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Feature Recognition Method of Aeroengine Blisk

A technology of aero-engine and blisk, which is applied in the field of CAD/CAM, can solve the problems of low accuracy, low efficiency of identification methods, lack of feature recognition function of aero-engine blisk in CAM system, etc., and achieve high accuracy and recognition high efficiency effect

Active Publication Date: 2017-07-28
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0005] The purpose of the present invention is that the current CAM system lacks the feature recognition function for the overall blisk of the aero-engine, and the existing identification method has low efficiency and low accuracy, which affects the design of the work procedure, and invents a feature of the blisk of the aero-engine recognition methods

Method used

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  • Feature Recognition Method of Aeroengine Blisk
  • Feature Recognition Method of Aeroengine Blisk
  • Feature Recognition Method of Aeroengine Blisk

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Embodiment Construction

[0031] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0032] Such as Figure 1-10 shown.

[0033]A feature recognition method for an aero-engine blisk, which can be summarized as follows: first, according to the structural characteristics of the aero-engine blisk, the machining feature of the aero-engine blisk is defined as a combination of a series of blade features and flow channel features. Secondly, the efficient feature recognition of blade features and flow channel features is carried out. Firstly, the part processing coordinate system is established, the parting surface is set, and then all geometric topological elements are uniquely identified, and the holographic attribute surface-edge graph is constructed, and the complete surface nodes and nodes are defined. Edge node attributes, and finally search for various special seed faces based on the holographic attribute face-edge graph, and identify t...

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Abstract

An aero-engine blisk feature recognition method is characterized by including the following steps that structural characteristics of a blisk part of an aero-engine are analyzed, and features and channel features of blades of a blisk are defined; the blisk part is preset and a holographic attribute face-edge graph is built; face search is carried out on the basis of a seed face, a parting surface and an expansion rule, and blade processing features are constructed; the corresponding channel features are constructed according to feature elements of two adjacent blades; information of the blades and the channel features is extracted, and a feature recognition result is obtained and stored in an XML file. The method can cover feature types of milling and cutting of the blisk, is high in recognition efficiency and accuracy, lays a foundation for improving the automation degree of blade processing, and provides an effective means for data transmission among CAD / CAPP / CAM systems.

Description

technical field [0001] The invention relates to a CAD / CAM technology, in particular to a CAD / CAM technology for improving the machining level of an aero-engine integral blisk, in particular to a feature recognition method for an aero-engine integral blisk. Background technique [0002] At present, CAD, CAPP, and CAM systems play a big role in product design, process design and NC programming respectively. However, these systems are independent and cannot realize automatic conversion and sharing of information between systems, and the degree of automation and efficiency in the application process are low. The integration of CAD / CAPP / CAM for the purpose of improving the automation and efficiency of product design, process design and NC programming has become an urgent need in the industry, and feature recognition technology can realize data transfer between systems, which is the key to realizing CAD / CAPP / An effective way of CAM integration. [0003] With the increasing thru...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
Inventor 李迎光刘旭马斯博郝小忠
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS