Abstract: Damper stacks, rotor blades, and turbomachines are provided. A rotor blade includes a main body including a shank and an airfoil extending radially outwardly from the shank. The rotor blade further includes a platform surrounding the main body, the platform comprising a slash face. The rotor blade further includes a damper stack disposed at the slash face and extending generally along an axial direction. The damper stack includes a plurality of damper pins, each of the plurality of damper pins being in contact with a neighboring damper pin.

Abstract: Damper stacks, rotor blades, and turbomachines are provided. A rotor blade includes a main body including a shank and an airfoil extending radially outwardly from the shank. The rotor blade further includes a damping passage defined in the main body, the damping passage extending radially through the main body. The rotor blade further includes a damper stack disposed within the damping passage, the damper stack including a plurality of damper pins, each of the plurality of damper pins in contact with a neighboring damper pin.

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil and a tip shroud coupled to the airfoil. The tip shroud includes a side surface. The airfoil and the tip shroud define a first cooling passage. The tip shroud further defines a second passage in fluid communication with the first cooling passage. The second cooling passage extends from the first cooling passage to a first outlet defined by the side surface. The first outlet is configured to direct a flow of coolant onto a tip shroud fillet of a first adjacent rotor blade.

Abstract: Damper stacks, rotor blades, and turbomachines are provided. A rotor blade includes a main body including a shank and an airfoil extending radially outwardly from the shank. The rotor blade further includes a platform surrounding the main body, the platform comprising a slash face. The rotor blade further includes a damper stack disposed at the slash face and extending generally along an axial direction. The damper stack includes a plurality of damper pins, each of the plurality of damper pins being in contact with a neighboring damper pin.

Abstract: Damper stacks, rotor blades, and turbomachines are provided. A rotor blade includes a main body including a shank and an airfoil extending radially outwardly from the shank. The rotor blade further includes a damping passage defined in the main body, the damping passage extending radially through the main body. The rotor blade further includes a damper stack disposed within the damping passage, the damper stack including a plurality of damper pins, each of the plurality of damper pins in contact with a neighboring damper pin.

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil having a leading edge and a trailing edge and defines a chord extending from the leading edge to the trailing edge. A tip shroud couples to the airfoil and includes a leading edge wall and a trailing edge wall and defines a tip shroud cavity. The tip shroud cavity includes a leading edge portion at least partially defined by the leading edge wall and positioned largely upstream of fifty percent of the chord. The tip shroud cavity also includes a trailing edge portion at least partially defined by the trailing edge wall and positioned largely downstream of fifty percent of the chord. An intermediate portion of the tip shroud cavity fluidly couples the leading edge portion of the tip shroud cavity and the trailing edge portion of the tip shroud cavity.

Abstract: The present disclosure is directed to a rotor blade that includes an airfoil defining a cooling passage and a tip shroud coupled to the airfoil. The tip shroud and the airfoil define a cooling core in fluid communication with the cooling passage. The cooling core includes a first cooling channel and a second cooling channel. The first cooling channel is radially spaced apart from the second cooling channel. Coolant flows in a first direction through the first cooling channel and in a second direction through the second cooling channel. The first direction is different than the second direction.

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil having a trailing edge surface and defining a cooling passage. The rotor blade also includes a tip shroud coupled to the airfoil. The tip shroud includes a radially inner surface. The tip shroud defines a cooling core fluidly coupled to the cooling passage. The cooling core includes at least one of a first outlet aperture having a first opening defined by the radially inner surface or a second outlet aperture having a second opening defined by the trailing edge surface of the airfoil. The first or second outlet apertures eject coolant from the cooling core in a direction of a local flow of combustion gases external to the tip shroud.

Abstract: A rotor blade for a turbomachine includes an airfoil having a leading edge, a trailing edge, a root, and a tip. The airfoil defines a chord extending from the leading edge to the trailing edge and a span extending from the root to the tip. A first particle-filled damper is positioned within the airfoil between fifty percent of the chord and one hundred percent of the chord.

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining a cooling passage and a tip shroud coupled to the airfoil. The tip shroud includes first and second walls that at least partially define a cooling core fluidly coupled to the cooling passage. The rotor blade also includes a plurality of ribs positioned within the cooling core and coupled to the first and second walls. The reinforcing structure includes a plurality of interconnected ribs having a first rib with a first orientation and a second rib with a second orientation. The first and second orientations are different in three spatial dimensions.

