Computer-aided Design of Axial Flow Turbine Structure of Aviation GTE

Abstract

The article discusses the issues of modeling the design of axial turbines of aircraft engines. Modeling is carried out using the developed expert decision-making system "AM". The advantage of using this system in the early stages of engine design is shown. This advantage is achieved by selecting the most optimal material for the main assembly units of an aircraft engine based on various calculations that represent the mathematical model of the expert system. It is shown that the expert system in addition to the selection of material also carries out the selection of measures to improve the resistance of the material to the external environment, and the recommended modes of surface treatment. As an example, the results of computer-aided design of the elements of the flow channel of high and low pressure turbine assemblies of a two spool turbojet engine with afterburner and mixed flow for a 4th generation military highly mobile aircraft are given. The results of the design simulation are compared with the actual design of the prototype engine. Comparison of the results is carried out both in terms of geometrical parameters (diametrical dimensions of the flow part and the dimensions of the chords of the nozzle assembly and blades), and in terms of mass characteristics.