Front and rear edge profile redesign method for adaptive processing

A front and back edge redesign technology, applied in computing, image data processing, 3D modeling, etc., to improve algorithm efficiency, reduce machining allowance shortage, and narrow search range

Inactive Publication Date: 2016-01-20
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

A small amount of literature has been published on the redesign of the leading and trailing edges of the blade. For example, the literature "Reconstruction of the model of the leading and trailing edges of precision forging blades for adaptive machining (Lin Xiaojun et al., Acta Aeronautica Sinica, 2015, 05: 1695-1703)" introduced a method based on cross-section. The method of reconstructing the leading and trailin

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  • Front and rear edge profile redesign method for adaptive processing
  • Front and rear edge profile redesign method for adaptive processing
  • Front and rear edge profile redesign method for adaptive processing

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Embodiment Construction

[0030] The present invention will be further described in detail below in conjunction with the accompanying drawings and examples. The following examples are explanations of the present invention and the present invention is not limited to the following examples.

[0031] As shown in the figure, a method for redesigning the shape of the leading and trailing edges of blade parts oriented to adaptive processing in the present invention is characterized in that it includes the following steps:

[0032] A. Airfoil section line division

[0033] Extract the section line of the airfoil, divide the section line into the proximal area A, the transition area B and the blade body area C, and take the midpoint on the arc segment of the proximal area as the centroid K. The leading edge of the proximal region is denoted as A q , and the proximal region of the trailing edge is denoted as A h , similarly with leading edge / trailing edge transition (B q / B h ) and leading / trailing centroid...

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Abstract

The invention discloses a front and rear edge profile redesign method for adaptive processing. A blade-shaped crosshatch is divided into a front and rear edge near-end area, a transitional area and a blade body area, a tolerance area of the centroids of the front and rear edge near-end area is determined according to tolerance requirements for blade components, the tolerance area of the centroids is optimized to obtain a tolerance track which reflects the torsion deformation and position deformation, to satisfy the processing balance, coordinates of the centroids of the front and rear edge near-end area are transformed to obtain a redesign contour of the front and rear edge near-end area of the blade, a contour of the transitional area is fit under the constraint of smooth connection between the near-end area and the blade body, the front and rear edges are combined, the crosshatch is redesigned, and further the curved profile of the front and rear edges is obtained. The method has the advantages that the front and rear edges which are not arched can be processed, and the searching range is narrow during contour adjustment.

Description

technical field [0001] The invention relates to the field of profile design of the leading and trailing edges of blades, in particular to a method for redesigning the profile of leading and trailing edges of blade parts for adaptive processing. Background technique [0002] Blades are the key parts of aero-engines. In order to improve the performance of the engines, new blade structures have been continuously developed, which also put forward higher requirements for the manufacturing process. A new class of sandwich hollow wide-chord blades in aero-engines, the typical manufacturing process is: first use superplastic forming / diffusion connection to obtain a near-net-shaped blade blank that is very close to the size and shape of the blade, and then use adaptive CNC cutting to The front and rear edges are processed, and finally the surface including the blade profile is polished to obtain a blade that meets the design requirements. [0003] The middle part of the airfoil obta...

Claims

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Application Information

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IPC IPC(8): G06T17/00
Inventor 刘胜兰王福海张丽艳袁稳
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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