摘要
根据疲劳、蠕变、热冲击损伤以及高周振动环境等效的原则,保证飞行载荷总谱和综合飞行剖面主循环数、次循环数、各载荷状态、各载荷状态持续时间相同,编制某涡轴发动机综合飞行剖面,为编制该发动机模拟任务持久试车谱、加速任务试车谱以及发动机零部件强度、寿命考核试验研究提供技术依据。首先根据飞行载荷总谱和使用环境确定三种飞行类别,选定综合飞行剖面的发动机工作参数,分别得到三种飞行类别主、次循环矩阵,进行归一化圆整处理。由时间分配谱统计各载荷状态的持续时间,进而编制综合飞行剖面。最后根据综合飞行剖面进行疲劳、蠕变和热冲击等损伤的误差分析。
According to the principle of equivalent fatigue, creep, thermal impact damage and high cycles vibration condition, namely the amounts of main loading cycles, the partial loading cycles, loading condition, loading duration are equal in general flight loading spectrum and composite flight profiles. The research derived one model of turbo-shaft aero engine＇ s composite flight profiles, which provides the technical besis for formulating the simulation mission equivalent test spectrum, the accelerated mission test spectrum and assessing the strength and life of the turbo-shaft aero engine components. Firstly, according to the general flight loading spectrum and using of circumstance, three flight forms are confirmed and parameters of aero engine are chosen for composite flight profiles. Secondly, main loading cycles and the partial loading cycles＇ matrixes of three flight forms are obtained respectively, subsequently, these matrixes are normalized and rounded. Thirdly, according to the time distribution spectrum, duration of loading conditions are calculated and composite flight profiles are derived. Finally, errors of fatigue, creep and thermal impact damage are analyzed for composite flight profiles.
出处
《机械强度》
EI
CAS
CSCD
北大核心
2006年第6期909-912,共4页
Journal of Mechanical Strength
关键词
载荷谱
综合飞行剖面
等效损伤
损伤误差
Loading spectra
Composite flight profiles
Equivalent of damage
Error of damage
