Verification of computing model of a two-stage high-pressure turbine of a modern GTE for civil aviation
The article presents the results of the first stage of work on the modernization of the cooled axial two-stage high-pressure turbine cycle. Two computing turbine models are described and verified using available experimental data. The choice of the number of finite volumes in the impeller passage and their distribution along the height of the blades is justified. The paper shows that the integral parameters of the turbine obtained in the calculation belong to the experimental data scatter band.