Method for evaluating service damage of single-crystal high-pressure turbine blade

By designing blade simulation components to conduct creep interruption tests and comparing graphic data, the problem of accuracy in evaluating the coating structure damage of single-crystal high-pressure turbine working blades was solved, and a comprehensive and accurate assessment of coating structure damage was achieved.

CN116223048BActive Publication Date: 2026-06-09AECC SHENYANG ENGINE RES INST
View PDF 3 Cites 0 Cited by

Patent Information

Authority / Receiving Office
CN Β· China
Patent Type
Patents(China)
Current Assignee / Owner
AECC SHENYANG ENGINE RES INST
Filing Date
2023-03-15
Publication Date
2026-06-09

AI Technical Summary

Technical Problem

Existing technologies lack a systematic, practical, and scientifically rigorous method for evaluating the microstructure damage of coatings on single-crystal high-pressure turbine blades, resulting in large errors in evaluation results and making it difficult to accurately predict differences in service temperature and stress.

Method used

By determining the various operating conditions of the actual single-crystal high-pressure turbine blades in service, a blade simulation component was designed and manufactured for creep interruption testing. Creep interruption test data was obtained, and damage maps and quantitative characterization of the coating and coating-substrate interface were established. The damage maps of the coating and coating-substrate interface of the actual blades in service were compared, and the temperature and stress of the closest simulation component were selected for damage assessment.

Benefits of technology

This method enables a comprehensive and accurate evaluation of the coating structure damage of single-crystal high-pressure turbine blades, improving the accuracy and reliability of damage assessment.

✦ Generated by Eureka AI based on patent content.

Smart Images

  • Figure CN116223048B_ABST
    Figure CN116223048B_ABST
Patent Text Reader

Abstract

The application belongs to the field of aero-engine design, and is a service damage evaluation method for single crystal high-pressure turbine working blades. The method comprises the following steps: firstly, determining the stress and temperature range of each working condition of the actual service single crystal high-pressure turbine working blades; secondly, designing and manufacturing a plurality of blade simulation pieces corresponding to the stress and temperature range of the different working conditions of the actual service single crystal high-pressure turbine working blades to perform a creep interruption test, so as to obtain the corresponding relationship between different temperature-stress and coating, coating-substrate interface microstructure damage; thirdly, comparing the interface microstructure damage atlas and the main phase content with the standard atlas of the blade simulation pieces under different temperatures and stress degrees, and selecting the temperature and stress of the blade simulation piece closest to the actual service single crystal high-pressure turbine working blades as the temperature and stress of the sampling position of the actual service single crystal high-pressure turbine working blades; and finally, evaluating the coating microstructure damage and performance degradation degree, so that the coating microstructure damage degree of the service single crystal high-pressure turbine working blades can be comprehensively and truly evaluated.
Need to check novelty before this filing date? Find Prior Art