航空发动机压气机钛火燃烧产生的大量熔滴及其产物会造成钛合金机匣烧穿，并致使其非包容失效，危害巨大。基于钛合金熔滴烧蚀机理和激光点火技术探索压气机钛火包容性定量评价方法，建立以TC4钛合金机匣水平扩展、垂直滴落两种构型抗熔滴烧穿能力为特征参数的测试与评价方法，实现了模拟气流环境下钛火扩散传播行为以及失效临界条件的实验验证。结果表明：在垂直滴落构型下，钛合金熔滴烧穿机匣的机理在于滴落接触界面处形成的局部高度热量集中；受传热机制影响，钛合金机匣基底原子动能急速升高，形成贯穿性液相区，最终造成烧穿，即钛火非包容失效；而在水平扩展构型下，熔滴在水平移动时会受到一定的反向气流作用等机制影响，削弱扩展效应。当熔滴在重力或离心力等作用下长期黏附于机匣模拟件表面时，释放的热量足以烧穿钛合金机匣，其临界厚度在1.5~2 mm之间。

A large number of droplets and their products produced by titanium fire combustion in aeroengine compressor will cause burn through and non-inclusiveness failure of titanium alloy casing. This has shown great harm. In this study， a quantitative evaluation method for titanium fire inclusiveness of compressor was explored based on the mechanism of titanium alloy melt drop ablation and laser ignition technology. A test and evaluation method was established with the characteristic parameters of the melt drop penetration resistance of two configurations of TC4 titanium alloy casing， namely horizontal expansion and vertical drip. Meanwhile， the diffusion behavior of titanium fire and the critical failure conditions under simulated airflow environment were varified by experiments as well. Those results show that the mechanism of titanium alloy droplet burning through the casing lies in the local high heat concentration formed at the droplet contact interface. Under the action of heat transfer， the kinetic energy of the atoms in the base of the titanium alloy cartridge increases rapidly， forming a penetrating liquid phase， and finally causing burn-through， that is， titanium non-inclusiveness failure. When the droplet moves horizontally in the process of extended combustion， it will be affected by some mechanism such as reverse airflow， which will weaken the expansion effect. When the droplet is adhered to the surface of the casing simulation for a long time under the action of gravity or centrifugal force， the heat released is enough to burn through the titanium alloy casing. Its critical thickness is between 1.5-2 mm.