Life extension method of nickel-based single crystal alloy blade based on heat treatment repairing

A nickel-based single crystal and alloy technology, which is applied in the field of turbine blades, can solve the problems such as the inability to repair the microstructure damage of turbine blades, and achieve the effects of improving mechanical properties and prolonging service life.

Inactive Publication Date: 2019-07-23
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
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Problems solved by technology

[0003] In the prior art, the apparent damage of turbine blades such as cracks and holes can be repaired by laser fusion welding or solid phase welding, but the microstructure damage of turbine blades cannot be repaired

Method used

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  • Life extension method of nickel-based single crystal alloy blade based on heat treatment repairing
  • Life extension method of nickel-based single crystal alloy blade based on heat treatment repairing
  • Life extension method of nickel-based single crystal alloy blade based on heat treatment repairing

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Embodiment Construction

[0025] Example embodiments will now be described more fully with reference to the accompanying drawings. Example embodiments may, however, be embodied in many forms and should not be construed as limited to the embodiments set forth herein; rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the concept of example embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar structures, and thus their detailed descriptions will be omitted.

[0026] Although relative terms such as "upper" and "lower" are used in this specification to describe the relative relationship of one component of an icon to another component, these terms are used in this specification only for convenience, for example, according to the description in the accompanying drawings directions for the example described above. It will be appreciated that if the illustrated device is turned over so...

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Abstract

The invention relates to the technical field of a turbine blade, and in particular to a life extension method of a nickel-based single crystal alloy blade based on heat treatment repairing. The life extension method comprises the following steps of: performing solid solution treatment to the nickel-based single crystal alloy blade so that a strengthening phase of the nickel-based single crystal alloy blade is completely dissolved in a matrix phase of the blade; performing cooling treatment to the nickel-based single crystal alloy blade after solid solution treatment, so that the strengtheningphase is analyzed from the middle of the matrix phase; performing a plurality of aging treatments to the nickel-based single crystal alloy blade after the cooling treatment, so that the strengtheningphase is completely precipitated from the matrix phase. The life extension method provided by the invention can repair the microstructure damage of the nickel-based single crystal alloy blade, so theservice life of the nickel-based single crystal alloy blade is prolonged.

Description

technical field [0001] The present disclosure relates to the technical field of turbine blades, in particular to a method for extending the life of a nickel-based single crystal alloy blade based on heat treatment repair. Background technique [0002] In the aviation industry, nickel-based single crystal alloys have become the preferred material for turbine blades in aero-engines due to their excellent mechanical properties at high temperatures, especially oxidation resistance, corrosion resistance, high toughness, and good processing plasticity. The working temperature of turbine blades is relatively high, which is close to or even exceeds 1000°C. Turbine blades are subjected to high pressure and vibration at high temperatures, so nickel-based single crystal alloys will inevitably undergo a certain degree of tissue damage and performance degradation, leading to eventual failure of turbine blades. In order to avoid accidents caused by the failure of turbine blades, it is ne...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22F1/10C30B29/52C30B33/02
CPCC22F1/10C30B29/52C30B33/02
Inventor 温志勋岳珠峰程昊蒋波谷淑宁王昭晗许壮壮
Owner NORTHWESTERN POLYTECHNICAL UNIV
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