Aero-engine formed by 3D printing

Abstract

Disclosed is an aero-engine formed by 3D printing. The aero-engine formed by 3D printing comprises a compressor shell (1), a radial diffuser (2), an impeller (3), an axial diffuser (4), a turbine (5)and a turbine shaft (6). The radial diffuser (2) is of a hollow disc-shaped structure, and the impeller (3) is arranged in the center of the radial diffuser (2). The axial diffuser (4) is of a hollowstructure, the turbine shaft (6) is arranged in the axial diffuser (4), and the two ends of the turbine shaft (6) are connected with the impeller (3) and the turbine (5) correspondingly. The aero-engine formed by 3D printing further comprises a shaft end nut (7), a stop ring (8), an engine shell (9), a tail jet outer shell (10) and a tail jet inner shell (11). Parts of the aero-engine formed by 3Dprinting are manufactured by 3D printing, and have the small wall thicknesses, then the light weight is given to the aero-engine, and therefore the carrying capacity of the aero-engine is improved under the condition of the same thrust.

Description

technical field [0001] The invention belongs to the field of aero-engines, and relates to aero-engines, in particular to a 3D printing aero-engine. Background technique [0002] An aero-engine is an engine that provides the power required for aircraft to fly. Unlike engines in other application fields, the weight of an aero-engine is a key factor affecting the flight power of an aircraft. Under the premise of ensuring the strength of use, the weight of the engine should be reduced as much as possible, so that more payload can be achieved under the same thrust. [0003] However, the weight of the aero-engine obtained by adopting the prior art is relatively large, thereby causing its thrust to be reduced, and the components of the aero-engine obtained by the prior art are simple in structure and cannot achieve good heat dissipation. Therefore, it is urgently needed A new type of aero-engine with light weight, high thrust and good heat dissipation. Contents of the invention ...

AI Technical Summary

Problems solved by technology

[0003] However, the weight of the aero-engine obtained by adopting the prior art is relatively large, thereby causing its thrust to be reduced, and the components of the aero-engine obtained by the prior art are simple in structure and cannot achieve good heat dissipation. Therefore, it is urgently needed A new type of aero-engine with light weight, high thrust and good heat dissipation effect

Images