Structural reliability analysis of an aeroengine 2nd-stage compressor disk is presented.
对某型发动机压气机第2级轮盘进行了结构可靠性分析。
Low cycle multiaxial fatigue failure is the main failure mode of aeroengine compressor disk.
低循环多轴疲劳失效是航空发动机低压压气机轮盘的主要失效形式。
The basic fatigue failure characteristics have been analyzed according to the stress analysis and simulation test under inhomogeneous swallowtail between compressor disk and blade.
分析了非均匀接触下燕尾形榫头连接的应力状态，并借助于模拟试验，提出了非均匀接触导致疲劳破坏的基本痕迹特征。
The formation of vane-integrated disk used in high-pressure compressor of turbine engine is simulated and analyzed with the finite element method (FEM) on the platform of software DEFORM 3d.
在DEFORM3d有限元分析软件平台上，对高压压气机整体叶盘的锻压成形过程进行了模拟与分析。
The formation of vane-integrated disk used in high-pressure compressor of turbine engine is simulated and analyzed with the finite element method (FEM) on the platform of software DEFORM 3d.
在DEFORM3d有限元分析软件平台上，对高压压气机整体叶盘的锻压成形过程进行了模拟与分析。
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