TURBOJET ENGINE Russian patent published in 1998 - IPC

FIELD: turbojet engines. SUBSTANCE: engine includes housing, axial-flow three-stage compressor, combustion chambers and gas turbine enclosed in massive casing. Longitudinal axes of combustion chambers are located at angle of 45-75 deg relative to end plane of engine and perpendicularly to surface of fin of gas turbine blade in zone of its leading edge. number of gas turbine blades is equal to or more than number of combustion chambers. Mounted coaxially after turbine is diffuser with straightening walls in form of flat blades evenly secured at one end over circumference of inner surface of engine housing and located radially in longitudinal axial plane and to hub at other end. Shaft runs through inner hole in hub. EFFECT: increased service life of engine and enhanced reliability. 2 dwg