Parameterized model-oriented design method of gas-cooled turbine blades
A technology of parametric models and design methods, applied in computing, electrical digital data processing, special data processing applications, etc.
Inactive Publication Date: 2018-05-01
AECC SHENYANG ENGINE RES INST
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[0006] The purpose of the present invention is to provide a kind of parameterized model-oriented turbine air-cooled blade design method, to solve at least one problem existing in the existing turbine air-cooled blade design method
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[0034] 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 invention relates to aeroengine blade design, and particularly to a parameterized model-oriented design method of gas-cooled turbine blades. The method includes the following steps: step 1, establishing a parameterized calculation model framework of the blades according to acquired heat transfer data of leaf-shape coordinate data; step 2, determining a basic cooling scheme form of the blades according to predetermined environment conditions; step 3, using an element design method as a principle to obtain a three-dimensional temperature field calculation result through a pipe network calculation program on the basis of a parameterized-model modeling manner; step 4, forming an initial scheme; and step 5, carrying out optimization design of the initial scheme of the blades. According to the parameterized model-oriented design method of the gas-cooled turbine blades of the invention, an entire design process of the blades is controlled through parameterization, the initial scheme can be quickly formed according to the temperature field calculation result, and a final initial scheme can be quickly obtained after optimization design.
Description
technical field [0001] The invention relates to the design of aeroengine blades, in particular to a parameterized model-oriented design 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 reserve of th...
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Login to View More IPC IPC(8): G06F17/50
CPCG06F30/17
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