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Aerodynamic performance-preserving construction method for a near-net-shape blade cross section

机译：Aerodynamic performance-preserving construction method for a near-net-shape blade cross section

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摘要

Aeroengine blades are typical thin-walled structural parts, which are prone to deformations when forming near-net-shape blade blanks. The qualified blade body is produced by a precision blanking process, but with a small deformation. Moreover, the leading edge and trailing edge (LE/TE) connected to the blade body have excess material to be removed. Using the design blade model, it is difficult to machine the LE/TE to a contour that smoothly transitions to the deformed body. However, a LE/TE with smooth joints to the blade body can be machined by constructing a temporary guiding model that guides the finishing process based on blank measurement data. Unfortunately, this model has a discrepancy between its LE/TE shape and design's in order to smoothly join with the deformed blade body, which causes its aerodynamic performance to deviate from the design value. To address the above issues, we have developed an innovative method for constructing aerodynamic performance-preserving cross sections for temporary guiding models. First, geometric features that have a significant impact on the aerodynamic performance are selected as constraints. Second, we define the constraint equations for the geometric features of the thickness curve and the camber line. Finally, an affine transformation is used to construct the camber lines, and a progressive iterative least square fitting algorithm is refined to construct the thickness curves. The total pressure loss coefficient of the constructed cross sections is simulated using computational fluid dynamics tools. The results show that the proposed method can effectively reduce the effect of blank forming deformations on the aerodynamic performance of machined blades.

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