Development and Improvement of the High-Pressure Turbine Cooled Blade Design

Numerical modeling to obtain the thermal state of cooled working blades and blades refinement is an integral process of modern gas turbine engine design since the issue of cooling at the gas temperature at the combustion chamber outlet of more than 1800-2000K becomes one of the key issues. To ensure the specified parameters of turbine operation in the process of its design it is necessary to use reliable calculation models. This article presents the algorithm of calculation model formation for determining the thermal state of the working blade of a high-temperature high-pressure gas turbine in the Ansys software package. The process of preparation of geometric and grid models is described, boundary conditions used for project setup in Ansys CFX Pre are given. The method of determining the cooling efficiency factor using Ansys CFX Post is given. Temperature and cooling efficiency distributions over the surfaces of the cooled blade are obtained. The process of blade improvement is shown. Average values of the cooling efficiency coefficient for the designed blade at different cooling air flow rates were compared with statistical data. Based on the comparison, it is concluded that the working blade considered in the paper corresponds to the current level of cooling efficiency.