A rotor assembly for use in a gas turbine engine having an axis of rotation includes a plurality of rotor blades. Each rotor blade includes a platform extending between opposing side faces, a shank extending radially inward from the platform, and a slot at least partially defined in each of the opposing side faces. A sealing member is configured to be inserted into each slot of a first rotor blade of the plurality of rotor blades such that at least a portion of each sealing member extends beyond one of the opposing side faces. A second rotor blade of the plurality of rotor blades is coupled adjacent the first rotor blade such that at least a portion of one sealing member is inserted into a corresponding second slot on the second rotor blade.

A gas turbine engine component has an axial seal pin assembly for sealing between adjacent platform regions where the seal pin assembly design provides a seal pin damper slot extending to a forward axial stop in a forward buttress region. The forward axial stop includes a relief slot to interrupt the loadpath from the airfoil into the blade neck and attachment regions to reduce the stress concentrations in these regions.

A gas turbine engine component has an axial seal pin assembly for sealing between adjacent platform regions where the seal pin assembly design provides a seal pin damper slot extending to a forward axial stop in a forward buttress region. The forward axial stop includes a relief slot to interrupt the loadpath from the airfoil into the blade neck and attachment regions to reduce the stress concentrations in these regions.

A seal assembly for a rotary machine is positioned between a rotating component and a stationary component of the rotary machine. The seal assembly includes a seal bearing face that opposes the rotating component and a slide device. The slide device is positioned between different fluid pressure volumes in the rotary machine. The slide device axially moves toward the rotating component responsive to pressurization of the rotary machine. The slide device includes cross-over ports and the seal bearing face includes feed ports. The feed ports extend through the seal bearing face to form an aerostatic portion of a film bearing between the seal bearing face and the rotating component. The seal bearing face and/or the rotating component is a non-planar surface that, during rotating motion of the rotating component, forms an aerodynamic portion of the film bearing between the seal bearing face and the rotating component.

A tip shroud, comprising a plurality of tip shoes encircling a rotor assembly, in a turbine may deform due to thermal gradients experienced during operation of the turbine. This can make it difficult to remove the tip shroud during disassembly of the turbine. In an embodiment, to facilitate consistent and reliable removal of the tip shroud during each disassembly of the turbine, one or more, including potentially all, of the tip shoes of a tip shroud may be provided with one or more radially protruding puller hooks. Each puller hook enables an axial force to be transferred by one or more tools to an axially inner surface of the puller hook, to thereby produce axial movement of the tip shoe out of the tip shroud.

The present disclosure is directed to a rotor blade for a gas turbine engine. The rotor blade includes an airfoil, a tip shroud having a side surface and a radially outer surface, and a transition portion coupling the tip shroud to the airfoil. The airfoil, the transition portion, and the tip shroud collectively define a primary cooling passage therein. The primary cooling passage includes a primary cooling passage outlet defined by the side surface of the tip shroud.

A method for producing a rotor vane (10) for a turbomachine, including producing a rough casting, the heel of which has a downstream lip (121) with a transverse increased thickness (130) such that the lip has an upstream surface (134) substantially parallel to an axis The method further includes machining said increased thickness so that the downstream lip has an upstream surface (138) inclined in relation to the axis.

A tip shroud includes a pair of opposed, axially extending wings configured to couple to an airfoil at a radially outer end thereof. The tip shroud also includes a tip rail extending radially from the pair of opposed, axially extending wings. Tip shroud surface profiles may be of the downstream and/or upstream side of the tip rail, a leading Z-notch of the tip shroud, and/or a downstream radially inner surface of a wing. The surface profiles may have a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X and Y, and perhaps Z and a thickness, set forth in a respective table. The radially inner surface of the wing may define a protrusion extending along the radially outer end of the airfoil, the suction side fillet, and a radial inner surface of the wing to an axial edge of the wing.

A turbocharger turbine wheel can include a hub that includes a rotational axis, a backdisk and a nose, where the rotational axis defines an axial coordinate (z) in a cylindrical coordinate system that includes a radial coordinate (r) and an azimuthal coordinate (0) in a direction of intended rotation about the rotational axis; and blades that extend outwardly from the hub, where each of the blades includes a hub profile, a shroud edge, a leading edge, a trailing edge, a pressure side, and a suction side, where the hub profile includes a global maximum radius and a global minimum radius, and where, between the global maximum radius and the global minimum radius, in an axial direction from the backdisk to the nose, the hub profile includes a local minimum radius at a first axial coordinate position and a local maximum radius at a second axial coordinate position.

A platform seal and damper assembly for turbomachinery (100), such as fluidized catalytic cracking (FCC) expanders or gas turbine engines; and methodologies for forming such assembly are provided. An axially-extending groove (160) is arranged on a side (162) of a respective platform. Groove (160) is defined by a radially-outward surface (168) at an underside of the platform and a surface (170) extending with a tangential component (T) toward radially-outward surface (168). A seal and damper member (152) is disposed in groove (160), where the body of seal and damper member has adjoining surfaces (190, 188) configured to respectively engage, in response to a camming action, with the surfaces (168, 170) that define the axially-extending groove. The camming action being effective to produce an interference fit of the seal and damper member (152) with the side of the respective platform (162) and an opposed side (163) of an adjacent platform.