Development of an energy efficient no-bleed environmental control system for aircraft with distributed power plant

Background: Today, there are high fuel efficiency requirements to state-of-the-art passenger aircraft. The environmental control system (ECS), a one on general aircraft systems, shall have high energy efficiency to ensure the overall fuel efficiency of the aircraft, including by integrating compressed air sources and electric air cycle machines in the ECS.

Aim: To estimate the performance of the circuit solution created during research and development (R&D) of the energy-efficient electric ECS of an aircraft.

Materials and methods: We developed a static mathematical model of an electric ECS with moisture content control to determine system parameters in various operating modes.

Results: The article presents specifications of the electric turbo compressor (ETC) as a key unit of the studied electric ECS and the calculation of ECS parameters for different operating modes.

Conclusion: The article presents conclusions on the operability of the proposed design of an energy-efficient ECS with an ETC for a regional distributed propulsion aircraft, the achieved level of readiness of the ECS technology, the need for research and development of ETC and ETC-based ECS pack.