Creep equivalence and simplification method for dense exhaust film holes of nickel-based single crystal turbine cooling blade

Abstract

The invention relates to a creep equivalence and simplification method for dense exhaust film holes of a nickel-based single crystal turbine cooling blade. The method comprises the steps of determining a nickel-based single crystal alloy creep constitutive equation based on the crystal plasticity theory, determining the gas film hole density of a nickel-based single crystal turbine cooling blade model according to the arrangement mode of dense exhaust film holes, introducing a gas film hole density function, and determinig a creep deformation expression under the arrangement mode; determining the creep equivalent parameters according to the creep deformation expression; according to the creep equivalent parameters and the arrangement mode of the dense exhaust film holes, simplifying the dense exhaust film holes into a single air film hole; and simplifying the gas film hole in the nickel-based single crystal turbine cooling blade model into one single gas film hole to obtain an equivalent model. According to the creep equivalence and simplification method for the dense exhaust film holes of the nickel-based single crystal turbine cooling blade, the structural strength analysis and the service life design difficulty of the blade can be reduced.

Description

technical field [0001] The present disclosure relates to the technical field of aero-engines, in particular to a creep equivalent and simplified method of a nickel-based single-crystal turbine cooling blade airtight film hole. Background technique [0002] As one of the main components of an aero-engine, the turbine blade plays a decisive role in the overall performance of the engine to some extent. In order to increase the turbine inlet temperature and ensure the reliability of turbine blades working in high temperature environment, the application of turbine blade cooling technology is more and more extensive. Nickel-based single-crystal superalloy materials contain only one grain, which eliminates the influence of grain boundaries. Compared with equiaxed crystals and oriented columnar crystals, they have higher strength, life and elongation, and can significantly improve the structural strength of turbine cooling blades And life, at the same time, it has excellent compre...

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Problems solved by technology

[0003] Usually, a large number of air film holes are designed on the turbine cooling blades to improve the cooling efficiency. While the cooling efficiency is improved, the existence of the air film holes damages the continuity of the turbine blade material and structure, and changes the stress and strain field in the local area of ​​the air film holes. And the surface state, to some extent will lead to the reduction of the structural strength and life of the blade, therefore, it is necessary to analyze the structural strength of the blade and predict the life

[0004] However, the air film holes are densely arranged on the turbine cooling blades, the hole diameter is small, and the number is large, which makes it difficult to divide the grid in the finite element analysis of the cooling blades, and causes great difficulties to the structural strength analysis and life prediction of the blades.

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