CONNECTION ASSEMBLY OF COMPRESSOR ROTORS AND TURBINE OF GAS TURBINE ENGINE Russian patent published in 2021 - IPC F02C7/36 

FIELD: engine building.

SUBSTANCE: invention relates to gas turbine engine building and can find an application in aircraft and ground engines. In the connection assembly of the compressor rotors and the turbine of a gas turbine engine, containing a high-pressure compressor shaft and a high-pressure turbine shaft connected by a flange connection, wherein the ends of the flanges are directed into the shafts, and a Hirth connection, namely: two rows of radial teeth are made on the ends of the shaft flanges along the circumference, wherein an annular groove with a flat bottom is made between the rows, wherein through holes are made in said bottom, wherein, in turn, bolts are installed with radial gaps, wherein an annular element is installed between the inner surfaces of the shaft flanges, contacting by a section of the outer surface thereof with the inner surface of the shaft flange of the high-pressure compressor, and a gap is formed between the inner surface of the shaft flange of the high-pressure turbine and the outer surface of the annular element, wherein an annular groove is made from the side of the outer surface of the annular element, wherein a split ring is installed with a radial gap, contacting by the outer surface with a section of the inner surface of the shaft flange of the high-pressure turbine, the annular element is also rigidly fixed relative to the shaft flange of the high-pressure compressor by means of a flange with holes for said bolts, made integral with the annular element and installed between the bolt caps and the nearest face of the shaft flange of the high-pressure compressor, wherein self-locking nuts contacting with tension at the ends with the shaft flange of the high-pressure turbine are installed on the bolts.

EFFECT: reduction of air leaks between adjacent parts of the turbine of the GTE and simplification of the design are achieved.

6 cl, 2 dwg