Analysis of machining deformation for adaptive CNC machining technology of near-net-shaped jet engine blade

Wu, Dongbo; Wang, Hui; Peng, Jinsong; Zhang, Kaiyao; Yu, Jiguo; Li, Yuan; Wang, Maomin; Zhang, Xindong

doi:10.1007/s00170-019-03898-6

Cited by 11 publications

(1 citation statement)

References 30 publications

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“…10,11 Inevitably, however, although blades before the grinding or polishing met the design tolerance needs, the clamping position, tool cutting force, cutting heat, residual stress, tool wear, and machining vibration can also lead to machining deformation. 12–14 The deformation will cause the actual blade profile to deviate from the original design and affect the aerodynamic performance of the compressor. Lebele-Alaw et al 15 studied the relationship between blade twist and its power consumption, and found that blade profile twist caused the airflow deflection angle to increase, resulting in an increase in compressor power consumption and a decrease in efficiency.…”

Section: Introductionmentioning

confidence: 99%

Research on blade grouping method for array machining

Xiao-dong

Zhang

2021

Proceedings of the Institution of Mechanical Engineers, Part B:

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Blades are the core component of aero-engines. The complexity of aero-engine blades deformation after multi-axis milling causes poor consistency in batch blades. In turn, the poor consistency of blades affects the aerodynamic performance of an aero-engine. Hence it is critical to ensure the consistency of blades before precise machining. This article proposes a clustering-based blade grouping strategy aiming to improve the consistency of the same group of blades automatically and efficiently. First, the feature vector of the blade and the distance between two blade surfaces are defined. Then the K-medoids clustering algorithm is used to group the blades. According to the maximum allowable distance between the blade surfaces and the Ray-Turi index, the ideal number of clusters, that is the number of groups, is determined. Finally, the clustering center of each cluster is selected as the blade processing model of each group. The experiment for aero-engine blade grouping and machining was performed to demonstrate the effectiveness of the proposed method and the results show that it can improve the consistency of the blades in each group. The geometric contour differences of the blades in the group are not more than 0.02 mm, which can satisfy the requirements of the following precise array machining.

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