Parametric model-based turbine air-cooled blade configuration method

Abstract

The invention relates to an aeroengine blade design, in particular to a parametric model-based turbine air-cooled blade configuration method. The method comprises the steps that 1, radial wall thickness of blades is controlled through root and top cross sections, and dorsal side wall thickness of the blades is controlled through positions of a leading edge point, a middle wing chord point and a tailing edge point and wall thickness parameters, so that a variable wall design of the turbine air-cooled blades is achieved to form a blade inner cavity structural frame; 2, based on a predetermined design unit, the inner cavity structural frame formed in step 2 is taken as an object, and topography unit division is conducted on serpentine channels of the blades; 3, a plurality of topography unitsof the serpentine channels of the blades are connected into a pipe network calculation model by setting geometric characteristic parameters of each unit. According to the method, a parametric model modeling method is taken as the basis, a unit design method is taken as a principle, and finally the pipe network calculation model is rapidly obtained to facilitate subsequent processing.

Description

technical field [0001] The invention relates to the design of aeroengine blades, in particular to a parameterized model-oriented configuration method for turbine air-cooled blades. Background technique [0002] Turbine air-cooled blades in aero-engines are subjected to high-temperature and high-pressure gas in the combustion chamber during operation, and large loads of centrifugal force, aerodynamic force, and thermal stress. The scheme design is difficult, the cycle is long, and the manufacturing cost is high. Reasonable and accurate design methods are required to achieve turbine air cooling. Rapid design of blades. [0003] The design of the turbine air-cooled blade scheme needs to complete multi-disciplinary collaborative evaluation - evaluate the working environment of the blade according to the overall performance parameters, the turbine aerodynamics professional provides the blade shape and heat transfer data, and the strength professional evaluates the strength reserv...

AI Technical Summary

Problems solved by technology

[0006] The purpose of the present invention is to provide a parameterized model-oriented turbine air-cooled blade configuration method to solve at least one problem existing in the existing turbine air-cooled blade configuration method

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