Thermal stress analysis in annular duct resembling gas turbine transition piece

Flow field in annular duct resembling a typical transition piece of gas turbine engine is considered. Velocity and temperature distributions in the duct and casing are predicated numerically using the FLUENT CFD code. The control volume approach is introduced when discretizing the governing equations of flow. Thermal stress development in the outer casing of the duct is computed using ANSYS FEM code. It is found that radial acceleration of flow at duct entry region lowers temperature in the casing in this region. The gradual increase in pressure along the axial direction prevents flow separation and formation of secondary flow in the duct. Axial stress component is compressive and its magnitude is almost uniform along the axial direction. The magnitude of von-Mises stress is less than the elastic limit of the substrate material.