Aviation blade cross section molded line contour parameter evaluation method and system

Abstract

The invention discloses an aviation blade cross section molded line contour parameter evaluation method and system, and belongs to the field of aviation blade detection. The method comprises: performing ICP matching on a theoretical data point set P and a blade profile contour point set Q to obtain an initial matching result; dividing q into a front edge sub-point set, a rear edge sub-point set, a blade basin sub-point set and a blade back sub-point set, and setting a tolerance zone range for each sub-point set; endowing each measuring point in each sub-point set with a coefficient according to the position relationship between the measuring point and the corresponding tolerance zone range; taking the x offset, the y offset and the torsion angle of the Q as to-be-optimized quantities, taking each measuring point coefficient as a weight, and constructing a target function with position constraint; enabling the initial matching result to be an initial value, and solving the target function to obtain an optimal matching result; and performing rigid body transformation by using the optimal matching result, comparing the aviation blade subjected to rigid body transformation with a design model, and judging whether the aviation blade is qualified or not. Different coefficients are given to different area measuring points, the target function with position constraint is constructed, the torsional angle and the offset are introduced, and the actual detection requirements are better met.

Description

technical field [0001] The invention belongs to the field of aviation blade detection, and more particularly relates to a method and system for evaluating parameters of a cross-section profile of an aviation blade. Background technique [0002] The aero-engine is a key component of the aircraft, and the blade of the aero-engine is the main component that determines the performance of the engine, which has a great impact on the power, reliability and economy of the aircraft flight. Therefore, the quality inspection requirements of aviation blade profiles are very strict. [0003] Patent CN111400667A discloses a method and system for detecting the profile of an aviation blade based on variable tolerance zone constraints. Concentrated down-sampling of profile measuring points to obtain sampled leaf profile measuring points; random fitting of circles using sampled leaf profile measuring points to achieve leaf profile segmentation and obtain leading edge point sets, trailing edg...

AI Technical Summary

Problems solved by technology

However, there are the following defects: using the Lagrange multiplier method to solve the objective function, there are many parameters and the calculation is complicated

However, there are the following defects: the torsion constraint and position constraint are not added to the actual matching process, but only after each match is completed to detect whether the torsion error and position error meet the detection requirements, the blade matching process and the offset, torsion angle Constraint process is separated

However, this method does not consider that the tolerances of the leading edge, trailing edge, blade pot, and blade back area of ​​the aviation blade are often different, that is, the accuracy requirements of each area are different, resulting in the error value of the area points with small tolerances often being out of tolerance , resulting in distorted matching results

At the same time, the torsion angle and offset of the airfoil matching are not evaluated, so that the blades with unqualified torsion angle and offset may be misjudged by the existing method.

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