| abstract |
Methods of making gas turbine structures with cooling channels,nsuch as, for example, combustor/transition pieces for gas turbines having andouble wall with a plurality of cooling channels, having axially and/orncircumferential cross-flow passages positioned between the structure's innernmember and the outer member to provide cooling air thereto, are disclosed. Anrepresentative method of producing such annular structures having a hot and ancold wall, and joining ribs, for the inner and the outer components of an annulus,nsuch as for jet engine turbine combustors, to net shape as an annular pre-formnincludes: forming a pre-form assembly including materials for the hot wall, coldnwall, and ribs and sacrificial segments for maintaining cooling channels duringnforming of the pre-assembly and later processing; rolling the pre-form to anrequired thickness and length as a flat pre-form; hoop-rolling the preform to anrequired thickness and a required length; welding the assembly; ring rolling to thenpre-form to a desired inner diameter, ring-rolling or metal spinning the pre-form tonproduce the proper wall contour and removing the sacrificial material to open thencooling channels. |