Abstract: A turbine nozzle assembly includes at least one airfoil and an outer endwall coupled to a radial outer end of the airfoil(s). A mounting rail is coupled to the outer endwall and extends at least partially radially outward from the outer endwall and at least partially circumferentially along the outer endwall. A stress relief structure is defined in the mounting rail and includes an end opening defined in a radial outer surface of the mounting rail, a slot defined through the rail thickness of the mounting rail and coupled to the end opening, and an oblong opening defined through the rail thickness of the mounting rail and coupled to a radial inner end of the slot. The oblong opening is symmetrical in a circumferential direction relative to the slot, and the slot is deeper into the mounting rail than previously provided to relieve stress where prevalent in the mounting rail.

Abstract: The present disclosure provides a turbine shroud with a cooling circuit and turbomachine with the subject turbine shroud. The turbine shroud includes a body with a rib thereon. The rib extends between a first and second sidewall of the body, the sidewalls extending between a forward end and an aft end of the body. The body is coupled to a turbomachine casing or an intermediate component for coupling the body to the turbomachine casing. A cooling circuit within the body is in fluid communication with a cooling chamber adjacent the body. The cooling circuit includes a plurality of inlet passages extending through the rib of the body, and a plurality of outlet passages fluidly coupled to the inlet passage and extending through an external surface of the body. The cooling circuit also includes a first plenum within the rib and in fluid communication with the plurality of inlet passages.

Abstract: The present disclosure provides a turbine shroud with a cooling circuit and turbomachine with the subject turbine shroud. The turbine shroud includes a body with a rib thereon. The rib extends between a first and second sidewall of the body, the sidewalls extending between a forward end and an aft end of the body. The body is coupled to a turbomachine casing or an intermediate component for coupling the body to the turbomachine casing. A cooling circuit within the body is in fluid communication with a cooling chamber adjacent the body. The cooling circuit includes a plurality of inlet passages extending through the rib of the body, and a plurality of outlet passages fluidly coupled to the inlet passage and extending through an external surface of the body. The cooling circuit also includes a first plenum within the rib and in fluid communication with the plurality of inlet passages.

Abstract: The present disclosure provides a turbine shroud with a cooling circuit and turbomachine with the subject turbine shroud. The turbine shroud includes a body with a structural member thereon. The body is coupled to a turbomachine casing or an intermediate component for coupling the body to the turbomachine casing. A cooling circuit within the body is in fluid communication with a cooling chamber adjacent the body. The cooling circuit includes an inlet passage extending through the structural member of the body, and an outlet passage fluidly coupled to the inlet passage and extending through an external surface of the body.