Simplified and Equivalent Method for Tight Vent Membrane Holes in Ni-based Single Crystal Turbine Blades

Abstract

The invention proposes a simplification and equivalent method for a nickel-based single crystal turbine cooling blade airtight exhaust film hole, which belongs to the technical field of structural reliability analysis and optimal design. The method for solving the structural failure probability determines the flat plate model of the blade according to the arrangement of the holes in the airtight air vent membrane of the blade, and simplifies the flat plate model of the blade into an equivalent single hole model; according to the thickness difference of the equivalent single hole model, the The equivalent single-hole model is divided into a plane stress state area and a generalized plane strain state area; according to the stress-strain relationship between the blade plate model and the equivalent single-hole model, the equivalent single-hole model is deduced in the plane Equivalent elastic constant expressions for the stress state and the generalized plane strain state. The simplification and equivalent method can accurately calculate the stress and strain fields around the film cooling holes while effectively reducing the amount of calculation, so as to determine the life of the turbine blades.

Description

technical field [0001] The invention belongs to the technical field of structural reliability analysis and optimal design, and in particular relates to a simplified and equivalent method for a nickel-based single crystal turbine blade airtight membrane hole. Background technique [0002] At present, nickel-based single crystal superalloys are widely used as turbine blade materials in the world. This alloy not only has excellent thermal corrosion resistance and oxidation resistance, but also has outstanding high temperature creep, fatigue performance and structural stability, and is widely used in Manufacture of hot end parts of aviation and aerospace engines. In order to adapt to the higher and higher turbine inlet temperature, the turbine blades of aero-engines mostly adopt the structure with airtight exhaust film cooling holes on the blade body. The stress-strain field at the edge of the film cooling hole is extremely complex, and accurate calculation of the stress and st...

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Problems solved by technology

In the finite element simulation calculation of turbine blades, the existence of a large number of air film holes will lead to a huge amount of calculation

[0003] At present, the equivalence of air film holes for blade cooling is mainly used in isotropic materials, such as the equivalence of material properties of structures with holes. The simplification and equivalent methods are based on isotropic materials, and the The same amount of deformation is the equivalent judgment standard, and the nickel-based single crystal alloy mainly used in domestic aero-engines is an anisotropic material, and its mechanical properties are orientation-dependent and sensitive, and the existing equivalent simplified method cannot be applied

Moreover, the airtight membrane holes are arranged in different ways, and a single simplified model cannot satisfy all situations.

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