FIELD: mechanical engineering.
SUBSTANCE: invention relates to the field of engine construction, namely to gas turbine engines and can be used in contemporary aircraft, ships and tanks. The proposed gas turbine internal combustion engine with compression ignition, contains centrifugal compressors, gas centripetal turbines and annular combustion chambers 6. In this case, the engine is divided into a stator 4 and a rotor 1, which is made of a semi-open type. In addition, the rotor 1 contains impellers with blades of centrifugal compressors 2 and centripetal turbines 3, made with it as a whole. Moreover, the injectors 5 for fuel injection, located in the stator 4, are connected to a high-pressure diesel fuel pump (HPFP) 8, equipped with an all-range regulator 9, which is a regulator with centrifugal loads and a system of control levers.
EFFECT: increase in the wear resistance of the engine elements while maintaining the high efficiency of a gas turbine internal combustion engine with compression ignition.
1 cl, 1 dwg
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