Comparative analysis of layout options and parameters of a supersonic civil aircraft engine

The article presents the results of a study that can be used in the development of technical specifications for the power plant of a supersonic civil aircraft. The proposed solutions are based on existing technology and proven designs, eliminating the need to create engines with complex configurations. A cruise engine for an aircraft designed to carry 20 passengers at a range of up to 10,000 km while flying at an altitude of 20 km at a speed of 2,500 km/h is being considered. A method for analyzing the layout schemes and basic thermodynamic parameters of a gas turbine engine, including the total pressure ratio and the bypass ratio, is described. The key flight modes are analyzed – takeoff, climb, cruise mode and descent, which made it possible to objectively assess the thrust and economic characteristics of a civilian aircraft installation, unlike existing analogues for multi-mode military supersonic aircraft. The data obtained make it possible to form requirements for the design of the engine and evaluate its operational properties. The choice of a turbofan engine layout with a mixing chamber ensures high manufacturability, reduces noise and harmful emissions, and improves flight safety.

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