Preparation method of monolithic turbine blade disc based on continuous carbon/silicon carbide fiber hybrid reinforced ceramic matrix composite material

A technology of silicon carbide fiber and turbine blisk, which is applied to the supporting elements of blades, mechanical equipment, machines/engines, etc., can solve problems such as poor practicability, achieve high-density preparation, improve low-temperature and high-temperature bearing performance, and shorten the preparation period. Effect

Inactive Publication Date: 2021-01-26
CENT SOUTH UNIV
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  • Abstract
  • Description
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Problems solved by technology

[0007] In order to overcome the shortcomings of the poor practicability of the existing integral turbine blisk preparation method, the purpose of the present invention is to provide a preparation method based on continuous carbon / silicon carbide fiber hybrid reinforced ceramic matrix composite integral turbine blisk, which can effectively shorten the The preparation cycle of the whole turbine blisks realizes the rapid and high-density preparation of the whole turbine blisks

Method used

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  • Preparation method of monolithic turbine blade disc based on continuous carbon/silicon carbide fiber hybrid reinforced ceramic matrix composite material

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0033] Step 1. Preparation of continuous C / SiC hybrid fibers mixed between bundles

[0034] First, install a bunch of 1K T300 carbon fiber and 1K silicon carbide fiber on the spinning frame respectively, the ratio of carbon fiber to silicon carbide is 20:80; they pass through the high temperature furnace at the same time, and the high temperature furnace adopts flowing inert gas (such as N 2 Gas, etc.) protection, the gas flow rate is 70L / min, the temperature in the furnace is 400°C,

[0035] Secondly, two bundles of C / SiC fibers are jointed at the furnace mouth of the high-temperature furnace, and then sizing is sequentially passed through the sizing tank. The sizing agent is 2% polyvinyl alcohol aqueous solution, and the water is deionized water;

[0036] Thirdly, the continuous C / SiC hybrid fiber after ply sizing is dried through a dryer in sequence, and the temperature of the dryer is 110°C;

[0037] Finally, a fiber winding machine is used to wind up the fibers to obtain...

Embodiment 2

[0058] Step 1. Preparation of continuous C / SiC hybrid fibers mixed between bundles

[0059] First, install a bunch of 3K T300 carbon fiber and 0.5K silicon carbide fiber on the spinning frame respectively, the ratio of carbon fiber to silicon carbide is 50:50; they pass through the high temperature furnace at the same time, and the high temperature furnace adopts flowing inert gas (such as N2 gas, etc.) protection, the gas flow rate is 70L / min, and the furnace temperature is 500°C.

[0060] Secondly, two bundles of C / SiC fibers are jointed at the furnace mouth of the high-temperature furnace, and then sizing through the sizing tank in turn. The sizing agent is 4% polyvinyl alcohol aqueous solution, and the water is deionized water;

[0061] Thirdly, the continuous C / SiC hybrid fiber after ply sizing is dried through the dryer in sequence, and the dryer adopts flowing high-temperature air to dry, and the temperature of the dryer is 200°C;

[0062] Finally, a fiber winding mach...

Embodiment 3

[0083] Step 1. Preparation of continuous C / SiC hybrid fibers mixed between bundles

[0084] First, install a bundle of 1K T800 carbon fiber and 0.6K silicon carbide fiber on the spinning frame, and pass them through the high-temperature furnace at the same time. The high-temperature furnace adopts flowing inert gas (such as N 2 Gas, etc.) protection, the gas flow rate is 70L / min, the furnace temperature is 600°C; the ratio of carbon fiber to silicon carbide is 40:60.

[0085] Secondly, two bundles of C / SiC fibers are jointed at the furnace mouth of the high-temperature furnace, and then sizing through the sizing tank in turn. The sizing agent is 5% polyvinyl alcohol aqueous solution, and the water is deionized water;

[0086] Thirdly, the continuous C / SiC hybrid fiber after ply sizing is dried through the dryer in sequence, and the dryer adopts flowing high-temperature air to dry, and the temperature of the dryer is 300°C;

[0087] Finally, a fiber winding machine is used to ...

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Abstract

The invention discloses a preparation method of a monolithic turbine blade disc based on a continuous carbon / silicon carbide fiber hybrid reinforced ceramic matrix composite material. According to themethod, carbon and silicon carbide fibers are intermingled through sizing equipment; a BN and PyC alternating multi-interface layer is prepared on the surface of the continuous C / SiC hybrid fiber byusing a chemical vapor infiltration method; the two-dimensional unit layer of the turbine blade disc prefabricated body is woven by adopting a plane polar coordinate weaving method, then the two-dimensional unit layer is paved by adopting a stacking method, and puncturing and sewing in the Z direction in the middle to finish weaving and shaping of the prefabricated body are carried out; the turbine disc prefabricated body ispre-densified by adopting a PIP method; and finally, the turbine disc blade is integrally machined, and the anti-oxidation coating is prepared through a chemical vapor infiltration method. Due to the fact that the fiber surface coating is uniform, continuous C / SiC hybrid fibers are arranged in the warp direction and the weft direction of the prefabricated body in the two principal stress directions, under the high-temperature aerobic condition, due to the fact that the C fibers are preferentially oxidized and sacrificed, the SiC fibers can be effectively protected,and the high-temperature bearing performance of the integral turbine blade disc is effectively improved.

Description

technical field [0001] The invention belongs to the technical field of integral turbine blisk preparation, and in particular relates to a method for preparing an integral turbine blisk based on continuous carbon / silicon carbide fiber hybrid reinforced ceramic matrix composite material. Background technique [0002] With the development of high-performance aircraft technology, higher requirements are put forward for the fuel efficiency, turbine temperature, and service life of aero-engines; conventional high-temperature alloy turbine blisks are gradually approaching their applications in terms of temperature resistance, high-temperature strength, and fatigue life. In addition, the space for alloy composition and turbine structure optimization is gradually shrinking, and the difficulty and complexity of performance improvement are huge, which seriously restricts the development of high-performance aircraft and technological progress in the future. [0003] Research in Document...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/80C04B35/628C04B35/84F01D5/02F01D5/28D04C1/02D04C1/06
CPCC04B35/62868C04B35/62873F01D5/02F01D5/284D04C1/02D04C1/06C04B2235/5248C04B2235/5244C04B2235/483C04B2235/96D10B2101/12D10B2101/16
Inventor 王春齐
Owner CENT SOUTH UNIV
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