Development of Numerical Methods for Modeling Aerodynamic Forces on Turbine Blades

In operation, the flow of gas to the working blades is not stationary due to the existence of an edge trace when the gas flow passes through the inter-blade channels of the guide vanes. This causes a variable aerodynamic force, which is periodically repeated with high frequency. In addition, the aerodynamic loads on the working blades are not evenly distributed since the aerodynamic profile of the blade varies along the length of the blade. All these values cause the complexity of mathematical modeling of aerodynamic forces and the assessment of their effect on the dynamic and strength characteristics of the turbine blades. To solve this problem, the work is devoted to the creation and development of numerical methods based on the blade element theory, Fourier series expansion and the time discretization method. As a result, a diagram of the distribution and magnitude of aerodynamic loads acting on the working blades, taking into account their changes in time and length of the blade, is presented. The paper describes the algorithm required to configure the model in Ansys Workbench to study the aerodynamics of a turbomachine compressor. The convergence of the dimension of the computational grid is considered, which must be carried out before detailed modeling to obtain accurate solutions to the problem of computational fluid dynamics.