Kevlar织物缠绕增强机匣包容性研究

发布时间：2018-07-01 17:16

本文选题：航空发动机 + 机匣包容性　；参考：《浙江大学》2015年硕士论文

【摘要】：纤维织物缠绕增强风扇机匣作为轻质复合材料机匣的优秀代表,在国外大涵道比涡扇发动机中广泛应用,而国内尚处空白。为弥补这一空白,本文结合试验和数值仿真研究Kevlar织物缠绕增强机匣包容性,完成以下工作：(1)进行数值分析方法研究。建立两种Kevlar49平纹织物受圆柱形弹体冲击的数值模型,对比分析表明连续介质模型可以表现出织物整体破坏的宏观形式,能量预测误差较小,适合于工程应用。(2)拟定Kevlar织物缠绕增强模拟机匣旋转试验台包容性试验方案和测试系统,完成模拟机匣的设计与制作,设计榫槽连接的模拟轮盘和模拟叶片,校核试验转子系统的稳定性。(3)进行Kevlar织物缠绕增强机匣的叶片包容性试验和数值分析研究。在高速旋转试验台上完成10余次Kevlar缠绕增强机匣包容性试验,获得了不同层数和不同叶片飞断转速下Kevlar织物缠绕增强机匣的损伤形式和包容能力。并结合数值分析方法,研究了飞断叶片与机匣的撞击过程,分析Kevlar平纹织物的吸能能力。通过计算不同Kevlar层数下,机匣的包容转速和非包容转速,形成叶片飞断能量与Kevlar缠绕层厚度之间关系的经验性设计公式,指导Kevlar缠绕增强机匣的实际应用。(4)进行Kevlar织物缠绕增强机匣的实际应用研究。把Kevlar织物缠绕增强结构的设计特点应用于某型真实航空发动机机匣的改进设计,仿真结果发现其已满足包容性的需求。
[Abstract]:As an outstanding representative of lightweight composite casing, filament-wound reinforced fan casing has been widely used in large ducted ratio turbofan engines in foreign countries, but it is still blank in China. In order to make up for this gap, this paper combines the experimental and numerical simulation to study the inclusiveness of Kevlar fabric wound reinforced casing. The main works are as follows: (1) numerical analysis method is carried out. Two numerical models of Kevlar49 flat fabric subjected to impact of cylindrical projectile are established. The comparative analysis shows that the continuum model can show the macroscopic form of fabric failure, and the energy prediction error is small. It is suitable for engineering application. (2) to design the inclusive test scheme and test system of Kevlar fabric wound reinforced simulated casing rotating test rig, to complete the design and manufacture of simulation casing, to design simulated wheel disc and simulated blade with tenon and groove connection, The stability of nuclear test rotor system was checked. (3) the blade inclusiveness test and numerical analysis of Kevlar fabric wound reinforced casing were carried out. More than 10 inclusive tests of Kevlar wound reinforced casing were carried out on a high speed rotary test rig. The damage form and containment ability of Kevlar fabric wound reinforced casing were obtained under different layers and different blade flying speed. Combined with numerical analysis, the impingement process of fly-break blade and casing was studied, and the energy absorption ability of Kevlar plain fabric was analyzed. The empirical design formula of the relationship between the blade breakage energy and the thickness of Kevlar winding layer is obtained by calculating the containment and non-containment speed of the casing under different Kevlar layers. To guide the practical application of Kevlar wound reinforced casing. (4) to study the practical application of Kevlar fabric wound reinforced casing. The design features of Kevlar fabric wound reinforced structure are applied to the improved design of a real aero-engine casing. The simulation results show that it meets the inclusive requirements.
【学位授予单位】：浙江大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V250;V235.13

【共引文献】