Axial turbomachines, commonly found in aircraft engines such as turbojets or turbofans, typically incorporate sequential pairs of rotating and stationary blades, named stages.The turbine located downstream of the combustion chamber is usually made of one or a few stages. It is designed to turn the intense heat and pressure contained in the exhaust gases into both thrust and torque power. The former is provided by high-momentum gas exhaust while the latter is used to make the turbomachine rotate around its shaft. Both rotating and stationary blades, also referred to as rotor and stator blades, must be able to endure the extreme pressure and temperature conditions within the turbine. A compressor bleed air system provides cooling airflow through internal ducts to reduce these thermal stresses and control blade deformation. In this video, the displacement, temperature, and stress in a model of a stator blade are evaluated using the Thermal Stress interface in COMSOL Multiphysics.
轴流式涡轮机常见于涡轮喷气发动机或涡轮风扇发动机等航空发动机，通常由连续成对的旋转叶片和固定叶片组成，称为“级”。位于燃烧室下游的涡轮机通常由一个或多个级组成，其功能是将废气中所含的高温和高压转化为推力和扭矩功率。推力来自高动量气体排放，而扭矩功率则用于推动涡轮机绕轴旋转。旋转叶片和固定叶片（又称动叶片和静叶片）必须能够承受涡轮机内的极端压力和温度条件。压缩机排气系统通过内部管道提供冷却气流，从而减少热应力并控制叶片变形。在本视频中，我们使用 COMSOL Multiphysics 的“热应力”接口计算静叶片模型中的位移、温度和应力。
