SiC/SiC复合材料涡轮叶片结构设计及静强度评价

石多奇; 刘长奇; 程震; 杨锐; 梁湘华; 栗尼娜; 杨晓光; 国怡泉

doi:10.13224/j.cnki.jasp.20210531

SiC/SiC复合材料涡轮叶片结构设计及静强度评价

doi: 10.13224/j.cnki.jasp.20210531

石多奇^{1, 2,},
刘长奇^1,,
程震^3,*, ,,
杨锐⁴,
梁湘华⁴,
栗尼娜⁴,
杨晓光^{1, 2},
国怡泉¹

1.
北京航空航天大学能源与动力工程学院，北京 100191
2.
北京航空航天大学航空发动机结构强度北京市重点实验室，北京 100191
3.
中国航天科技集团有限公司北京航天发射技术研究所，北京 100076
4.
中国航发贵阳发动机设计研究所，贵阳 550000

基金项目: 国家自然科学基金（51772009，51911530201）；北京航空航天大学博士生卓越学术基金

详细信息

作者简介:
石多奇（1975-），男，教授、博士生导师，博士，主要从事航空发动机结构强度、疲劳和蠕变、高温材料本构关系研究

通讯作者:
程震（1990-），男，工程师，博士，主要从事复合材料力学行为研究与结构设计工作。E-mail：zhencheng@buaa.edu.cn

中图分类号: V231.91
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出版历程
- 收稿日期: 2021-09-22
- 网络出版日期: 2022-11-10

Structural design and static strength evaluation of SiC/SiC-composite turbine blade

SHI Duoqi^{1, 2
,},
LIU Changqi^1
,,
CHENG Zhen^{3,*
, ,},
YANG Rui⁴,
LIANG Xianghua⁴,
LI Nina⁴,
YANG Xiaoguang^{1, 2},
GUO Yiquan¹

1.
School of Energy and Power Engineering，Beihang University，Beijing 100191，China
2.
Beijing Key Laboratory of Aero-Engine Structure and Strength， Beihang University，Beijing 100191，China
3.
Beijing Institute of Space Launch Technology， China Aerospace Science and Technology Corporation，Beijing 100076，China
4.
Guiyang Engine Design Research Institute，Aero Engine Corporation of China，Guiyang 550000，China

摘要

摘要:
以高温合金低压涡轮叶片为原型，研究了采用SiC/SiC复合材料进行该型涡轮叶片结构设计的可行性。完成了SiC/SiC叶片的宏观设计、榫头设计和细节设计。计算分析了金属和复合材料涡轮叶片的变形和应力特点。对按设计制备的SiC/SiC叶片开展了拉伸强度测试，并在试验中监测了叶片的应变。计算结果表明：SiC/SiC叶片在额定状态下的伸长量低于原金属叶片；叶身叶根与缘板过渡处应力水平最高，但低于SiC/SiC复合材料的拉伸强度；榫头榫颈处有发生局部剪切破坏的风险。试验结果表明：该SiC/SiC叶片的断裂明显呈现出拉伸失效模式，以断裂转速计算的静强度储备系数约为1.3；所采用的SiC/SiC叶片结构设计方法可行，所制备的复合材料叶片也顺利通过了实验室条件下的静强度考核。
- 涡轮叶片 /
- 陶瓷基复合材料 /
- 结构设计 /
- 数字图像相关(DIC)法 /
- 静强度
Abstract:
A superalloy low-pressure turbine blade was taken as a reference, and the feasibility of SiC/SiC composites for the structural design of this type of turbine blade was studied. The macro design, dovetail design and detail design of the blade were successively conducted. The deformation and stress characteristics of the metal and composite turbine blades were calculated. Tensile tests of the turbine blades prepared according to the above design were carried out, and the deformation of blade body and dovetail was monitored during the tests. The calculation results showed that the elongation of the SiC/SiC-composite blade was lower than that of original metal blades under rated condition. The stress level at the transition between blade root and listrium was relatively high, but lower than the ultimate tensile strength of the SiC/SiC composites. There was a risk of local shear failure at the neck of the dovetail. The results of the experiments indicated that the eventual failure of the blades distinctly exhibited a tensile failure mode, and the coefficient of the margin of strength calculated by the rotate speed at fracture was about 1.3. This structural design method adopted proved feasible, and the SiC/SiC-composite blades successfully passed the static strength tests under the laboratory condition.
- turbine blade /
- ceramic matrix composites /
- structural design /
- digital image correlation (DIC) method /
- static strength

