Integrated combustor nozzles with continuously curved liner segments

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.

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.