Development of an Air Electric Compressor for a No-Bleed Environmental Control System of an Advanced Regional Aircraft

Abstract

BACKGROUND: Aircraft designers strive to increase the fuel efficiency of aircrafts, including increasing the efficiency of aviation environmental control systems (ECS) by introducing an autonomous source of compressed air with an electric drive as part of aircraft.
 AIM: The present paper aimed to consideration of the results of research work (RD) of the technologies demonstrator for the electric compressor of the aircraft electric ECS and estimation of the performance and compliance of the simulated and experimental characteristics of this electric compressor.
 MATERIALS AND METHODS: Comparison of the simulated 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 technologies demonstrator for the electric compressor with those specified in the request for proposals (RFP), and by comparing the simulated and experimental values of the compression ratio of the compressor stage, isentropic coefficient of performance (COP), obtained during RD study.
 RESULTS: Information about the technical characteristics and design of the electric compressor is given and discussed. A comparative analysis of the presented simulated and experimental characteristics of the electric compressor has been carried out.
 CONCLUSIONS: Conclusions are drawn on the compliance of the compressor characteristics with the characteristics specified in the RFP; on the achieved level of readiness of the technology of the electric compressor for the electric ECS of the aircraft, on the need for experimental design work on the electric compressor, taking account of external influencing factors typical for an application as part of aviation equipment.