A Parametric Modeling Method for the Geometry Model of Gas-Heat Coupling Computational Domain of Turbine Blade

Abstract

The invention discloses a parametric modeling method of a turbine blade aero-thermal coupling computational domain geometric model. The parametric modeling method comprises the following steps that firstly, a blade model is imported into UG; a preliminary fluid computational domain covering the blade is created according to the blade model; then a mean camber blade body of the blade is created, is extended in a natural curvature manner along the four sides of the blade body and is made to be capable of penetrating through the preliminary fluid computational domain; the extended blade body is rotated to obtain a front boundary surface and a rear boundary surface of a blade fluid computational domain; an upper boundary surface and a lower boundary surface of the blade fluid computational domain are created according to specified heights; according to the preliminary fluid computational domain preliminarily obtained by trimming the upper boundary surface, the lower boundary surface, the front boundary surface and the rear boundary surface, contours of the surfaces, corresponding to the front edge and the tail edge of the blade, of the trimmed solid body are stretched to obtain a fluid inlet area and a fluid outlet area respectively; the created fluid computational domain and the blade body are subjected to Boolean subtraction; and an inner profile and an outer profile of the solid body of the blade are extracted, and according to the solid body obtained through segmentation of the inner profile and the outer profile and the Boolean subtraction, the aero-thermal coupling computational domain geometric model with a fuel gas domain and a cold air domain is obtained.

Description

technical field [0001] The invention relates to the field of turbine blade design, in particular to a parametric modeling method for a geometric model of a gas-thermal coupling computational domain of a turbine blade. Background technique [0002] In order to obtain a higher thrust-to-weight ratio and thermal efficiency, modern aviation gas turbine engines continuously increase the turbine inlet temperature. At present, the turbine inlet temperature has far exceeded the melting point temperature of the blade material, and complex cooling techniques must be used to maintain the normal operation of the turbine blades. Predicting the temperature field of turbine blades is a key issue to improve cooling efficiency and prolong the working life of blades. With the continuous development of computational fluid dynamics, gas-thermal coupling numerical simulation technology has become an important tool for predicting the temperature distribution of engine hot-end parts. However, for s...

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Problems solved by technology

[0005] (1) The creation of the geometric model of the gas-thermal coupling calculation domain of the turbine blade is an interdisciplinary problem, and there are few researches and related patents on its parametric modeling, which leads to the transition from the CAD model to the CAE model when performing the gas-thermal coupling numerical simulation of the turbine blade There are problems of model accuracy and modeling efficiency in the conversion of

[0006] (2) The existing method of determining the front and rear boundaries of the turbine blade fluid calculation area generally uses the curved surface of the blade basin or the back surface of the blade, resulting in asymmetric fluid calculation domains after segmentation, which affects subsequent mesh division and finite element analysis

[0007] (3) The geometric model modeling of the existing turbine blade gas-thermal coupling calculation domain is mainly the turbine blade with relatively simple internal flow path, and there is still a lack of geometric model modeling for some turbine blades with complex internal flow path gas-thermal coupling calculation domain

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