A Parametric Model-Oriented Configuration Method for Air-cooled Turbine Blades
A parametric model and blade technology, applied in design optimization/simulation, special data processing applications, geometric CAD, etc., to achieve the effect of convenient follow-up processing
Active Publication Date: 2021-12-28
AECC SHENYANG ENGINE RES INST
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[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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[0028] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...
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The present invention relates to the design of aeroengine blades, in particular to a parametric model-oriented configuration method for turbine air-cooled blades, including: step 1, controlling the radial wall thickness of the blade through the two sections of the root and the top; , the positions of the three points on the trailing edge and the wall thickness parameters to control the wall thickness of the back side of the blade basin, so as to realize the variable wall thickness design of the turbine air-cooled blade and form the structural framework of the blade cavity; step 2, based on the predetermined design unit, take The internal cavity structure frame formed in step 1 is used as the object, and the topological unit is divided into the serpentine channel of the blade; step 3, by setting the geometric characteristic parameters of each unit, several topological units of the serpentine channel of the blade are connected into a pipe network calculation Model. The parametric model-oriented turbine air-cooling blade configuration method of the present invention is based on the parametric model modeling method, and uses the unit design method as the principle, and finally quickly obtains the formation pipe network calculation model 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...
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IPC IPC(8): G06F30/17G06F30/15G06F30/20
CPCG06F30/17G06F30/20
Inventor 吴伟龙吴向宇屈云凤王雷徐景亮韩绪军杜治能贺佳慧宋伟吕东
Owner AECC SHENYANG ENGINE RES INST