GAS-TURBINE INSTALLATION Russian patent published in 2010 - IPC F02C7/20 F02K3/02 

FIELD: machine building.

SUBSTANCE: gas turbine installation is made on base of double-circuit aircraft engine and consists of turbo-compressor with mixer at output and with channel of external circuit. An external case of the installation is connected with a case of the turbo-compressor over a combustion chamber; a working ring over the first working blade of the turbo-compressor is telescopically connected with an external ring of an inlet guiding device in axial direction. The combustion chamber is equipped with external flame tubes arranged together with external cases of the flame tubes in the channel of the external circuit. Poles are located before the cases of the flame tubes and are equipped with a connection telescopic in radial direction. The mixer at the output is connected with the external case of the turbo-compressor telescopically in axial direction and at the output in the axial direction it is rigidly coupled with the external case of the external circuit channel.

EFFECT: raised reliability due to uniformity of cooling cases of flame tubes and due to additional fastening turbo-compressors in radial direction.

5 dwg