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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 ab

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.

대표청구항 ▼

1. A combination, comprising:a gas turbine engine including an annular combustor, said annular combustor having a combustor liner; a plurality of circumferentially spaced apart projections extending from said combustor liner; a free-standing ring disposed about said combustor liner and positioned ad

1. A combination, comprising:a gas turbine engine including an annular combustor, said annular combustor having a combustor liner; a plurality of circumferentially spaced apart projections extending from said combustor liner; a free-standing ring disposed about said combustor liner and positioned adjacent said plurality of projections; and wherein a number of said projections engage a corresponding circumferentially facing portion of said ring and circumferentially support said combustor liner while allowing relative radial displacement between said combustor liner and said ring.