Nozzle segment for use with multiple different turbine engines

An assembly of a turbine engine, the assembly comprising:

• an outer casing including anti-rotation elements;
• and
• a nozzle segment coupled to the outer casing, the nozzle segment comprising:
• an inner band;
• an outer band comprising an inner surface and an outer surface opposite the inner surface;
• a first hook extending radially outwardly from the outer surface and extending circumferentially across the outer surface;
• and
• at least one nozzle vane extending radially between the inner and outer bands;
• wherein the first hook is coupled to the outer casing;
• wherein slots are defined in the first hook, a first of the slots comprising a first circumferential load surface, a second of the slots comprising a second circumferential load surface, and a third of the slots comprising a third circumferential load surface;
• and wherein the slots are positioned such that at least one of the first circumferential load surface, the second circumferential load surface, and the third circumferential load surface engages one of the anti-rotation elements while at least another one of the first circumferential load surface, the second circumferential load surface, and the third circumferential load surface does not engage any of the anti-rotation elements of the outer casing.

A method of assembling a turbine engine, said method comprising:

• coupling a nozzle segment to a support within the turbine engine, the nozzle segment including an inner band, an outer band, and at least one nozzle vane extending radially between the inner and outer bands, the outer band including an outer surface and a hook extending radially outwardly from the outer surface and circumferentially across the outer surface, the hook including slots defined therein, a first of the slots including a first circumferential load surface, and a second of the slots including a second circumferential load surface, wherein coupling the nozzle segment to the support comprises coupling the nozzle segment to the support using the hook, and one of:
• engaging the first circumferential load surface with an anti-rotation element of the support, wherein the second circumferential load surface does not engage the support;
• and
• engaging the second circumferential load surface with an anti-rotation element of the support, wherein the first circumferential load surface does not engage the support.

A method of manufacturing a nozzle segment selectively couplable within a first turbine engine and a second turbine engine, wherein the first turbine engine includes a first support for coupling the nozzle segment within the first turbine engine, the first support having a first anti-rotation element configuration, wherein the second turbine engine includes a second support for coupling the nozzle segment within the second turbine engine, the second support having a second anti-rotation element configuration that is different from the first anti-rotation element configuration, said method comprising:

• providing the nozzle segment including an inner band, an outer band, at least one nozzle extending between the inner and outer bands, and a hook extending outwardly from the outer band, wherein the hook is selectively couplable to each of the first support and the second support;
• defining a first slot in the hook with a size, shape, and position determined according to the first anti-rotation element configuration such that, when the nozzle segment is coupled within the first turbine engine, an anti-rotation element of the first support engages the first slot;
• and
• defining a second slot in the hook with a size, shape, and position determined according to the second anti-rotation element configuration such that, when the nozzle segment is coupled within the second turbine engine, an anti-rotation element of the second support engages the second slot.