration technology to infiltrate Cr and Cu on the surface of titanium alloys. Form a flame-retardant alloy layer, but this technology has problems such as long high-temperature treatment time, thin infiltrated layer, and influence on the mechanical properties of the matrix (see the article "Research on Double-layer Glow Ionized Cr on Ti-6Al-4V Surface" written by Zhang Pingze et al. , published in "Weapons Materials Science and Engineering", 2005, Vol. 28 No. 1, pp. 17-20)

[0006] The working conditions of the titanium alloy compressor are harsh, and the blades often cause pits, falling blocks, cracks, breaks, etc. due to foreign object damage, and the wear of the blade tip is out of tolerance, etc., which affect the performance and reliability of the engine, and must be repaired in time. However, it is difficult to replace the damaged blades of the titanium alloy blisks, and the material and manufacturing costs of the blisks are very expensive, so it is necessary to consider the high-quality remanufacturing and repair of the damaged blisks

[0007] In summary, in order to meet the development needs of future high-performance aeroengines, it is necessary to develop a titanium alloy integral blade disc with composite properties, which is difficult to achieve with existing technologies, that is, to simultaneously achieve high room temperature plasticity, strength and low Cycle fatigue performance, the disk edge is required to have high high temperature fracture toughness and creep resistance. High-quality restoration of bladed disks

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