燃烧室复杂结构的热振特性研究  

Thermal-vibration Characteristics of Complex Combustor Structure

作　　者：邵康[1] 张静静[1] 董龙雷[1] 闫桂荣[1] 

机构地区：[1]西安交通大学机械结构强度与振动国家重点实验室,西安710049

出　　处：《装备环境工程》2015年第6期126-132,共7页Equipment Environmental Engineering

摘　　要：目的提高复杂飞行器结构在服役过程中的安全性和稳定性问题。方法以复杂结构燃烧室为例,从数值模拟和试验两方面入手,研究不同工况下结构的动力学参数随温度变化的规律。结果随着温度的升高,模态频率呈下降趋势,模态阻尼呈升高、下降再升高的趋势,加热对结构的模态振型无影响。结论对于自由-自由状态的燃烧室结构,在加热的过程中,影响模态频率下降的主要因素是弹性模量的变化,热应力和几何非线性的变化可以不考虑。同时通过开展燃烧室结构的自由-自由状态热模态试验验证了数值模拟方法的正确性。Objective To improve the safety and stability of the complex aircraft structure in the process of service.Methods Taking the engine combustor of complex aircraft as example, the changing patterns of dynamic parameters along with temperature under different working conditions were investigated numerically and experimentally. Results The results indicated that the modal frequency decreased and the mode damping first raised then fell and finally raised again with the increase of temperature, and heating had no influence on the mode shape of the structure. Conclusion For a free-free configuration combustor, the main cause of decrease in the modal frequency was the change of elastic modulus and the influence of thermal stress and geometric nonlinearity could be ignored in hot environment. Moreover,by conducting the thermal modal test on a free-free configuration combustor, the correctness of the numerical simulation method was verified.

关 键 词：燃烧室 热环境 振动特性 

分 类 号：TJ01[兵器科学与技术—兵器发射理论与技术] V416.4[航空宇航科学与技术—航空宇航推进理论与工程]