Integrated combustor nozzles with continuously curved liner segments
An integrated combustor nozzle includes an inner liner segment; an outer liner segment; and a panel extending radially between the inner and outer liner segments. The panel includes a forward end, an aft end, and a side walls extending axially from the forward end to the aft end. The aft end defines a turbine nozzle having a trailing edge circumferentially offset from the forward end. The inner liner segment has a pair of sealing surfaces, each of which defines a first continuous curve in the circumferential direction. The outer liner segment has a pair of sealing surfaces, each of which defines a second continuous curve in the circumferential direction. In some instances, the curves are monotonic in the circumferential direction. A segmented annular combustor including an array of such integrated combustor nozzles is also provided.
1. An integrated combustor nozzle comprising:
an inner liner segment, the inner liner segment having a first sealing surface and a second sealing surface circumferentially spaced apart from the first sealing surface;
an outer liner segment disposed opposite the inner liner segment, the outer liner segment having a third sealing surface and a fourth sealing surface circumferentially spaced apart from the third sealing surface;
a panel extending radially between the inner liner segment and the outer liner segment, the panel having a forward end, an aft end, a first side wall extending axially from the forward end to the aft end, and a second side wall opposite the first side wall and extending axially from the forward end to the aft end, the aft end defining a turbine nozzle having a trailing edge circumferentially offset from the forward end;
wherein the inner liner segment extends axially between a first upstream end and a first downstream end extending axially beyond the trailing edge, each of the first sealing surface and the second sealing surface having an inner sealing surface forward end at the first upstream end circumferentially offset from an inner sealing surface aft end at the first downstream end, and wherein each respective sealing surface of the inner liner segment curves continuously from the inner sealing surface forward end to the inner sealing surface aft end; and
wherein the outer liner segment extends axially between a second upstream end and a second downstream end extending axially beyond the trailing edge, each of the third sealing surface and the fourth sealing surface having an outer sealing surface forward end at the second upstream end circumferentially offset from an outer sealing surface aft end at the second downstream, and wherein each respective sealing surface of the outer liner segment curves continuously from the outer sealing surface forward end to the outer sealing surface aft end.
2. The integrated combustor nozzle of claim 1 , wherein the curve of the first sealing surface, the second sealing surface, the third sealing surface, and the fourth sealing surface is monotonic in the circumferential direction.
3. The integrated combustor nozzle of claim 1 , wherein the curve of the first sealing surface and the second sealing surface or the curve of the third sealing surface and the fourth sealing surface comprises an inflection point in the radial direction.
4. The integrated combustor nozzle of claim 1 , wherein the first sealing surface and the second sealing surface of the inner liner segment each define a seal slot having a depth, and wherein the depth of a first seal slot in the first sealing surface is equal to the depth of a second seal slot in the second sealing surface.
5. The integrated combustor nozzle of claim 1 , wherein the third sealing surface and the fourth sealing surface of the outer liner segment each define a seal slot having a depth.
6. The integrated combustor nozzle of claim 5 , wherein the depth of a third seal slot in the third sealing surface is equal to the depth of a fourth seal slot in the fourth sealing surface.
7. The integrated combustor nozzle of claim 5 , wherein the depth of the seal slot in at least one of the third sealing surface and the fourth sealing surface varies along an axial length of the outer liner segment.
8. An integrated combustor nozzle comprising:
an inner liner segment, the inner liner segment having a first sealing surface and a second sealing surface circumferentially spaced apart from the first sealing surface;
an outer liner segment disposed opposite the inner liner segment, the outer liner segment having a third sealing surface and a fourth sealing surface circumferentially spaced apart from the third sealing surface;
a panel extending radially between the inner liner segment and the outer liner segment, the panel having a forward end, an aft end, a first side wall extending axially from the forward end to the aft end, and a second side wall opposite the first side wall and extending axially from the forward end to the aft end, the aft end defining a turbine nozzle having a trailing edge circumferentially offset from the forward end:
wherein the inner liner segment extends axially between a first upstream end and a first downstream end extending axially beyond the trailing edge, each of the first sealing surface and the second sealing surface having an inner sealing surface forward end at the first upstream end circumferentially offset from an inner sealing surface aft end at the first downstream end, and wherein each respective sealing surface of the inner liner segment curves continuously from the inner sealing surface forward end to the inner sealing surface aft end;
wherein the outer liner segment extends axially between a second upstream end and a second downstream end extending axially beyond the trailing edge, each of the third sealing surface and the fourth sealing surface having an outer sealing surface forward end at the second upstream end circumferentially offset from an outer sealing surface aft end at the second downstream, wherein each respective sealing surface of the outer liner segment curves continuously from the outer sealing surface forward end to the outer sealing surface aft end; and
wherein the first sealing surface and the second sealing surface of the inner liner segment each define a seal slot having a depth, and wherein the depth of the seal slot of at least one of the first sealing surface and the second sealing surface varies along an axial length of the inner liner segment.
