Design, fabrication and testing of ceramic-matrix composite turbine blisk

被引：0

作者：

Liu X. ^{[1
]}

Xu Y. ^{[2
]}

Li J. ^{[2
]}

Luo X. ^{[2
]}

Guo X. ^{[2
]}

Hu X. ^{[3
]}

Cao X. ^{[4
]}

Li L. ^{[5
]}

Liu C. ^{[1
]}

Dong N. ^{[1
]}

Liu Y. ^{[1
]}

机构：

[1] School of Materials Science and Engineering, Northwestern Polytechnical University, Xi′an

[2] Hunan Aviation Powerplant Research Institute, Aero Engine Corporation of China, Zhuzhou

[3] School of Aircraft Engineering, Nanchang Hangkong University, Nanchang

[4] School of Materials Science and Engineering, Wuhan University of Technology, Wuhan

[5] College of Civil Aviation, Nanjing University of Aeronautics and Astronautics, Nanjing

来源：

Fuhe Cailiao Xuebao/Acta Materiae Compositae Sinica | 2023年 / 40卷 / 03期

基金：

中国国家自然科学基金;

关键词：

engine bench test; environmental barrier coatings (EBCs); gas turbine engines; over rotation test; SiC/SiC; spider web structure (SWS); turbine blisk;

D O I：

10.13801/j.cnki.fhclxb.20220407.001

中图分类号：

学科分类号：

摘要：

Turbine rotor is the key component of gas turbine engines. Design, fabrication, and experimental verification of SiC/SiC turbine blisk were investigated. The Spider Web Structure (SWS) SiC preform was used as the reinforcement in turbine blisk. The BN interphase and SiC matrix were deposited on the surface of the SWS SiC fiber preform, respectively. The SiC/SiC turbine blisk was machined by "on-line processing" to form a turbine bisk that meets the design requirements. The environmental barrier coatings (EBCs) were prepared on the surface of SiC/SiC turbine blisk using the atmospheric plasma spraying (APS) method. The CT scan was conducted to characterize the internal defects in SiC/SiC turbine blisk. The mechanical performance evaluation, over rotation test and engine bench test were performed, respectively. The maximum failure strength approached 300 MPa. During the over rotation test, when the rotating speed reached n=104 166 r/min, the blade in the turbine blisk broke; and when the rotating speed reached n=108 072 r/min, the disk in the turbine blisk broke. During the engine bench test, low cyclic fatigue of N=994 cyclic with maximum speed nmax=60 000 r/min and N=100 cyclic with maximum speed nmax= 70 000 r/min were completed. On January 1, 2022, the SiC/SiC turbine blisk successfully completed the first flight test in Zhuzhou, which is also the first flight test of the domestic SiC/SiC rotor assembly platform and verified the feasibility of SiC/SiC turbine rotor application in gas turbine engines. © 2023 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.

引用

页码：1696 / 1706

页数：10

共 39 条

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