Improving the efficiency of aviation turbofan engines by using an intercooler and a recuperative heat exchanger


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Abstract

Continuous improvement of fuel efficiency of aircraft engines is the main global trend in modern engine construction. To date, aviation gas turbine engines have reached a high degree of thermodynamic and design-and technology perfection. One of the promising ways to further improve their fuel efficiency is the use of complex thermodynamic cycles with turbine exhaust heat regeneration and with intermediate cooling in the process of air compression. Until recently, the use of cycles with a recuperative heat exchanger and an intercooler in aircraft gas turbine engines was restrained by a significant increase in the mass of the power plant due to the installation of heat exchangers. Currently, it has become technologically possible to create compact, light, high-efficiency heat exchangers for use on aircraft without compromising their performance. An important target in the design of engines with heat recovery is to select the parameters of the working process that provide maximum efficiency of the aircraft system. The article focuses on the statement of the task of optimization and choice of rational parameters of the working process of a bypass three-shaft turbojet engine with an intercooler and a recuperative heat exchanger. On the basis of the developed method multi-criteria optimization was carried out by means of numerical simulations. The results of optimization of thermodynamic cycle parameters of a bypass three-shaft turbojet engine with an intercooler and a recuperative heat exchanger in the aircraft system according to such criteria as the total weight of the engine and fuel required for the flight, and the aircraft specific fuel consumption per ton - kilometer of the payload are presented. A passenger aircraft of the Airbus A310-300 type was selected. The developed mathematical model for calculating the mass of a compact heat exchanger, designed to solve optimization problems at the stage of conceptual design of the engine is presented. The developed methods and models are implemented in the ASTRA program. The possibility of improving the efficiency of turbofan engines due to the use of complex thermodynamic cycles is shown.

About the authors

H. Omar

Samara National Research University

Author for correspondence.
Email: dr.hewa.omar@gmail.com
ORCID iD: 0000-0003-4574-0339

Postgraduate Student of the Department of Theory of Aircraft Engines

Russian Federation

V. S. Kuz'michev

Samara National Research University

Email: kuzm@ssau.ru
ORCID iD: 0000-0003-1696-2899

Doctor of Science (Engineering), Professor, Professor of the Department of Theory of Aircraft Engines

Russian Federation

A. Yu. Tkachenko

Samara National Research University

Email: tau@ssau.ru
ORCID iD: 0000-0002-5951-9064

Candidate of Science (Engineering), Associate Professor, Assistant Professor of the Department of Theory of Aircraft Engines

Russian Federation

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