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A platform for research: civil engineering, architecture and urbanism
Turbine guide blade of aero-engine capable of being used for long-life service at 1300 DEG C and preparation method of turbine guide blade
The invention discloses an aero-engine turbine guide blade capable of being used for long-life service at the temperature of 1300 DEG C and a preparation method of the aero-engine turbine guide blade. The preparation method comprises the steps that a SiC/SiC composite material is adopted for preparing the turbine guide blade with a complex appearance structure, and a Si/mullite/BSAS environment barrier coating is prepared on the surface of the SiC/SiC turbine guide blade with the complex structure appearance; by means of the matching effect of the structure and the coating, the problem that the service life of the turbine guide blade is short in the 1300 DEG C gas environment is solved, the problems that the coating is discontinuous, uneven and prone to stripping due to the fact that the SiC/SiC turbine guide blade and the environment barrier coating are prepared and cut are solved, the high-temperature working stability of the Si/mullite/BSAS-SiC/SiC turbine guide blade is effectively improved, and the service life of the Si/mullite/BSAS-SiC/SiC turbine guide blade is effectively prolonged.
本发明公开了一种可用于1300℃长寿命服役的航空发动机涡轮导向叶片及其制备方法，其制备方法为采用SiC/SiC复合材料制备具有复杂外形结构的涡轮导向叶片，并在具有复杂结构外形的SiC/SiC涡轮导向叶片表面制备Si/mullite/BSAS环境屏障涂层，通过结构与涂层的配合作用，解决了涡轮导向叶片在1300℃燃气环境下服役寿命短的问题，避免了SiC/SiC涡轮导向叶片与环境屏障涂层制备割裂导致的涂层不连续、不均匀、易剥落的问题，有效提高了Si/mullite/BSAS‑SiC/SiC涡轮导向叶片的高温工作稳定性与服役寿命。
Turbine guide blade of aero-engine capable of being used for long-life service at 1300 DEG C and preparation method of turbine guide blade
The invention discloses an aero-engine turbine guide blade capable of being used for long-life service at the temperature of 1300 DEG C and a preparation method of the aero-engine turbine guide blade. The preparation method comprises the steps that a SiC/SiC composite material is adopted for preparing the turbine guide blade with a complex appearance structure, and a Si/mullite/BSAS environment barrier coating is prepared on the surface of the SiC/SiC turbine guide blade with the complex structure appearance; by means of the matching effect of the structure and the coating, the problem that the service life of the turbine guide blade is short in the 1300 DEG C gas environment is solved, the problems that the coating is discontinuous, uneven and prone to stripping due to the fact that the SiC/SiC turbine guide blade and the environment barrier coating are prepared and cut are solved, the high-temperature working stability of the Si/mullite/BSAS-SiC/SiC turbine guide blade is effectively improved, and the service life of the Si/mullite/BSAS-SiC/SiC turbine guide blade is effectively prolonged.
本发明公开了一种可用于1300℃长寿命服役的航空发动机涡轮导向叶片及其制备方法，其制备方法为采用SiC/SiC复合材料制备具有复杂外形结构的涡轮导向叶片，并在具有复杂结构外形的SiC/SiC涡轮导向叶片表面制备Si/mullite/BSAS环境屏障涂层，通过结构与涂层的配合作用，解决了涡轮导向叶片在1300℃燃气环境下服役寿命短的问题，避免了SiC/SiC涡轮导向叶片与环境屏障涂层制备割裂导致的涂层不连续、不均匀、易剥落的问题，有效提高了Si/mullite/BSAS‑SiC/SiC涡轮导向叶片的高温工作稳定性与服役寿命。
Turbine guide blade of aero-engine capable of being used for long-life service at 1300 DEG C and preparation method of turbine guide blade
一种可用于1300℃长寿命服役的航空发动机涡轮导向叶片及其制备方法
CAO XINXIN (author) / LI JIANZHANG (author) / ZHANG ZIQI (author) / CHENG LAIFEI (author)
2023-04-28
Patent
Electronic Resource
Chinese
Aero-engine turbine blade life assessment using the Neu/Sehitoglu damage model
| British Library Online Contents | 2014
Aero-engine turbine blade life assessment using the Neu/Sehitoglu damage model
| British Library Online Contents | 2014
Aero-engine turbine blade life assessment using the Neu/Sehitoglu damage model
| British Library Online Contents | 2014