Computer-aided design of aircraft gas turbine engines and selection of materials for their main parts

Abstract

The problem of aircraft gas turbine engine computer-aided design is dealt with in the article. An expert system for the selection of materials, coatings and other kinds of preparing surfaces of the main components and assembly units of the aircraft gas turbine engine flow section at the design stage developed on the basis of thermogasdynamic simulation modeling of DVIGw aviation engines is described. The system performs thermal gas calculation of the engine and its main components, develops the most likely structure of the main parts, estimates the thermal state of air-gas channel elements, makes an approximate strength prediction of the main elements and assembly units, analyzes the applicability of the materials from the developed database, generates the list of the most applicable materials, offers possible variants of coatings and heat treatment conditions. A topological model of two-spool mixed flow turbofan with an afterburner chamber for military high-maneuverability aircraft in the developed expert system is presented in the article. Some results of modeling and choosing materials for the main engine parts are presented. It is shown that the expert system can analyze both metallic and composite materials. For composite materials a unidirectional orthotropic composite material is designed on the basis of the composite materials database and its properties at the existing flow temperatures are predicted. The main advantage of using this method is time and labor saving in the process of designing new aircraft engines and their main parts.