Design And Finite Element Analysis Of 2.5D Lattice Structures For Internal Air-Cooled Gas Turbine Blades

Making lightweight designs without changing the properties of materials is very important for aviation. In addition, effective cooling of metallic jet engine parts operating at high temperatures, such as gas turbine blades, is necessary to increase the efficiency of the engine and extend the service life of the gas turbine blade. In this regard, in parallel with the developments in additive manufacturing, lattice structures that provide both significant weight reduction and large surface area for effective cooling have recently started to be a hot topic. In this study, square, triangular and hexagonal 2.5D lattice structures were designed for the internal air-cooled gas turbine blade and analyzed by the finite element method. A conventional gas turbine blade with air cooling channels was used as a reference. The results showed that up to 17.14% weight reduction and up to 93.43% air cooling surface area increase can be achieved in the gas turbine blade thanks to lattice designs. When the results of maximum stress, FOS and deformation in turbine blades, as well as weight reduction and surface area increase, were evaluated together, it was concluded that the most suitable 2.5D lattice design was hexagonal.