GAS TURBINE ENGINE Russian patent published in 2010 - IPC F02C5/12 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine comprises rotor with combustion chambers and turbine rigidly fitted on the shaft arranged inside the housing. Combustion chambers are arranged all around the rotor, each having a fuel feed hole on one rotor side and nozzle made on the opposite side. Rotor and turbine hollow shaft allows compressed air to flow from compressor there through. Separating disk with elongated openings arranged on opposite sides of the axis of symmetry is mounted in the housing between rotor and turbine and rigidly coupled with the housing. Multiple blades are arranged in every said opening all along its length, coupled with said separating disk or made integral with it, for example cast as a single piece. Every blades of said separating disk represents a section bent along housing cross section that makes with adjacent blade section aforesaid passage for compressed gas to flow from combustion chamber to turbine blades. One end of said air passage is directed towards rotor combustion chamber. Opposite end of said passage runs towards turbine blades. Axis of nozzle of every combustion chamber is inclined to combustion chamber crosswise axis.

EFFECT: higher engine efficiency, its power and simplified design.

13 dwg