Lakhasly

As a core component of the combustor, the gas turbine swirler's thermomechanical behavior directly impacts overall engine safety.The methodology involves obtaining the combustion flow field temperature distribution via Fluent, transferring the temperature field loads to the Steady-State Thermal and Static Structural modules, and performing thermal stress analysis on a 1/24 periodic symmetric model.Through one-way coupled numerical simulation implemented on the ANSYS Workbench platform, this study investigates the thermal stress of the swirler under typical operating conditions.

As a core component of the combustor, the gas turbine swirler’s
thermomechanical behavior directly impacts overall engine safety. Current research on
the fluid-thermal-structural coupling response of swirlers under actual combustion
conditions remains insufficient. Through one-way coupled numerical simulation
implemented on the ANSYS Workbench platform, this study investigates the thermal
stress of the swirler under typical operating conditions. The methodology involves
obtaining the combustion flow field temperature distribution via Fluent, transferring the
temperature field loads to the Steady-State Thermal and Static Structural modules, and
performing thermal stress analysis on a 1/24 periodic symmetric model. Key findings
include: (1) Under stable conditions, stress concentrations occur at blade roots and tips
while maintaining safe material limits; (2) Flashback conditions cause temperatures in
swirler blades and venturi surfaces to reach 1300°C with thermal stresses exceeding the
420 MPa material limit. This research establishes a methodology for evaluating swirler
thermomechanical performance under combustion conditions, providing theoretical
support for preventing hot-end component failures