Patent ID: 8156648
Filing Date: 2012-04-17
Classification: B64D,F16C,Y10T

Abstract:
1. A method of manufacturing a hollow structural connecting rod for an aircraft engine assembly, said method comprising: manufacturing a first pre-form for a first connecting rod element from a first billet and a second pre-form for a second connecting rod element from a second billet, the manufacturing the first and second pre-forms resulting in to-be-connected first ends thereof having an added thickness of material compared to medial portions thereof; machining first and second hollow shanks in the first ends of the first and second pre-forms, respectively; flow-turning the first and second pre-forms, respectively, by inserting a rotating flow-turning cylindrical mandrel into the first and second hollow shanks, to lengthen the first and second hollow shanks, wherein a length of the first hollow shank is equal to a length of the second hollow shank; and assembling the first hollow shank to the second hollow shank at the first ends thereof to form an integrally joined assembly of said first and second connecting rod elements such that the joint between the first and second hollow shanks is located at a mid-length of the integrally joined assembly to take up aircraft engine thrust forces when said assembly is interposed between an aircraft engine structure and an engine.