Thermal Stress Analysis of a Turbine Stator Blade

Duration: 6:10

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.

Chapter Selection

Select the Physics (0:22) Set Up the Geometry (0:48) Specify Material Properties (1:28) Define the Physics (1:50) Create the Mesh and Run the Simulation (4:48) Postprocess the Results (5:02)