Research and development of the Gas Generator cycle Air-Turbo Ramjet (GG-ATR) engine for the supersonic aerospace plane is in progress as this propulsion engine. Ball bearings of this engine will be operated under severe high-speed rotation. Therefore, the bearings produce heat by their own friction and become hot. In order to investigate the rotordynamic characteristics of the rotor and aerodynamic performance of the compressor and turbine for the engine, cold run test campaign was conducted by using nitrogen / helium gas as driving gas. Heat generation and cooling characteristics of those bearings are evaluated by its temperature data and theoretical analysis result. Based on those experimental results, the issue to do are discussed concerned with the rotor-bearing system for the engine.
