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A Method for Service Damage Evaluation and Creep Life Prediction of Superalloy Turbine Blades

A technology of turbine blades and high-temperature alloys, applied in measuring devices, using stable tension/pressure to test material strength, instruments, etc., can solve problems such as difficult to provide accurate prediction results, differences in creep deformation mechanisms, etc., and achieve true results Reliable, broad prospects, and strong engineering application effects

Active Publication Date: 2020-06-26
UNIV OF SCI & TECH BEIJING
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Problems solved by technology

This series of microstructure evolution may lead to significant differences in the creep deformation mechanism of superalloys at different stages of creep, and a series of creep life prediction methods that only consider macroscopic mechanical properties will be difficult to provide accurate prediction results

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  • A Method for Service Damage Evaluation and Creep Life Prediction of Superalloy Turbine Blades
  • A Method for Service Damage Evaluation and Creep Life Prediction of Superalloy Turbine Blades
  • A Method for Service Damage Evaluation and Creep Life Prediction of Superalloy Turbine Blades

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Embodiment Construction

[0028] The following examples will further illustrate the present invention in conjunction with the accompanying drawings, so that those skilled in the art can better understand the advantages and features of the present invention.

[0029] First of all, taking a DZ125 alloy turbine blade after 300 hours of service as an example, it is carried out as follows figure 2 For the cuts shown, the microstructure of each part was obtained, as image 3 shown. Refer to the grid point method in GB / T 15749 to quantitatively count the volume fraction (Vf) of the γ' phase. Set 216 grid intersection points, when the intersection point is located in the γ′ phase, it is counted as 1, when the intersection point is located at the interface between the γ′ phase and the matrix, it is counted as 0.5, when the intersection point is located in the matrix, it is counted as 0, the ratio of the above statistical results to the total number of intersection points is is Vf. Use the announcement:

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Abstract

The invention provides a method for evaluating the service damage of a high-temperature alloy turbine blade and predicting the creep life of the same and relates to the evaluation of the creep residual life of a DZ125 directional solidified high-temperature alloy turbine blade. According to the method, a DZ125 directional turbine blade service damage and creep residual life evaluation and prediction method and process are constructed based on the microstructure evolution database of DZ125 alloy under a near-service condition. With the method and the process adopted, the evaluation of the service damage degree of an on-service turbine blade in a macroscopic level and a microscopic level and the prediction of the creep residual life of the on-service turbine blade are realized. Compared withan existing creep residual life method, the method starts from the quantitative characterization of a microscopic structure, thereby having higher accuracy and reasonability. The method is suitable for engineering application and has relatively high engineering application significance and a bright prospect in the creep residual life prediction, maintenance and design of DZ125 alloy and other single-crystal or directional alloy turbine blades.

Description

technical field [0001] The invention belongs to the technical field of nickel-based directional solidification high-temperature alloy blades, and in particular relates to a method for service damage evaluation and creep life prediction of high-temperature alloy turbine blades. Background technique [0002] Aeroengines are highly complex and sophisticated thermodynamic machines. As one of the most critical components of aeroengines, turbine blades are important hot-end components that convert the enthalpy and kinetic energy of gas into mechanical energy. With the continuous improvement of the thrust-to-weight ratio of aeroengines, the temperature of the gas outside the blades and the speed of the turbine continue to increase, resulting in a gradual increase in the service temperature and stress of the turbine blades. Under the combined action of high temperature and stress, the turbine blades of aero-engines inevitably undergo creep deformation, which may cause the elongation...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01N3/18G06F30/20
CPCG01N3/18G01N2203/0071G01N2203/0647G06N3/04
Inventor 冯强付超李龙飞郑为为
Owner UNIV OF SCI & TECH BEIJING
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