Abstract: A method includes removing a casting shell and core from a cast component, which may be a gas turbine blade. The method further includes utilizing a focused removal technique, such as a water jet or laser drill, to remove a portion of a virtual pattern cast (VPC) shell from the cast component. The cast component is then exposed to a leaching solution and high pressure water wash to remove an internal core material and a portion of the VPC shell remainder from the cast component. The method further includes exposing the cast component to a high agitation leaching solution and to the high pressure water wash for a minimal time. An electroless nickel-boron coating is then applied to the cast component, and an electrolytic palladium coating is further applied to the cast component. The cast component is further exposed to a high agitation leaching solution for an extended period.

Abstract: A combination including a gas turbine engine extending along an axis is disclosed herein. The gas turbine engine includes an annular combustor having a combustor liner. The combination also includes a plurality of projections extending from the combustor liner and spaced from one another circumferentially about the axis. The combination also includes a free-standing ring disposed about the combustor liner and positioned adjacent to the plurality of projections along the axis. The plurality of projections engage the free-standing ring and circumferentially support the combustor liner while allowing relative radial displacement between the combustor liner and the free-standing ring. The combination also includes a plurality of pins each being integrally-formed with one of the plurality of projections. Each of the plurality of pins extends along the axis and is received in one of a plurality of slots formed in the free-standing ring.

Abstract: A method includes removing a casting shell and core from a cast component, which may be a gas turbine blade. The method further includes utilizing a focused removal technique, such as a water jet or laser drill, to remove a portion of a virtual pattern cast (VPC) shell from the cast component. The cast component is then exposed to a leaching solution and high pressure water wash to remove an internal core material and a portion of the VPC shell remainder from the cast component. The method further includes exposing the cast component to a high agitation leaching solution and to the high pressure water wash for a minimal time. An electroless nickel-boron coating is then applied to the cast component, and an electrolytic palladium coating is further applied to the cast component. The cast component is further exposed to a high agitation leaching solution for an extended period.

Abstract: A combination including a gas turbine engine extending along an axis is disclosed herein. The gas turbine engine includes an annular combustor having a combustor liner. The combination also includes a plurality of projections extending from the combustor liner and spaced from one another circumferentially about the axis. The combination also includes a free-standing ring disposed about the combustor liner and positioned adjacent to the plurality of projections along the axis. The plurality of projections engage the free-standing ring and circumferentially support the combustor liner while allowing relative radial displacement between the combustor liner and the free-standing ring. The combination also includes a plurality of pins each being integrally-formed with one of the plurality of projections. Each of the plurality of pins extends along the axis and is received in one of a plurality of slots formed in the free-standing ring.

Abstract: The present invention contemplates an apparatus for supporting an annular combustor liner in a gas turbine engine. In one embodiment, the apparatus includes a plurality of radial lugs extending outwardly from an outer surface of the combustor liner and being spaced circumferentially and uniformly about a periphery of the combustor liner. A band is disposed about the outer surface of the combustor liner and coupled to the radial lugs. The radial lugs each include a radially extending slot having opposing circumferentially facing radial surfaces. The band includes a plurality of pins, each pin being disposed within a respective one of the slots. The pin is configured to bear against at least one of the radial surfaces to provide circumferential support to the combustor liner by substantially preventing relative circumferential movement between the combustor liner and the band. The pin is slidable between the radial surfaces to allow relative radial movement between the combustor liner and the band.