Gas turbine engine

A gas turbine engine, comprising:

• a turbine wheel;
• a compressor wheel, coaxially configured with the turbine wheel and rotating integrally;
• a rotary shaft, comprising an outer shaft portion connected to the compressor wheel, a penetration portion extending along an axis direction and formed at an axis center of the outer shaft portion, and an inner shaft portion passing through the penetration portion and connected to the turbine wheel, so that rotation of the turbine wheel is transmitted to a driving member;
• and
• a thrust cancel disc, provided between an inner surface of the turbine wheel and an inner surface of the compressor wheel, wherein
• the compressor wheel has a hollow portion extending along the axis direction and formed at an axis center, and at least the inner shaft portion of the rotary shaft passes through the hollow portion,
• the turbine wheel has a first thread portion protruding from a center of the inner surface of the turbine wheel toward the inner surface of the compressor wheel,
• at least one end portion of the inner shaft portion extends toward the inner surface of the turbine wheel and has a second thread portion screwed with the first thread portion,
• two side surfaces of the thrust cancel disc are respectively provided with an annular gear-shaped first convex portion structure, the inner surface of the turbine wheel and the inner surface of the compressor wheel are respectively provided with an annular gear-shaped second convex portion structure, and the thrust cancel disc is connected to the inner surface of the turbine wheel and the inner surface of the compressor wheel, respectively, through coupling of the first convex portion structure and the second convex portion structure, and
• a through hole is provided in a center of the thrust cancel disc, and the first thread portion of the turbine wheel or the end portion of the inner shaft portion with the second thread portion passes through the through hole.