Abstract: This invention relates to gas turbine engines of continuous combustion in a high speed gas flow through an open circuit in high heating value gas turbine fuels. It may be used in transportation facilities, such as aviation and power plants, and also as a drive in gas compressor units. The engine contains two or more combustion chambers for high-calorific fuel suitable for combustion in speed gas and air stream. Each combustion chamber after the previous combustion chamber raises the temperature of the working body after the work at the turbine stage to the value optimal for work at next turbine stage. There is a possibility of independent reallocation of immediate bulk flows between the main stream of the working body and supplementary bypass parallel streams of the working body. For this purpose the engine, apart from the multistaged turbine, contains at least two compressor stages of air compression with bends. Each combustion chamber contains its fuel sprayers.