大展弦比叶栅气弹响应的数值研究  

Numerical Investigation of High-aspect-ratio Blade Cascade Aeroelastic Response

作　　者：李密[1] 吴虎[1] 王征[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《科学技术与工程》2010年第34期8471-8475,共5页Science Technology and Engineering

摘　　要：对大型承载飞机普遍使用的大展弦比发动机转子叶栅,使用有限单元方法(FEM)建立叶栅模型,然后对叶栅的结构及旋转状态下的动态特性进行分析。同时在不同转速下计算模态和振动频率,对等效应力分布、等效应变分布和整体形变进行求解,并由此绘制了叶栅共振曲线的坎贝尔图,该图显示了固有振动频率和振动响应条件下的共振激励。最后结合在不同转速下的流场稳态计算结果,对叶栅进行在气动力作用下动态响应分析。该模型的气动弹性分析结果表明,基于有限单元法的静压力计算、动频分析方法,在大展弦比叶栅的优化设计参考和振动安全诊断等方面可以提供很大的帮助。The high-aspect-ratio rotor cascade used widely in the jumbo jet is modeled on finite element method（FEM）,and the modal and vibration frequency in the different rotational speed are calculated.Then it simulates equivalent stress distribution,equivalent elastic strain distribution and total deformation.Campbell diagram is generated on the simulation,which displays the inherent vibration frequency and shock excitation in the resonance vibration.Finally,the dynamic response study analyzes rotor cascade under aerodynamic force with the steady state results of the flow field calculations.The aeroelastic analysis results show the algorithms of the static pressure and the dynamic frequency analysis based on finite element method can be effectively on reference for optimization design and vibration safeness verification for this fan blade cascade.

关 键 词：有限单元法 动态特性 模态 共振 气动弹性 

分 类 号：V231.96[航空宇航科学与技术—航空宇航推进理论与工程]