Rotating detonation engines (RDEs) can get thrust or work by keeping detonation waves propagating in circumferential direction. Our objective is to apply rotating detonation engines (RDEs) to aircraft engines since we expect that the aircraft such as airplanes is to fly longer range by more simple structure. In this study, we designed a rotating detonation turbine engine (RDTE) with a single stage centrifugal compressor and a single stage radial flow turbine. The outer diameter of RDTE is about 200 mm. The revolution speed is 110000 rpm and rated air mass flow rate was 0.610 kg/s. We made two-parallel-plane rotating detonation combustor. We performed hot test with ethylene and oxygen. We analyzed several combustion modes with streak pictures and pressure time history. We observed the number of detonation waves, quenching and re-ignition phenomena by streak pictures.