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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 circumferen

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.

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1. A combination comprising: a gas turbine engine extending along an axis and including an annular combustor having a combustor liner;a plurality of projections extending from said combustor liner and spaced from one another circumferentially about said axis, wherein each of said plurality of projec

1. A combination comprising: a gas turbine engine extending along an axis and including an annular combustor having a combustor liner;a plurality of projections extending from said combustor liner and spaced from one another circumferentially about said axis, wherein each of said plurality of projections extends from a base to a distal end and includes a flange projecting along said axis from the distal end, wherein a notch cutout extends through each of said flanges from the plurality of projections along said axis in an at least partially radial direction relative to said axis, and wherein said flange includes a radially inward facing surface;a free-standing ring disposed about said combustor liner and positioned adjacent to said plurality of projections along said axis, wherein said free-standing ring includes a plurality of slots formed therein;a leaf seal having a radially outer surface; anda plurality of pins, each pin being integrally formed with one of said plurality of projections and extending along said axis, wherein each of said plurality of pins is received into one of said plurality of slots,wherein said plurality of pins engage said free-standing ring via said plurality of slots, and wherein said plurality of pins and said plurality of slots are positioned to circumferentially support said combustor liner by virtue of the engagement of the plurality of pins with the plurality of slots while allowing relative radial displacement between said combustor liner and said free-standing ring;wherein said radially inward facing surface is positioned to radially constrain the leaf seal against outward radial movement via the radially outer surface and said notch is positioned to constrain the leaf seal against circumferential movement; andwherein the leaf seal does not include an opening therein. 2. The combination of claim 1 wherein each of said plurality of pins are further defined as extending away from only one axial side of said plurality of projections. 3. The combination of claim 2 wherein each of said plurality of pins are further defined as extending away in an aft direction from an aft axial side of said plurality of projections. 4. The combination of claim 1 wherein said notches and said pins are disposed on opposite sides of said projections. 5. The combination of claim 1 further comprising: a plurality of leaf seals arranged about said combustor liner and abutting said plurality of projections, at least part of each of said leaf seals received in one of said notches for limiting circumferential movement of said plurality of leaf seals relative to said plurality of projections. 6. The combination of claim 5 wherein said plurality of leaf seals further comprises: a first layer of leaf seals abutting said plurality of projections; anda second layer of leaf seals abutting said first layer of leaf seals and spaced from said plurality of projections along said axis, wherein said first and second layers of leaf seals engage alternating and opposite projections. 7. The combination of claim 1 wherein said free-standing ring further comprises: a first radially-extending flange disposed on a first side of said plurality of projections along said axis; anda second radially-extending flange disposed on a second side of said plurality of projections along said axis opposite said first side, wherein said plurality of slots are formed only in one of said first and second radially-extending flanges. 8. The combination of claim 7 further comprising: a plurality of leaf seals arranged circumferentially about said combustor liner between said plurality of projections and said first radially-extending flange, said first radially-extending flange and said plurality of leaf seals contacting one another at a radially-innermost edge and at a radially-outermost edge, wherein contact between said first radially-extending flange and said plurality of leaf seals is radially continuous between said radially-innermost edge and said radially-outermost edge. 9. The combination of claim 8 wherein contact between said first radially-extending flange and said plurality of leaf seals is circumferentially substantially continuous about said axis. 10. The gas turbine engine of claim 1, wherein each pin includes opposing flat surfaces, wherein said plurality of pins are received into and engage said plurality of slots with said opposing flat surfaces to support said combustor liner by virtue of the engagement of the opposing flat surfaces of the plurality of pins with the plurality of slots while allowing relative radial displacement between said combustor liner and said free-standing ring. 11. A method comprising the steps of: extending a gas turbine engine including an annular combustor having a combustor liner along an axis;extending a plurality of projections spaced from one another circumferentially about the axis radially outward from the combustor liner, wherein each of said plurality of projections extends from a base to a distal end and includes a flange projecting along said axis from the distal end, wherein a notch cutout extends through each of said flanges from the plurality of projections along said axis in an at least partially radial direction relative to said axis, and wherein said flange includes a radially inward facing surface;extending a plurality of pins along the axis from the plurality of projections, wherein each pin is formed integrally with one of said plurality of projections;disposing a free-standing ring about the combustor liner adjacent to theplurality of projections along the axis, wherein the free-standing ring includes a plurality of slots formed therein;positioning the plurality of slots and the plurality of pins to circumferentially support the combustor liner;engaging the plurality of slots of the free-standing ring with the plurality of projections pins;providing a leaf seal having a radially outer surface, wherein the leaf seal does not include an opening therein;radially constraining the leaf seal using the radially inward facing surface against the radially outer surface;positioning the notch to constrain the leaf seal against circumferential movement;radially constraining the leaf seal against circumferential movement; andcircumferentially supporting the combustor liner with the plurality of pins by virtue of the engagement of the plurality of pins with the plurality of slots while allowing relative radial displacement between the combustor liner and the free-standing ring. 12. The method of claim 11 further comprising the step of: forming the projection to define a recessed portion for receiving a seal, the recessed portion bound at least in part by a first wall being arcuate and extending circumferentially about the axis and by a second wall extending radially relative to the axis with at least one shoulder defined at a junction of the first and second walls. 