Shroud for a gas turbine engine

A shroud segment for a gas turbine engine, the gas turbine engine including a rotor blade stage and a nozzle stage, the nozzle stage including a plurality of circumferentially spaced nozzles, with each nozzle including an outer nozzle end and an airfoil extending from the outer nozzle end, the shroud segment comprising:

• a forward end, the forward end defining an outer wall of the rotor blade stage;
• an aft end, the aft end defining an outer wall of the nozzle stage, the aft end defining at least a portion of an opening therethrough for receipt of a nozzle;
• and
• a pocket defined in the aft end adjacent the opening, the pocket axially extending into a portion of the aft end and confronting at least a portion of the airfoil,
• wherein the forward end and the aft end forms a single, continuous component;
• and
• wherein the plurality of circumferentially spaced nozzles each extend through the opening such that the outer nozzle end of each nozzle extends radially outward beyond an outer surface of the shroud segment.

A method of assembling a gas turbine engine, the gas turbine engine including a rotor blade stage and a nozzle stage, the method comprising:

• positioning a shroud to form an outer wall of both the rotor blade stage and the nozzle stage;
• inserting a nozzle through an opening defined in the shroud, the nozzle including an airfoil having opposite pressure and suction sides extending radially from an inner nozzle end to an outer nozzle end and extending axially from a leading edge to a trailing edge;
• and
• positioning a retainer radially outward from the outer nozzle end of the nozzle such that an entirety of the retainer is provided radially outward from a portion of the outer nozzle end the retainer overlays the retainer extending circumferentially across the outer nozzle end.