FIELD: engines and pumps.
SUBSTANCE: invention relates to turbojet engine gas turbines. Gas turbine blades are mounted on a cylindrical sleeve to rotate and axially move thereon which is provided for by attaching it to structural circular wall tapered ledge. The said wall central part represents a two-wall cylinder incorporating a spring fitted between the cylinder walls and resting upon the circular ledge of cylindrical barrel rigidly fixed on the shaft. The barrel rear part has a circular wall made integral with a part of vortex turbine blades to allow the second part of aforesaid blades made on the structural circular wall inner surface to enter into the said first part to have both parts aligned in axial travel. Circular webs arranged on the turbojet engine intermediate structural casing confine the vortex turbine blade outer parts. Fuel, in compliance with the fuel lines, actuates the cylindrical sleeve axial travel mechanism to vary the circular gap size controlling the passage of gas flow onto the gas turbine blades.
EFFECT: power take-off adjustment.
2 cl, 5 dwg
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