Optimization design method for shape of inner cavity of turbine disc with radial plate based on hyperelliptic curve

Abstract

The invention discloses an optimization design method for a shape of an inner cavity of a turbine disc with a radial plate based on a hyperelliptic curve, and is used for solving the technical problem of long design cycle of the conventional optimization design method for a multi-arc-section curve shape. The invention adopts the following technical scheme: the method comprises the step of carrying out finite element modeling, analyzing and sensitivity solving on the cross section of the turbine disc with the radial plate by hyperelliptic curve boundary conditions and carrying out optimization iteration according to the obtained sensitivity information until a final design result is obtained by convergence. According to the method, the profile of the initial shape of the inner cavity of the turbine disc is effectively subjected to optimization design, the design cycle is short, and better horizontal stress distribution is obtained; the maximal stress after the optimization is 769.47 MPa and is reduced by 47.32% than the stress of 1460.75 MPa before the optimization; the maximal stress after the optimization by the method provided by a literature is 842.7 MPa and is reduced by 7.6% than the stress of 912 MPa before the optimization; and the method provided by the invention is low in stress concentration level of an optimization result and is remarkably superior to the background technology.

Description

technical field

[0001] The invention relates to a method for optimizing the shape of the inner cavity of a turbine disc with webs, in particular to a method for optimizing the shape of the inner cavity of a turbine disc with webs based on a hyperelliptic curve. Background technique

[0002] Aeroengine turbine disk is one of the key parts of aeroengine. Its volume and weight are relatively large. The loads include the centrifugal force of the turbine disk and the blade centrifugal force generated by the high-speed rotation of the turbine disk, as well as the temperature gradient from the high-temperature and high-pressure gas in the combustion chamber. loads and blade aerodynamic loads, etc. Therefore, the loads borne by the turbine disk during work are relatively complex, and stress concentration is likely to occur, which reduces its fatigue life.

[0003] The literature "Zhu Jihong, Li Junshuo, etc., Application of modern shape optimization technology in the design of aero...

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