Single crystal nickel-base high-temperature alloy and aero-engine turbine part

Abstract

The invention relates to the technical field of high-temperature alloys, and discloses a single crystal nickel-base high-temperature alloy and an aero-engine turbine part. The single crystal nickel-base high-temperature alloy is prepared from the components in percentage by mass: 3 to 4 percent of Cr, 5.5 to 6.5 percent of Co, 0.3 to 0.5 percent of Mo, 6 to 7 percent of W, 6.5 to 7.5 percent of Ta, 0.08 to 0.12 percent of Hf, 5 to 6 percent of Al, 4.7 to 5.3 percent of Ru, 6.1 to 6.7 percent of Re, and the balance Ni and inevitable impurities. Compared with typical fifth-generation single crystal alloys TMS173 and TMS196, through increasing the contents of the Co, the W and the Ta, the solid solution capacity, the heat intensity and the castability of the high-temperature alloy are improved; through reducing the content of the Mo, the heat stability of the high-temperature alloy is improved, and the separation of a TCP phase is reduced; through controlling the content of the Cr to be between the TMS173 and the TMS196, the balance of the oxidation resistance and the heat stability of the high-temperature alloy is realized; and through controlling the contents of the impurities and microelements, the influence of the impurities and the microelements on the mechanical property of the high-temperature alloy is reduced.

Description

technical field [0001] The invention relates to the technical field of high-temperature alloys, in particular to a single-crystal nickel-based high-temperature alloy used for aeroengine turbine components. Background technique [0002] The high-pressure turbine blades of aero-engines are listed as the first key components of aero-engines because they are located in the parts with the highest temperature, the most complex stress and the harshest environment. With the continuous increase of the inlet temperature of the aero-engine turbine, the requirements for blade materials are becoming more and more stringent. The turbine inlet temperature of the F119 aero-engine currently in service reaches 1900-2050K, and the turbine inlet temperature of the latest generation engine is expected to reach 2100-2200K, which puts forward higher requirements for the temperature-bearing capacity of the turbine blade material. [0003] Due to the large addition of refractory elements in advance...

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Problems solved by technology

[0004] In view of this, the present invention provides a single crystal nickel-based superalloy and aero-engine turbine components, which solve the technical problems of poor oxidation resistance, thermal stability, thermal strength and casting performance of existing single crystal alloys

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