Gas turbine transition duct profile

1. A transition duct comprising:

an inlet ring;

an aft frame; and,

a panel assembly extending therebetween and connecting the inlet ring to the aft frame, the panel assembly having an inlet end of generally circular cross section and a center and an outlet end of generally rectangular arc-like cross section, the panel assembly having an uncoated internal profile substantially in accordance with coordinates X, Y, and Z at an angle Θ, as set forth by Table 1, the X, Y, and Z values carried to three decimal places wherein the coordinates are relative to an origin at the center of the inlet end and taken at a sweep angle Θ that is measured from a first plane defined by the inlet end and increases toward a second plane defined by the outlet end, the planes intersecting at a line about which the angle Θ is measured, and wherein X, Y, and Z are coordinates defining the panel assembly profile at each angle Θ from said inlet end, with X, Y, and Z having an origin at the center of the inlet end, and a z-axis extending perpendicular from the first plane.

2. The transition duct of claim 1 , wherein the panel assembly comprises a first panel and a second panel, the first panel and second panel joined together along a plurality of generally axial seams.

3. The transition duct of claim 1 , wherein the internal profile for the panel assembly can vary up to 0.125 inches due to manufacturing tolerances.

4. The transition duct of claim 1 , wherein the transition duct panel assembly has a two-layer air plasma sprayed coating comprising a bond coating applied along the internal profile of the panel assembly and a top coating applied over the bond coating.

5. The transition duct of claim 4 , wherein the two-layer coating applied along the internal profile has a combined thickness of at least 0.019 inches.

6. The transition duct of claim 1 further comprising a plurality of cooling holes in the panel assembly.

7. The transition duct of claim 1 , wherein the panel assembly is fabricated from a high-temperature nicked-base alloy.

8. A transition duct comprising:

an inlet ring;

an aft frame;

a panel assembly extending between the inlet ring and the aft frame and connected thereto, the panel assembly having an inlet end generally circular in cross section having a center and an outlet end of generally rectangular arc-like cross section, the panel assembly having an uncoated internal profile with an envelope of +/− 0.250 inches in a direction normal to any surface formed from coordinate values X, Y, and Z at an angle Θ, as set forth in Table 1, the X, Y, and Z values carried only to three decimal places wherein the coordinates are relative to an origin at the center of the inlet end and taken at the sweep angle Θ, which is measured from a first plane defined by the inlet end and increases toward a second plane defined by the outlet end, the planes intersecting at a line about which the angle Θ is measured, and wherein X, Y, and Z are coordinates defining the panel assembly profile at each angle Θ from the inlet end, with X, Y, and Z having an origin at the center of the inlet end, and a z-axis extending perpendicular from the first plane.

9. The transition duct of claim 8 , wherein the panel assembly comprises a first panel and a second panel, the first panel and the second panel joined together along a plurality of generally axial seams.

10. The transition duct of claim 9 further comprising a plurality of cooling holes in the first panel.

11. The transition duct of claim 9 further comprising a plurality of cooling holes in the second panel.

12. The transition duct of claim 8 , wherein the transition duct panel assembly has a multi-layer coating comprising at least a bond coating applied along the internal profile of the panel assembly and a top coating applied over the bond coating.

13. The transition duct of claim 12 , wherein the two-layer coating applied along the internal profile has a thickness of at least 0.019 inches.

14. A gas turbine transition duct panel assembly comprising a first panel and second panel fixed together along a plurality of seams, the panel assembly having an inlet end and an outlet end with a first plane established at the inlet end and a second plane established at the outlet end, the panel assembly having an uncoated internal profile within an envelope of +/− 0.250 inches in a direction normal to any surface formed from coordinate values X, Y, and Z at an angle Θ, as set forth in Table 1, the X, Y, and Z values carried only to three decimal places wherein the coordinates are relative to an origin at the center of the inlet end and taken at the sweep angle Θ, which is measured from the first plane and increases toward a second plane defined by the outlet end, the planes intersecting at a line about which angle Θ is measured, and wherein X, Y, and Z are coordinates defining the panel assembly profile at each angle Θ from the inlet end, with X, Y, and Z having an origin at the center of the inlet end, and a z-axis extending perpendicular from the first plane.

15. The panel assembly of claim 14 further comprising a two-layer air plasma sprayed coating comprising a bond coating applied along the internal profile of the panel assembly and a top coating applied over the bond coating.

16. The panel assembly of claim 15 , wherein the two-layer coating applied along the internal profile of at least 0.019 inches thick.

17. The panel assembly of claim 14 further comprising a plurality of cooling holes in the first panel.

18. The panel assembly of claim 17 further comprising a plurality of cooling holes in the second panel.