Development of an air electric compressor for a no-bleed environmental control system of an advanced regional aircraft

BACKGROUND: Aircraft designers strive to increase the fuel efficiency of aircraft, including by increasing the efficiency of aviation environmental control systems (ECS) by introducing an autonomous source of compressed air with an electric drive as part of aitcraft. 
AIM: This article aimed to evaluation of the performance and compliance of the calculated and experimental characteristics, created in the course of research work (RD) of the demonstrator of technologies for the electric compressor of the electric ECS of the aircraft. 
MATERIALS AND METHODS: Comparison of the calculated and experimental characteristics of the electric compressor of the electric ECS of the aircraft was carried out by confirming the compliance of the operating parameters of the demonstrator of technologies of the electric compressor with those specified in the request for proposals (RFP), and by comparing the calculated and experimental values of the compression ratio of the compressor stage, isentropic coefficient of performance (COP), obtained during the performance of research. 
RESULTS: Information about the technical characteristics and design of the electric compressor is given. A comparative analysis of the presented calculated and experimental characteristics of the electric compressor has been carried out. 
CONCLUSIONS: Conclusions are drawn about the compliance of the characteristics of the compressor with the characteristics specified in the request for proposal (RFP), about the achieved level of readiness of the technology of the electric compressor of the electric ECS of the aircraft, about the need for experimental design work on the electric compressor, taking into account external influencing factors typical for use as part of aviation equipment.