UA88223C2 - Gas-turbine engine - Google Patents

Abstract

A gas-turbine one-shaft engine with two-support rotor of turbo-group on elastic-damper bearings proposed that realizes Brayton cycle has a compressor, a combustion chamber, a turbine that brings into action the compressor and electric generator, with actuating of electric generator from side of compressor and with axial outlet for gases from turbine, at that power circuit of bodies comprises connected to each other with outlet and inlet flanges power bodies of compressor, combustion chambers, turbines. The compressor is arranged as centrifugal one, with console section, at that rotor of turbo-group is arranged assembled, of cylinder-disc type, and includes connected to each other rotor of centrifugal compressor with console section, cylindrical insert with disc that has gaskets, rotor of turbine. Front pin of rotor of turbo-group with support and rest bearings is placed in console section of compressor, and to its flange for transfer of torque to console section of compressor flexible hub of middle disc of console section of the rotor is connected. The combustion chamber is arranged as group of remote combustion chambers placed in radial positions, there fire pipes are in middle cross section with telescopic connections and at output through shoe-like branch pipe those are hermetically connected to first nozzle apparatus of the turbine. The power circuit of the bodies additionally has outer power body that consists of connected to each other front cone, cylindrical insert, back cone and tightly surrounds the turbine and at least part of compressor, and outside it is connected to power bodies of group of remote combustion chambers.