A design method for the final stage stator and intermediate casing support plate of a fan

Abstract

This application provides a design method for a fan's final-stage stator and intermediate casing support plate, belonging to the technical field of compression systems in aero-engines. Specifically, the final-stage stator and intermediate casing support plate are shaped as an integrated blade structure. The shaping method includes: determining the number and distribution of spanwise basic airfoils in the integrated blade structure; determining the inlet geometry, maximum thickness, and maximum thickness position of each basic airfoil; adjusting the chord length of the basic airfoils at different spanwise positions according to the sweep of the three-dimensional shape of the final-stage stator; adjusting the bend angle distribution of the stator segments of the basic airfoils at different spanwise positions according to the bend of the three-dimensional shape of the final-stage stator; and radially stacking the basic airfoils at their trailing edges to obtain the integrated blade structure. This method can reduce the impact of the support plate's potential on the upstream stator while meeting the requirements of the support plate structure, achieving an ultra-compact intermediate casing design integrating the stator and support plate.

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