combustion gas generated by the detonation phenomenon to flow out from the detonation chamber 14 according to the detonation engine 10 having such a structure the overall engine structure can be simplified and continuous output can be obtained moreover according to the flying object 1 comprising such a detonation engine 10 continuous output can be always maintained and hence stable flying conditions can be maintained at all times a second embodiment of the detonation engine according to the present invention is described using fig4 fig4 is similar to fig2 being a cross sectional view of the main parts of the detonation engine 20 according to the present embodiment as shown in fig4 the detonation engine 20 according to the present embodiment comprises an inlet 11 a fuel injection nozzle 12 a detonation chamber 14 a nozzle 15 a turbine nozzle 21 and a turbine rotor 22 as the main components since the inlet 11 the fuel injection nozzle 12 the detonation chamber 14 and the nozzle 15 have already been explained for the first embodiment explanation thereof is omitted here the turbine nozzle 21 comprises a plurality of nozzle guide vanes having an airfoil cross section which are arranged annularly and has a function to expand and decompress the gas flowing out from the detonation chamber 14 and to change the flow direction of the gas flowing out from itself so that it can impinge on the turbine blades 26 described later at an optimum angle the turbine rotor 22 comprises a shaft 23 an impeller compressor.