2D and 3D thermoelastic phenomena in double wall transpiration cooling systems for gas turbine blades and hypersonic flight

Double wall transpiration cooling (DWTC) systems allow the operating temperature of gas turbines to be increased beyond current levels, promising further enhancements in engine efficiency and a reduction fuel consumption emissions. Alongside outstanding performance DWTC systems, there are structural integrity implications that need evaluated. Our theoretical Finite Element (FE) analysis here determine thermal stresses arising range double configurations two-dimensional (2D) three-dimensional (3D) space. The 3D geometric effects spacing, thickness ratio, connecting pedestal spacing between walls interpreted based on considerations 2D idealisations. We highlight although an inner cool may essential for applying internal impingement system enhance its aerothermal performance, at same time increases compression hot outer wall, due kinematic constraint two must extend equally. As result, critical compressive can relieved by using thinner wall. study determines nominal stress fields drive concentrations associated local creep-plasticity-fatigue features such as effusion holes pedestals.