13. The method of claim 11 further comprising the steps of: disposing the plurality of projections between first and second radially-extending flanges of the free standing ring; andpositioning the pins in slots formed by only by the first radially-extending flange. 14. The method of claim 13 further comprising the step of: forming a seal between the second radially-extending flange and the plurality of projections wherein the seal is continuous both circumferentially and radially relative to the axis. 15. The method of claim 11 further comprising the step of: projecting each of the plurality pins from respective distal ends of the plurality of projections. 16. A gas turbine engine comprising: an annular combustor extending along an axis of said gas turbine engine, and having a combustor liner extending along said axis;a plurality of projections extending from said combustor liner and evenly spaced from one another circumferentially about said axis, wherein each of said plurality of projections extends from a base to a distal end and includes a flange projecting along said axis from the distal end, wherein a notch cutout extends through each of said flanges from the plurality of projections along said axis in an at least partially radial direction relative to said axis, and wherein said flange includes a radially inward facing surface;a plurality of pins extending from the plurality of projections, wherein each pin includes first opposing flat surfaces;a free-standing ring disposed about said combustor liner and positioned adjacent to said plurality of projections along said axis and having a plurality of slots, wherein each slot has second opposing flat surfaces positioned to engage the first opposing flat surfaces; anda leaf seal having a radially outer surface, wherein the leaf seal does not include an opening therein,wherein said first opposing flat surfaces are received into and engage said second opposing flat surfaces, and wherein said first opposing flat surfaces and said second opposing flat surfaces are positioned to form a cross-key arrangement that supports said combustor liner by virtue of the engagement of the first opposing flat surfaces with the second opposing flat surfaces while allowing relative radial displacement between said combustor liner and said free-standing ring; andwherein said radially inward facing surface is positioned to radially constrain the leaf seal against outward radial movement via the radially outer surface and said notch is positioned to constrain the leaf seal against circumferential movement. 17. The gas turbine engine of claim 16 wherein a cross-section of at least one of said pins is substantially rectangular. 18. The gas turbine engine of claim 16 wherein said free-standing ring further comprises: a first radially-extending flange disposed on a forward side of said plurality of projections along said axis; anda second radially-extending flange disposed on an aft side of said plurality of projections along said axis, wherein said plurality of slots are formed only in said second radially-extending flange and said first radially-extending flange is circumferential and radially continuous about said axis. 19. The gas turbine engine of claim 18 further comprising: first and second layers of leaf seals arranged circumferentially about said combustor liner between said plurality of projections and said free-standing ring, said free-standing ring and said second layer of leaf seals contacting one another at a radially-innermost edge and-at a radially-outermost edge, wherein contact between said first radially-extending flange and said second layer of leaf seals is fully continuous between said radially-innermost edge and said radially-outermost edge and substantially continuous circumferentially about said axis. 20. The gas turbine engine of claim 19 wherein said combustor liner further comprises: a radially-outer liner half;a radially-inner liner half encircled by said radially-outer liner half, a combustion chamber defined between said radially-outer liner half and said radially-inner liner half, wherein said plurality of projections extend from at least one of said radially-outer liner half and said radially-inner liner half. 21. A gas turbine engine comprising: a combustor liner extending along an axis of the gas turbine engine, wherein said combustor liner includes a plurality of projections extending radially from said combustor liner substantially perpendicular to said axis, wherein said combustor liner includes a plurality of pins extending from said projections in a direction along said axis; wherein at least one pin extends from each projection; and wherein each pin includes first opposing flat surfaces, each flat surface extending in a plane approximately perpendicular to a circumferential direction about said axis, wherein each of said plurality of projections extends from a base to a distal end and includes a flange projecting along said axis from the distal end, wherein a notch cutout extends through each of said flanges from the plurality of projections along said axis in an at least partially radial direction relative to said axis, and wherein said flange includes a radially inward facing surface;a leaf seal having a radially outer surface, wherein the leaf seal does not include an opening therein; anda free-standing ring disposed about said combustor liner and positioned adjacent to said plurality of projections along said axis, wherein said freestanding ring includes a plurality of radially-extending slots in positional correspondence with said plurality of pins, each slot including second opposing flat surfaces;wherein said plurality of pins are received into and engage said plurality of slots, and wherein said first opposing flat surfaces and said second opposing flat surfaces are positioned to form a cross-key arrangement that supports said combustor liner and allows relative radial displacement between said combustor liner and said free-standing ring; andwherein said radially inward facing surface is positioned to radially constrain the leaf seal against outward radial movement via the radially outer surface and said notch is positioned to constrain the leaf seal against circumferential movement.