陶瓷基复合材料涡轮叶盘设计、制备与考核验证

刘小冲; 徐友良; 李坚; 罗潇; 郭小军; 胡晓安; 曹学强; 李龙彪; 刘持栋; 董宁; 刘永胜

doi:10.13801/j.cnki.fhclxb.20220407.001

陶瓷基复合材料涡轮叶盘设计、制备与考核验证

doi: 10.13801/j.cnki.fhclxb.20220407.001

1.
西北工业大学　材料学院，西安 710072
2.
中国航发湖南动力机械研究所，株洲 412000
3.
南昌航空大学　飞行器工程学院，南昌 330063
4.
武汉理工大学　材料科学与工程学院，武汉 430070
5.
南京航空航天大学　民航学院，南京 211106

基金项目: 国家自然科学基金重大研究计划重点支持项目(92060202)；国家自然科学基金(52172100)

详细信息

通讯作者:
徐友良，博士，研究员，研究方向为发动机结构与强度　E-mail：youliang_xu@163.com

中图分类号: TB332
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出版历程
- 收稿日期: 2022-03-07
- 修回日期: 2022-03-25
- 录用日期: 2022-03-31
- 网络出版日期: 2022-04-08
- 刊出日期: 2023-03-15

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

1.
School of Materials Science and Engineering, Northwestern Polytechnical University, Xi′an 710072, China
2.
Hunan Aviation Powerplant Research Institute, Aero Engine Corporation of China, Zhuzhou 412000, China
3.
School of Aircraft Engineering, Nanchang Hangkong University, Nanchang 330063, China
4.
School of Materials Science and Engineering, Wuhan University of Technology, Wuhan 430070, China
5.
College of Civil Aviation, Nanjing University of Aeronautics and Astronautics, Nanjing 211106, China

Funds: Project Supported by the Major Research Plan of the National Natural Science Foundation of China (92060202); National Natural Science Foundation of China (52172100)

摘要

摘要: 涡轮转子是燃气涡轮发动机的核心部件。针对SiC/SiC涡轮叶盘设计、制备与考核验证开展研究，采用蛛网仿形(SWS)SiC纤维预制体作为涡轮叶盘的增强体，预制体表面分别沉积BN界面相与SiC基体，通“在线加工”方式对SiC/SiC涡轮叶盘分别进行粗加工和精加工，采用大气等离子喷涂方法制备环境障碍涂层，形成满足设计要求的涡轮叶盘。采用CT对SiC/SiC涡轮叶盘进行无损检测，表征叶盘内部缺陷分布。针对制备的SiC/SiC涡轮叶盘开展性能评价、超转试验、台架试验等考核验证，研究表明：SiC/SiC涡轮叶盘最大破坏强度达到300 MPa；在室温超转试验中，当转速达到n=104166 r/min时，叶片发生断裂，当转速达到n=108072 r/min时，轮体发生破裂；在发动机台架试验中，累积完成了N=994次最高转速n_max=60000 r/min的循环载荷及N=100次最高转速n_max=70000 r/min的循环载荷试车考核。2022年1月1日，SiC/SiC涡轮叶盘在株洲成功完成了首次飞行试验验证，这也是国内陶瓷基复合材料转子首次配装平台的空中飞行试验，验证了SiC/SiC涡轮转子在航空发动机上应用的可行性。
- SiC/SiC /
- 涡轮叶盘 /
- 蛛网仿形(SWS) /
- 环境障碍涂层(EBCs) /
- 超转试验 /
- 台架试验 /
- 燃气涡轮发动机
Abstract: 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=104166 r/min, the blade in the turbine blisk broke; and when the rotating speed reached n=108072 r/min, the disk in the turbine blisk broke. During the engine bench test, low cyclic fatigue of N=994 cyclic with maximum speed n_max=60000 r/min and N=100 cyclic with maximum speed n_max=70000 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.
- SiC/SiC /
- turbine blisk /
- spider web structure (SWS) /
- environmental barrier coatings (EBCs) /
- over rotation test /
- engine bench test /
- gas turbine engines

HTML全文

图 1 SiC/SiC涡轮叶盘SiC纤维预制体设计方案

Figure 1. Design of SiC fiber preform in SiC/SiC turbine blisk

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图 2 蛛网仿生结构SiC/SiC涡轮叶盘预制体定型

Figure 2. Spider web structure fiber perform of SiC/SiC turbine blisk

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图 3 SiC纤维表面BN界面相检测取样及厚度测试

Figure 3. Sampling and thickness measurement of BN interphase on SiC fiber surface

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图 4 SiC纤维预制体SiC基体致密化：(a) 预制体SiC沉积；(b) 高温模具脱除后的SiC预制体

Figure 4. SiC matrix densification on the SiC fiber preform: (a) Deposition of SiC matrix; (b) SiC preform after removing mold

