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。
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/SiCcomposite 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.
作者
石多奇
刘长奇
程震
杨锐
梁湘华
栗尼娜
杨晓光
国怡泉
SHI Duoqi;LIU Changqi;CHENG Zhen;YANG Rui;LIANG Xianghua;LI Nina;YANG Xiaoguang;GUO Yiquan(School of Energy and Power Engineering,Beihang University,Beijing 100191,China;Beijing Key Laboratory of Aero-Engine Structure and Strength,Beihang University,Beijing 100191,China;Beijing Institute of Space Launch Technology,China Aerospace Science and Technology Corporation,Beijing 100076,China;Guiyang Engine Design Research Institute,Aero Engine Corporation of China,Guiyang 550000,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2023年第1期1-12,共12页
Journal of Aerospace Power
基金
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。
