Parametric model-based turbine air-cooled blade configuration method

A parametric model and blade technology, applied in the fields of electrical digital data processing, design optimization/simulation, special data processing applications, etc.

Active Publication Date: 2018-05-29
AECC SHENYANG ENGINE RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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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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  • Parametric model-based turbine air-cooled blade configuration method
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  • Parametric model-based turbine air-cooled blade configuration method

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Embodiment Construction

[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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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...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
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
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