GAS TURBINE ENGINE Russian patent published in 2019 - IPC F02C5/04 

FIELD: engines.

SUBSTANCE: gas turbine engine includes housing with annular shells, combustion chambers, fuel supply and igniting devices. In the housing there is a blade wheel with blades rims, on the ends of which there fixed are flat banding rings. Bypass channels are made in housing with inlet and outlet holes and adjoin to outer contour of rims of vaned wheel. Inlet sector holes adjoining the inner contour of the blade rims are made in the housing, partially aligned with the outlet sector openings adjoining the outer contour of the blade rims. Inlet sector holes are connected with diffusers made at body ends, and blades arranged on hub of blade wheel, adjacent to inner outline of annular shell. Between bypass channels and output sector openings there are nozzles with regulators, horizontal and vertical, with inlet holes made in the housing and adjoining the outer contour of rims of the blade wheel, and vertical nozzles are connected to horizontal ones, displaced vertically. Between the fuel feeders and igniter devices there are cylindrical chambers with spring-loaded pistons, inlet openings with valves, channels with valves and nozzles connected to the housing. Cylindrical chambers are made hollow and with pistons with regulators. Between firing devices and output sector openings there are outlet sector holes in housing, which adjoin to inner contour of blade wheel rims, outer contour of which can be made less than external contour of its rim blades.

EFFECT: invention is aimed at improvement of reliability and increase of specific power by efficiency of combustion chambers operation.

9 cl, 10 dwg