Abstract: The present disclosure is directed to a rotor blade that includes an airfoil defining a cooling passage and a tip shroud coupled to the airfoil. The tip shroud and the airfoil define a cooling core in fluid communication with the cooling passage. The cooling core includes a first cooling channel and a second cooling channel. The first cooling channel is radially spaced apart from the second cooling channel. Coolant flows in a first direction through the first cooling channel and in a second direction through the second cooling channel. The first direction is different than the second direction.

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining a cooling passage and a tip shroud coupled to the airfoil. The tip shroud and the airfoil define a cooling core in fluid communication with the cooling passage. The tip shroud including a forward exterior wall, an aft exterior wall spaced apart from the forward exterior wall along an axial direction, a radially inner exterior wall, a radially outer exterior wall spaced apart from the radially inner wall along a radial direction, a pressure side wall, and a suction side wall spaced apart from the pressure side wall along a circumferential direction. The tip shroud further includes first and second interior walls positioned within the cooling core. The first interior wall is non-coplanar with the second interior wall in the axial, radial, and circumferential directions.

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining a cooling passage and a tip shroud coupled to the airfoil. The tip shroud includes first and second walls that at least partially define a cooling core fluidly coupled to the cooling passage. The rotor blade also includes a plurality of ribs positioned within the cooling core and coupled to the first and second walls. The reinforcing structure includes a plurality of interconnected ribs having a first rib with a first orientation and a second rib with a second orientation. The first and second orientations are different in three spatial dimensions.

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil having a trailing edge surface and defining a cooling passage. The rotor blade also includes a tip shroud coupled to the airfoil. The tip shroud includes a radially inner surface. The tip shroud defines a cooling core fluidly coupled to the cooling passage. The cooling core includes at least one of a first outlet aperture having a first opening defined by the radially inner surface or a second outlet aperture having a second opening defined by the trailing edge surface of the airfoil. The first or second outlet apertures eject coolant from the cooling core in a direction of a local flow of combustion gases external to the tip shroud.

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil and a tip shroud coupled to the airfoil. The tip shroud includes a side surface. The airfoil and the tip shroud define a first cooling passage. The tip shroud further defines a second passage in fluid communication with the first cooling passage. The second cooling passage extends from the first cooling passage to a first outlet defined by the side surface. The first outlet is configured to direct a flow of coolant onto a tip shroud fillet of a first adjacent rotor blade.

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil having a leading edge and a trailing edge and defines a chord extending from the leading edge to the trailing edge. A tip shroud couples to the airfoil and includes a leading edge wall and a trailing edge wall and defines a tip shroud cavity. The tip shroud cavity includes a leading edge portion at least partially defined by the leading edge wall and positioned largely upstream of fifty percent of the chord. The tip shroud cavity also includes a trailing edge portion at least partially defined by the trailing edge wall and positioned largely downstream of fifty percent of the chord. An intermediate portion of the tip shroud cavity fluidly couples the leading edge portion of the tip shroud cavity and the trailing edge portion of the tip shroud cavity.

Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil having a leading edge, a trailing edge, a root, and a tip. The airfoil defines a chord extending from the leading edge to the trailing edge and a span extending from the root to the tip. A first particle-filled damper is positioned within the airfoil between fifty percent of the chord and one hundred percent of the chord.

Abstract: A turbine blade is provided and includes pressure and suction surfaces connected to define an interior through which coolant is passable and first and second pedestal arrays, each of the first and second pedestal arrays including pedestals respectively coupled to radially outboard portions of respective interior faces of one of the pressure and suction surfaces. The pedestals of the first pedestal array are separated from pedestals of the second pedestal array by gaps respectively defined therebetween.

Abstract: A turbine blade is provided and includes pressure and suction surfaces connected to define an interior through which coolant is passable and first and second pedestal arrays, each of the first and second pedestal arrays including pedestals respectively coupled to radially outboard portions of respective interior faces of one of the pressure and suction surfaces. The pedestals of the first pedestal array are separated from pedestals of the second pedestal array by gaps respectively defined therebetween.

Abstract: A turbomachine includes a housing, and at least one turbine vane arranged within the housing. The at least one turbine vane includes a platform portion operatively connected to the airfoil portion. A cooling cavity is formed in the platform portion. The cooling cavity includes a first wall, a second wall arranged opposite the first wall, a third wall linking the first and second walls, and a fourth wall linking the first and second walls and positioned opposite the third wall. An impingement cooling plate extends into the cooling cavity and defines an inner cavity portion and an outer cavity portion. The impingement cooling plate including at least one impingement cooling passage that is configured and disposed to guide an impingement cooling flow onto at least one of the first, second, third and fourth walls of the cooling cavity.