BYPASS TURBOJET ENGINE WITH AIRFLOW REDISTRIBUTION AT INLET Russian patent published in 2012 - IPC F02K3/02 

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises inlet device, low- and high-pressure compressors, combustion chamber, low- and high-pressure turbines, mixer of circuit flows, and nozzle. Engine inlet accommodates two flow-twist-controlled-diffusers and incoming flow power redistribution in radial direction. Cylindrical combustion chamber is arranged between first and second diffusers. Second diffuser is arranged directly at low-pressure compressor inlet. Multi-vane diffusers have their vanes arranged radially. Fixed parts of first diffuser vanes thrust by their one end against central body while another end thrust against chamber channel inner surface front section. Fixed parts of second diffuser vanes thrust by their one end low-pressure compressor cone while another end thrust against chamber channel inner surface rear section. First diffuser is equipped with rear shaped turning sections of vanes to deflect airflow. Second diffuser is equipped with front shaped turning sections of vanes to deflect airflow coupled with appropriate drives and with fixed sections of vanes via moving joints. Drive are incorporated with common engine control system.

EFFECT: increased thrust, optimised engine operating conditions.

5 dwg