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图 1 三维四向编织SiC/SiC复合材料的内部细观结构

Figure 1. Internal meso-structure of the three-dimensional 4-directional braided SiC/SiC composites

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图 2 微观尺度和细观尺度的代表性体积单元的有限元模型

Figure 2. Finite element models of micro RVE and macro RVE

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图 3 燕尾型榫头可用设计空间示意图

Figure 3. Schematic diagram of available space for dovetail design

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图 4 参数化的榫头二维截面几何模型

Figure 4. Two-dimensional parameterized geometric model of dovetail section

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图 5 φ₂和R₃对最大应力的影响

Figure 5. Influence of φ₂ and R₃ on maximum stress

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图 6 榫头和榫槽的最终设计方案

Figure 6. Final design scheme of dovetail and groove

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图 7 SiC/SiC涡轮叶片局部细节调整

Figure 7. Adjustment of local details of the SiC/SiC turbine blade

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图 8 有限元分析前处理

Figure 8. Pre-processing in the finite element analysis

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图 9 SiC/SiC涡轮叶片和金属叶片的径向位移

Figure 9. Radial displacements of the SiC/SiC turbine blade and metal blades

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图 10 SiC/SiC涡轮叶片径向应力

Figure 10. Radial stress of the SiC/SiC turbine blade

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图 11 SiC/SiC榫头的局部应力

Figure 11. Local stress of the SiC/SiC dovetail

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图 12 SiC/SiC榫头和榫槽的周向应力分布

Figure 12. Circumferential stress of the SiC/SiC dovetail and groove

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图 13 涡轮盘Mises应力分布

Figure 13. Mises stress of the turbine disk

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图 14 涡轮叶片拉伸测试所使用的试验系统

Figure 14. Experimental system used in the tensile test of the turbine blade

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图 15 SiC/SiC涡轮叶片的试验拉伸曲线

Figure 15. Experimental tensile curves of the SiC/SiC turbine blades

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图 16 SiC/SiC涡轮叶片拉伸断口

Figure 16. Fracture surfaces of the SiC/SiC turbine blades

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图 17 SiC/SiC涡轮叶片冷态额定转速下纵向应变

Figure 17. Longitudinal strain of the SiC/SiC turbine blade at cold rated speed

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图 18 涡轮叶片A和B在不同载荷下的应变场

Figure 18. Strain fields of the turbine blades A and B at different loads

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图 19 叶片B榫头端面应变场模拟结果和试验值的对比

Figure 19. Comparison between simulated results and experimental values of strain fields at the dovetail end face of blade B

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图 20 叶片A断口的SEM图

Figure 20. SEM image of the fracture surface of blade A

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表 1 α₁₁和α₂₂预测值和试验值的比较

Table 1. Comparison of predicted and experimental results of α₁₁ and α₂₂ 10⁻⁶ ℃⁻¹

参数	数值
α₁₁预测值	2.498
α₂₂预测值	2.391
α₁₁试验值1	2.40
α₁₁试验值2	2.54
α₁₁试验值3	3.45

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表 2 SiC/SiC复合材料的弹性常数和强度数据^[23-24]

Table 2. Elastic constants and strength data of the SiC/SiC composites^[23-24]

弹性常数	数值	材料强度	数值
E₁₁/GPa	107	T₁₁/MPa	150
E₂₂/GPa	89	T₂₂/MPa	100
G₁₂/GPa	38.2	C₁₁/MPa	100
G₂₃/GPa	38.6	C₂₂/MPa	150
ν₁₂	0.239	S_12,s/MPa	100
ν₂₃	0.27	S_23,s/MPa	50

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表 3 SiC/SiC涡轮叶片离心应力初步预测

Table 3. Primary prediction about the centrifugal stress of the SiC/SiC turbine blade

参数	数值
叶身部位体积/cm³	19.34
叶片总体积/cm³	37.96
叶身部位质心半径/mm	275.5
叶片质心半径/mm	239.0
叶身部位离心力/kN	16.7
叶片总离心力/kN	28.4
叶根截面积/cm²	250.3
叶根名义拉伸应力/MPa	66.6

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