Patent ID: 9702267
Date: 2017-07-11
CPC Classifications: F01D,F05D

Claim:
1. A method for making an assembly of a gas turbine engine structure, the assembly including at least co-axially positioned annular outer and inner cases interconnected by a plurality of circumferentially spaced load transfer members extending radially between the outer and inner cases, the method comprising: (1) substantially forming the assembly of the gas turbine engine structure on a fixture by positioning the outer case and the inner case co-axially with each other on the fixture and affixing a radially-inner end of each of the load transfer members to the inner case while letting a radially-outer end portion of each of the load transfer members extend radially through one of a plurality circumferentially spaced openings defined in the outer case; (2) creating a plurality of commonly machined surfaces each provided by a machined end surface of one of the load transfer members flush with and surrounded by a machined surface of the outer case, by temporarily securing the substantially formed assembly on the fixture and machining the radially-outer end portion of the respective load transfer members exposed through the respective openings of the outer case and machining an area of the outer case surrounding each of the radially-outer ends; and then (3) securing the co-axial position of the outer and inner cases before the assembly is removed from the fixture by attaching a retaining device to the outer case to retain the respective commonly machined surfaces in place.