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图 5 SiC基体沉积纯度检验结果

Figure 5. Purity test result of the SiC matrix

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图 6 SiC/SiC涡轮叶盘在线加工成型过程

Figure 6. On-line machining process of SiC/SiC turbine blisk

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图 7 环境障碍涂层(EBCs)截面形貌SEM图像

Figure 7. Cross-section SEM image of environmental barrier coatings (EBCs)

R—La, Nd, Sm, Gd, Yb; CMC—Ceramic-matrix composite

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图 8 EBCs-SiC/SiC经过1350℃空气气氛保温300 h的三点弯曲载荷-位移曲线

Figure 8. Three-point bending load-displacement curve of EBCs-SiC/SiC after holding at 1350℃ in air atmosphere for 300 h

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图 9 EBCs-SiC/SiC三点弯曲后断口形貌 (a) 和截面形貌 (b)

Figure 9. Fracture surface (a) and cross-section surface (b) of EBCs-SiC/SiC after three-point flexure testing

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图 10 EBCs-SiC/SiC表面烧蚀温度曲线 (a) 和表面烧蚀2000次后的外观形貌 (b)

Figure 10. Surface ablation temperature curve (a) and morphology after 2000 times of surface ablation (b) of EBCs-SiC/SiC

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图 11 SiC/SiC涡轮叶盘CT检测图

Figure 11. CT detection of SiC/SiC turbine blisk

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图 12 SiC/SiC涡轮叶盘CT数据3D重构分析

Figure 12. 3D reconstruction analysis of SiC/SiC turbine disk CT data

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图 13 SiC/SiC在1400^oC真空环境下的拉伸应力-应变曲线

Figure 13. Tensile stress-strain curve of SiC/SiC composite at 1400^oC in vacuum atmosphere

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图 14 SiC/SiC涡轮叶盘性能评价方法：(a) 随炉圆环试样；(b) 缺口圆环试样；(c) 拉伸断裂测试；(d) 断裂试样；(e) 有限元仿真缺口圆环试样断裂；(f) 涡轮叶盘应力分布

Figure 14. Evaluation of SiC/SiC turbine blisk performance: (a) Circular specimen; (b) Notched circular specimen; (c) Tensile fracture test; (d) Fracture specimen; (e) Finite element simulation of notched circular specimen fracture; (f) Turbine blisk stress distribution

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图 15 SiC/SiC涡轮叶盘超转实验：(a)旋转试验台；(b) CT检测系统；(c) 涡轮叶盘试验件；(d) 激光测频系统

Figure 15. SiC/SiC turbine blisk over rotation experiment: (a) Rotation test equipment; (b) CT detection system; (c) Turbine blisk; (d) Laser frequency measurement system

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图 16 SiC/SiC涡轮叶盘室温超转试验结果：(a) 叶片飞断；(b) 超转破坏后的残骸；(c) 碎块体视镜照片；(d) 碎块体扫SEM图像

Figure 16. Results of over rotation test of SiC/SiC turbine blisk at room temperature: (a) Blade flying off; (b) Fragments after over rotation damage; (c) Fragment stereoscopic photo; (d) Fragment SEM image

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图 17 (a) 发动机试车台；(b) 安装在发动机内的SiC/SiC涡轮叶盘；(c) SiC/SiC原始涡轮叶盘；(d) EBCs-SiC/SiC涡轮叶盘；(e) N=994次n=60000 r/min试验后的轮盘表面状态；(f) 表面氧化形貌；((g)~(h)) 轮盘表面氧化产物形貌；(i) 叶片掉块；(j) CT切片；(k) CT切片

Figure 17. (a) Engine test bench; (b) SiC/SiC turbine blisk assembled in the test engine; (c) Original SiC/SiC turbine blisk; (d) EBCs-SiC/SiC turbine blisk; (e) EBC-SiC/SiC turbine blisk after N=994 tests at n=60000 r/min; (f) Surface morphology of SiC/SiC turbine blisk after test; ((g)-(h)) Surface morphology of oxidation products ; (i) Damage in the blade; (j) CT section; (k) CT section

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图 18 (a) SiC/SiC涡轮叶盘转速曲线；(b) SiC/SiC涡轮叶盘排气温度和油耗曲线

Figure 18. (a) Rotation curves of SiC/SiC turbine blisk; (b) Exhaust temperature and fuel consumption curves of SiC/SiC turbine blisk

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图 19 SiC/SiC涡轮叶盘飞行考核试验

Figure 19. Flight testing of SiC/SiC turbine blisk

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表 1 叶片频率衰退范围统计表

Table 1. Statistical of blade frequency degradation range

Degradation range Number of blades

0.0%-0.5% 0
0.5%-1.0% 0
1.0%-1.5% 4
1.5%-2.0% 13
2.0%-2.5% 2
2.5%-3.0% 2
3.0%-3.5% 2
3.5%-4.0% 0
4.0%-4.5% 0
4.5%-5.0% 1

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