9. A segmented annular combustor comprising:
a circumferential array of integrated combustor nozzles, each integrated combustor nozzle being identical;
wherein each of the integrated combustor nozzles comprises:
an inner liner segment, the inner liner segment having a first sealing surface and a second sealing surface circumferentially spaced apart from the first sealing surface;
an outer liner segment disposed opposite the inner liner segment, the outer liner segment having a third sealing surface and a fourth sealing surface circumferentially spaced apart from the third sealing surface;
a panel extending radially between the inner liner segment and the outer liner segment, the panel having a forward end, an aft end, a first side wall extending axially from the forward end to the aft end, and a second side wall opposite the first side wall and extending axially from the forward end to the aft end, the aft end defining a turbine nozzle having a trailing edge circumferentially offset from the forward end;
wherein the inner liner segment extends axially between a first upstream end and a first downstream end extending axially beyond the trailing edge, each of the first sealing surface and the second sealing surface having an inner sealing surface forward end at the first upstream end circumferentially offset from an inner sealing surface aft end at the first downstream end, and wherein each respective sealing surface of the inner liner segment curves continuously from the inner sealing surface forward end to the inner sealing surface aft end; and
wherein the outer liner segment extends axially between a second upstream end and a second downstream end extending axially beyond the trailing edge, each of the third sealing surface and the fourth sealing surface having an outer sealing surface forward end at the second upstream end circumferentially offset from an outer sealing surface aft end at the second downstream, and wherein each respective sealing surface of the outer liner segment curves continuously from the outer sealing surface forward end to the outer sealing surface aft end.
10. The segmented annular combustor of claim 9 , wherein the first sealing surface and the second sealing surface each continuously curve in a direction tangent to the circumferential direction as the first sealing surface and the second sealing surface each extend axially from the first upstream end to the first downstream end, and wherein the third sealing surface and the fourth sealing surface each continuously curve in a direction tangent to the circumferential direction as the third sealing surface and the fourth sealing surface each extend axially from the second upstream end to the second downstream end.
11. The segmented annular combustor of claim 9 , wherein the curve of the first sealing surface, the second sealing surface, the third sealing surface, and the fourth sealing surface is monotonic in the circumferential direction.
12. The segmented annular combustor of claim 9 , wherein the curve of the first sealing surface and the second sealing surface or the curve of the third sealing surface and the fourth sealing surface comprises an inflection point in the radial direction.
13. The segmented annular combustor of claim 9 , wherein the first sealing surface and the second sealing surface of the inner liner segment each define a seal slot having a depth.
14. The segmented annular combustor of claim 13 , wherein the depth of a first seal slot in the first sealing surface is equal to the depth of a second seal slot in the second sealing surface.
15. The segmented annular combustor of claim 13 , wherein the depth of the seal slot of at least one of the first sealing surface and the second sealing surface varies along an axial length of the inner liner segment.
16. The segmented annular combustor of claim 9 , wherein the third sealing surface and the fourth sealing surface of the outer liner segment each define a seal slot having a depth.
17. The segmented annular combustor of claim 16 , wherein the depth of a third seal slot in the third sealing surface is equal to the depth of a fourth seal slot in the fourth sealing surface.
18. The segmented annular combustor of claim 16 , wherein the depth of the seal slot in at least one of the third sealing surface and the fourth sealing surface varies along an axial length of the outer liner segment.