Aviation-engine-blade-surface data evaluation method based on model

An aero-engine and evaluation method technology, applied in the direction of measuring devices, instruments, etc., can solve the problems that the measurement results cannot reflect the real situation of the parts, the evaluation method of profile measurement data is unreasonable, and the measurement reproducibility is poor, so as to improve the detection technology and detection. efficiency, improving product quality and testing efficiency, and the effect of stable operation quality

Active Publication Date: 2019-03-15
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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Problems solved by technology

[0005] In view of the unreasonable and non-standard evaluation method of profile measurement data in the detection process of aero-engine blades in the prior art, which leads to the shortcomings that the measurement results cannot reflect the real situation of the pa

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  • Aviation-engine-blade-surface data evaluation method based on model
  • Aviation-engine-blade-surface data evaluation method based on model
  • Aviation-engine-blade-surface data evaluation method based on model

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Embodiment Construction

[0033] The present invention will be further elaborated below in conjunction with the accompanying drawings of the description.

[0034] A kind of model-based evaluation method of aeroengine blade profile data of the present invention comprises the following steps:

[0035] 1) The profile of the blade profile to be evaluated is the line profile without reference, and the line profile is fitted with the theoretical profile before the evaluation;

[0036] 2) Thicken the existing blade profile design model, and generate a new blade profile through the blade curve group as a theoretical model for profile evaluation;

[0037] 3) In the case of ensuring that the position of the tolerance zone of the blade profile remains unchanged, change the upper and lower limit values ​​of the tolerance zone, change the original tolerance +0.05mm~-0.01mm, and set the new tolerance to +0.03mm~-0.03 mm, make the contour tolerance zone a symmetrical tolerance zone;

[0038] 4) Use the theoretical ...

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Abstract

The invention discloses an aviation-engine-blade-surface data evaluation method based on a model. The method includes the steps that the profile degree of an evaluated blade surface is a linear profile degree, and the linear profile degree and a theory molded line fit before evaluation; an existing blade-surface design model is thickened, a new blade surface is generated through a curve set of a blade to serve as a theory model of profile degree evaluation; under the condition that it is guaranteed that the position of a blade-surface tolerance band is invariable, an upper limiting value and alower limiting value of the tolerance band are changed, original tolerance is changed to be +0.05 mm to -0.01 mm, new tolerance is changed to be +0.03 mm to -0.03 mm, and the profile tolerance band is a symmetry tolerance band; theory data of the thickened theory model is used as a theory molded line that the profile degree evaluates the blade-surface profile degree. According to the aviation-engine-blade-surface data evaluation method based on the model, reality of a part is reflected, the measuring reproducibility is good, integrated development from the engine detection technology capacityto digitization designing, manufacturing and detecting is promoted, and the key detection technology and detection efficiency are improved.

Description

technical field [0001] The invention relates to an aeroengine blade data evaluation technology, in particular to a model-based aeroengine blade profile data evaluation method. Background technique [0002] The geometric shape of the aeroengine blade has irregular curved surface features, and the curved surface is a closed curve along the airflow direction. In the acceptance of the geometric dimension of the blade surface, 4 to 5 sections are selected along the direction of the blade coordinate system (such as figure 1 shown) to evaluate the blade parameters. [0003] The design requires parameters such as profile degree, position degree, chord angle and chord length to be evaluated according to the design model. Judging from the design model and the distribution of the tolerance zone, the tolerance zone of the blade profile is -0.01~+0.05, the thickness of the blade is allowed to be 0.05mm, and the thickness is only 0.01mm (such as figure 2 As shown), regardless of the de...

Claims

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Application Information

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IPC IPC(8): G01B21/20
CPCG01B21/20
Inventor 张露穆轩高阳任丽芬高金磊
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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