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Turbine blade nonlinearity creep analysis method based on beam theory

A turbine blade and analysis method technology, applied in the direction of electrical digital data processing, special data processing applications, instruments, etc., can solve the time-consuming 3D finite element creep analysis, difficult to adapt to multi-scheme, multi-working conditions, long-life blade design Analysis and real-time monitoring of blade life, low efficiency and other issues, to achieve the effect of convenient acquisition, improved acquisition efficiency, and good engineering practicability

Active Publication Date: 2017-05-31
CHINA AVIATION POWER MACHINE INST
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Problems solved by technology

[0004] The present invention provides a nonlinear creep analysis method for turbine blades based on beam theory to solve the problem that the existing three-dimensional finite element creep analysis takes a long time, has low efficiency, and is difficult to adapt to multi-scheme, multi-working conditions, long-life blade design analysis and Technical Problems of Real-time Monitoring of Blade Life

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  • Turbine blade nonlinearity creep analysis method based on beam theory
  • Turbine blade nonlinearity creep analysis method based on beam theory
  • Turbine blade nonlinearity creep analysis method based on beam theory

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Embodiment Construction

[0033] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings, but the present invention can be implemented in various ways defined and covered below.

[0034] figure 1 It is a flow chart of the steps of the nonlinear creep analysis method of the turbine blade based on the beam theory in the preferred embodiment of the present invention. Such as figure 1 As shown, the nonlinear creep analysis method of the turbine blade based on the beam theory of the present embodiment includes the following steps: a, determining the material creep parameters at multiple temperatures within the working range of the turbine blade; Time is divided into multiple time steps; c. Select multiple sections of turbine blades and divide them into meshes; d. Based on beam theory, obtain the stress and permanent damage of blade creep and creep relaxation at each time step; e. Obtain blade Creep elongation and creep permanent damage. Optio...

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Abstract

The invention discloses a turbine blade nonlinearity creep analysis method based on beam theory. The method comprises the following steps: a, a material creep parameter of a turbine blade under a plurality of temperature within scope of work is determined; b, working time is divided into a plurality of time steps; c, a plurality of section of turbine blade is selected, and a divided gridding is divided; d, a stress and durable damage of blade based on beam theory in each time step after creeping and creeping deformation is obtained; e, a turbine blade creep deformation extension and a creep deformation durable damage are obtained. The main element of the turbine blade creep deformation is considered, and is convenient and fast, the engineering practical demand can be met, obtained efficiency is increased hundreds of times, the projects blade contrastive analysis, the full-life blade creep analysis and the turbine blade on line lifetime monitoring are suitable, the engineering practicability is better. The creep deformation prolongation and the creep rupture life for polytopes launch turbine blade are analyzed and verified, the long-term- test effect of engine is indicated, obtained data precision can be met for engineering practical requirement.

Description

technical field [0001] The invention relates to the technical field of detection and calibration of aeroengine turbine blades, in particular to a beam theory-based nonlinear creep analysis method for turbine blades. Background technique [0002] The turbine blade is the part with the worst working environment in the engine. The creep deformation and creep permanent fracture of the turbine blade are important modes of turbine blade failure. The creep analysis of the turbine blade is an important content of engine design and field monitoring. Creep is a nonlinear deformation that increases with time, and blade creep is related to operating temperature, stress level and duration. [0003] The existing blade creep analysis generally adopts the general three-dimensional finite element method, considers the creep in the constitutive equation, and simulates the creep of the structure through the material creep parameters and discretized structural stiffness and applying correspondi...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/17
Inventor 成晓鸣郭飞跃章胜张勇吴立强胡锦文
Owner CHINA AVIATION POWER MACHINE INST
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