Study of the ECS System of a Passenger Aircraft with a Hybrid Propulsion

Development of a promising passenger airplane with a hybrid propulsion (HP) is an urgent task from the point of view of improving the environmental friendliness of air transportation by eliminating the negative impact of combustion products of aviation fuel on the atmosphere. The key feature of the hybrid propulsion of such an airplane is the use of liquid nitrogen as a cryoagent for its cooling. After cooling the hybrid propulsion, nitrogen has a sufficiently low temperature and a significant residual refrigerant resource, which can be usefully utilized in the Environmental Control System (ECS) of the aircraft under consideration. The purpose of this work is to form a possible design of an ECS for a regional jet with a HP. To achieve this goal, a number of tasks were solved: two possible variants of ECS schematic solution were considered, thermal and humidity calculation of the presented schematic solutions was performed at the main possible operating modes, the degree of thermodynamic perfection of ECS was determined depending on the liquid nitrogen flow rate, the scheme of its movement and the degree of cabin air recirculation.