Optimization of the working process of a two-stage HPT of a modern GTE for civil aviation

Abstract

The paper describes the optimization of an axial cooled two-stage high-pressure turbineGTE for a civil aircraft. At the same time, the problem of increasing the efficiency and reducing theoutput swirl gradient was solved. The difficulty of the solution was the high efficiency of the originalversion and the need to take into account cooling. To achieve the result, a series of optimizationproblems was solved, in which the parameterization schemes, the number of variable sections, thegrid of finite volumes, and the degree of detail of the mathematical model were varied. As a result,2 variants for optimizing the geometry of the turbine were found, differing in the degree of changein the initial design, which made it possible to increase the efficiency of the turbine by 0.37 and0.63 %.