Optimization the main thermodynamics parameters of the aviation turbofan engines with heat recovery in the aircraft system

Abstract

Improving the fuel efficiency of aircraft engines is the main global trend of modern propulsion engineering. One of the promising ways to improve fuel efficiency is the use of complex thermodynamic cycles with heat recovery of exhaust gases. An important task in the design of engines with heat recovery is to select the main thermodynamic parameters process that ensures maximum efficiency of the engine in the aircraft system. The article presents the setting problem of optimization and selection of rational parameters of the working process of turbofan engines with heat recovery. Based on the developed method of multi-criteria optimization utilizing numerical simulations conducted and presented the results of optimization of parameters of the working process of turbofan engines with heat recovery in the system of aircraft according to criteria such as the total mass of the engine and fuel required for the flight, the specific fuel consumption of the aircraft on a ton per kilometre and the specific fuel consumption of engine (SFC). The developed mathematical model for calculating the mass of a compact heat exchanger presents to solve optimization problems at the stage of the conceptual design of the engine. The developed methods and models are implemented in the ASTRA program.