Development of a mathematical model of the compact heat exchanger used for optimizing thermodynamic parameters of the aviation gas turbine engine

Abstract

Nowadays, the task of using automation for improving the technical and economic efficiency of the engine by reducing the specific fuel consumption and reducing the specific weight is one of the main trends in the development of the aviation industry. A promising approach for decrement of specific fuel consumption and obtaining high thermal efficiency of the gas turbine engine (30% and above) is based on the concept of the recuperative cycle of the gas turbine engine. The article presents the computer-aided calculation of a heat exchanger for analysing the heat exchanger surface and developing the mathematical model of heat exchanger in terms of weight goodness, flow passage goodness, and optimum weight and flow passage. Design calculations had been carried out for an aircraft engine with a heat exchanger made up with deferent heat transfer surfaces. To appraise the reliability of the obtained models, the results of design calculations on the developed models have been compared with the data of other authors and with the data on the created regenerator. The obtained model focus on mathematical design calculation for optimizing the main thermodynamic parameters of a gas turbine engine coupled with a heat exchanger at the stage of conceptual design of aviation gas turbine engine with heat recovery of exhaust gas.