摘要
针对大涵道比航空发动机工作过程中常见的鸟撞问题,基于MSC.Dytran软件,研究了实体元平板鸟撞流固耦合数值模拟方法;在此基础上,建立了鸟撞实体元空心叶片转子级有限元模型,模拟了叶片遭受鸟撞发生失效的过程,并进行相应计算。结果表明:鸟体密度、叶片的屈服应力和硬化模量对叶片初始撞击应力响应峰值的影响较大,且屈服应力和硬化模量的增加分别会提高和减小恒定流动的应力峰值;鸟体体积模量对叶片应力响应的影响较小;叶片的弹性模量的增加对叶片初始撞击应力响应峰值的影响较小,但会显著提高恒定流动的应力峰值。
Aimng at the frequent bird impact issue occured at the working process ofthe high bypass ratio aeroengine, the fluid-solid coupling numerical simulation method of bird impacts solid-element fiat was studied by MSC.Dytran software. The rotor stage finite element model of the bird impact solid-element hollow blades was built , the failure process of the blade impacted by bird was simulated and the corresponding calculations were conducted. The results show the bird density, yield stress and hardening modulus of the blades have great influence on the peak stress of the blades initial impact stress responses. The increasing of yield stress will increase the peak stress of the steady flow and the raising of the hardening modulus will decrease the peak stress of the steady flow. The bird bulk modulus have small influence on the stress response of the blades. The increasing of the blades elastic modulus has little influence on the peak stress of the blades initial impact stress responses, but will increase the peak stress of steady flow remarkably. The failure process of the blades after bird impact was simulated finally.
出处
《航空发动机》
2013年第2期70-74,89,共6页
Aeroengine
基金
"凡舟"青年科研基金(20080401)资助
关键词
鸟撞
实体元
空心叶片
流固耦合
数值模拟
航空发动机
bird impact
solid element
hollow blade
fluid-solid coupling
numerical simulation
aeroengine
