Composite material blade design method

A composite material and design method technology, applied in design optimization/simulation, computer-aided design, calculation, etc., can solve problems such as low efficiency, avoid a lot of waste, avoid a lot of design to process iteration work, and improve design efficiency.

Active Publication Date: 2021-02-02
AECC SHENYANG ENGINE RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Therefore, the current technological path for composite blade design is less efficient

Method used

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  • Composite material blade design method
  • Composite material blade design method
  • Composite material blade design method

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Embodiment Construction

[0053]In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application. 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 application. The embodiments described below by referring to the figures are exemplary, and are intended to explain the present application, and should not be construed as limiting the present application. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application. Embodiments of the present application will be described in detail below in conjunction with the...

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Abstract

The invention belongs to the technical field of engine maintenance equipment design, and particularly relates to a composite material blade design method which comprises the following steps: 1, calculating the number distribution of composite material blade layouts; 2, calculating the accuracy of the layering number partition, and judging whether the accuracy of the layering number partition meetsthe design requirement or not; if yes, determining the layering number partition of the blade, and carrying out the step 3; if not, returning to the step 1, and adjusting the accuracy of the layeringnumber partition until the design requirement is met; and step 3, carrying out fiber direction and tailoring design on each laying layer of the composite material blade. According to the design method of the composite material blade, forward design of the composite material blade is achieved, the technical problem in a semi-reverse design method based on a process test is solved, the design intention can be fully implemented, consumption of materials and labor cost in the repeated iteration process is reduced, process iteration of a trial paving method is avoided, and the design efficiency ofthe composite material blade is improved. Improving design efficiency.

Description

technical field [0001] The application belongs to the technical field of engine maintenance equipment design, and in particular relates to a design method for composite material blades. Background technique [0002] With the development of composite material design and processing technology, composite material structural parts have been more and more widely used in aero-engines. At present, in the field of aero-engines, resin-based composite materials are mainly used in components such as outer casings, fan rotor blades, and stator segments. More and more attention has been paid to advantages such as height limit. [0003] Aeroengine blades (especially fan / compressor blades) have small thickness but large variations, and have obvious bending, twisting, sweeping and other modeling characteristics. These characteristics pose great challenges to the structural design of composite blades. [0004] At present, at the beginning of the design of composite material blades, the bl...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/17G06F30/23
CPCG06F30/23G06F30/17G06F2113/26
Inventor 曹铁男杨吉星宋旭圆
Owner AECC SHENYANG ENGINE RES INST
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