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A gas turbine engine comprising an annular reverse-flow combustor having a sheet metal combustor wall between a long exit duct portion and a small exit duct portion of the combustor. An exit duct portion of the combustor forms a sliding joint with a downstream turbine vane assembly and has at least

A gas turbine engine comprising an annular reverse-flow combustor having a sheet metal combustor wall between a long exit duct portion and a small exit duct portion of the combustor. An exit duct portion of the combustor forms a sliding joint with a downstream turbine vane assembly and has at least two discrete sheet metal walls fastened to the sheet metal combustor wall at a common intersection region.

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The invention claimed is: 1. An annular reverse-flow combustor for a gas turbine engine comprising: an outer combustor liner; an inner sheet metal combustor liner; and an exit duct portion disposed at an exit of the combustor and being fastened to the inner sheet metal combustor liner, the exit duc

The invention claimed is: 1. An annular reverse-flow combustor for a gas turbine engine comprising: an outer combustor liner; an inner sheet metal combustor liner; and an exit duct portion disposed at an exit of the combustor and being fastened to the inner sheet metal combustor liner, the exit duct portion having first and second sheet metal walls radially spaced from each other at downstream ends thereof such that the exit duct portion is adapted to form a sliding-type joint with an outer platform of a turbine vane assembly disposed downstream from the exit of the combustor, wherein the first and second sheet metal walls of the exit duct portion and the inner sheet metal combustor liner are independently formed and fastened together along a common annular interface, and wherein a single attachment fastens the first and second sheet metal walls and the inner sheet metal combustor liner together at said common annular interface. 2. The combustor as defined in claim 1, wherein the attachment means is an annular weld. 3. The combustor as defined in claim 2, wherein the annular weld is continuous and performed in a single manufacturing operation. 4. The combustor as defined in claim 1, wherein the common annular interface is defined by one of the first and second sheet metal walls abutted end-to-end to the inner sheet metal combustor liner to define an annular joint therebetwcen, and the other of the first and second sheet metal walls overlaps the annular joint. 5. The combustor as defined in claim 4, wherein the first and second sheet metal walls and the inner sheet metal combustor liner are fastened together by a single weld about the annular joint. 6. The combustor as defined in claim 5, wherein the single weld comprises a butt and lap welded joint performed in a single operation. 7. A gas turbine engine comprising an annular reverse-flow combustor having a sheet metal combustor wall and a combustor exit defined between radially inner and outer exit duct portions of the combustor, the radially outer exit duct portion being fastened to an inner liner of the sheet metal combustor wall and being adapted for forming a sliding joint with a downstream turbine vane assembly, the radially outer exit duct portion having at least two discrete sheet metal walls fastened to the inner liner of the sheet metal combustor wall at a common interface, and wherein the two discrete sheet metal walls and the sheet metal combustor wall are fastened together about a single annular joint at the common interface, a single attachment fastening the two discrete sheet metal walls and the sheet metal combustor wall together. 8. The gas turbine engine as defined in claim 7, wherein the attachment means is an annular weld. 9. The gas turbine engine as defined in claim 8, wherein the annular weld is continuous and performed in a single manufacturing operation. 10. The gas turbine engine as defined in claim 7, wherein one of the two discrete sheet metal walls is abutted end-to-end to the sheet metal combustor wall to define an annular joint therebetween, and the other of the two discrete sheet metal walls overlaps the annular joint. 11. The gas turbine engine as defined in claim 10, wherein the two discrete sheet metal walls and the sheet metal combustor wall are fastened together by a single weld about the annular joint. 12. The gas turbine engine as defined in claim 11, wherein the single weld comprises a butt and lap welded joint. 13. A method of forming a gas turbine engine annular reverse flow combustor having a combustor liner, the method comprising forming at least an exit duct of the combustor out of sheet metal, including the steps of: forming discrete first and second sheet metal wall portions of the exit duct; abutting one of the first and second sheet metal wall portions to an end of the combustor liner, defining an annular joint therebetween; overlaying the other of the first and second sheet metal wall portions over the annular joint on an outer side of the combustor, such that the first and second sheet metal wall portions and the combustor liner meet at the annular joint; and fastening the first and second sheet metal wall portions and the combustor liner together along the annular joint, including welding the first and second sheet metal wall portions and the inner combustor liner together at the annular joint. 14. The method as defined in claim 13, further comprising performing the welding about the annular joint in a single manufacturing operation. 15. The method as defined in claim 13, wherein the step of forming further comprises forming the discrete first and second sheet metal wall portions further into nestable annular components of the exit duct which each define a substantially U-shaped cross-sectional area.