A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod.

A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod.

An outer diameter shroud for retaining a stator of a gas turbine engine having an axis includes an annular body positioned around the axis, extending in an axial direction, and defining a plurality of slots each configured to receive a portion of one of a plurality of stators. The outer diameter shroud further includes a shroud flange coupled to the annular body, extending in a direction perpendicular to the annular body, and configured to be fastened to a case of the gas turbine engine.

An outer diameter shroud for retaining a stator of a gas turbine engine having an axis includes an annular body positioned around the axis, extending in an axial direction, and defining a plurality of slots each configured to receive a portion of one of a plurality of stators. The outer diameter shroud further includes a shroud flange coupled to the annular body, extending in a direction perpendicular to the annular body, and configured to be fastened to a case of the gas turbine engine.

A bladed rotor system (10) for a turbomachine includes a row of blades (14) mounted on a rotor disc (12). Each blade (14) includes an airfoil (16) with a mid-span snubber (30). The row of blades (14) includes first (H) and second (L) sets of blades (14). The blades (14) of the second set (L) are distinguished from the blades (14) of the first set (H) by a geometry of the snubber (30) that is unique to the respective set (H, L). In particular, the snubbers (30) of the second set (L) are attached to the respective airfoils (16) at a different span-wise height than that of the snubbers (30) of the first set (H). Thereby the natural frequency of a blade (14) in the second set (L) differs from the natural frequency of a blade (14) in the first set (H) by a predetermined amount. Blades (14) of the first set (H) and the second set (L) are positioned alternately in the row of blades (14), to provide a frequency mistuning to stabilize flutter of the blades (14).

A bladed rotor system (10) for a turbomachine includes a row of blades (14) mounted on a rotor disc (12). Each blade (14) includes an airfoil (16) with a mid-span snubber (30). The row of blades (14) includes first (H) and second (L) sets of blades (14). The blades (14) of the second set (L) are distinguished from the blades (14) of the first set (H) by a geometry of the snubber (30) that is unique to the respective set (H, L). In particular, the snubbers (30) of the second set (L) are attached to the respective airfoils (16) at a different span-wise height than that of the snubbers (30) of the first set (H). Thereby the natural frequency of a blade (14) in the second set (L) differs from the natural frequency of a blade (14) in the first set (H) by a predetermined amount. Blades (14) of the first set (H) and the second set (L) are positioned alternately in the row of blades (14), to provide a frequency mistuning to stabilize flutter of the blades (14).

A turbine blade includes an airfoil that extends radially between a root end and a tip end, a platform coupled to the root end, and a shank that extends radially inwardly from the platform. The shank includes a cover plate. The cover plate includes an outer surface, an opposite inner surface, and a contoured face that at least partially defines a damper pin slot. The contoured face extends from the outer surface to a first blend edge. The cover plate also includes a blended surface that extends from the first blend edge to a second blend edge. The second blend edge intersects with the inner surface.

A turbine blade includes an airfoil that extends radially between a root end and a tip end, a platform coupled to the root end, and a shank that extends radially inwardly from the platform. The shank includes a cover plate. The cover plate includes an outer surface, an opposite inner surface, and a contoured face that at least partially defines a damper pin slot. The contoured face extends from the outer surface to a first blend edge. The cover plate also includes a blended surface that extends from the first blend edge to a second blend edge. The second blend edge intersects with the inner surface.

An airfoil assembly includes at least one airfoil that has a hollow interior. First and second platforms are disposed between the airfoil. At least one tie-spar extends along an axis through the first platform, the hollow interior of the airfoil, and the second platform. There is a thermal expansion difference between a thermal expansion of the tie-spar in the axial direction and the combined thermal expansion of the airfoil and the first and second platform in the axial direction. At least one spacer portion is arranged on the tie-spar. The spacer portion has a thermal expansion in the axial direction that is greater than the thermal expansion difference such that the spacer portion maintains the tie-spar under tension and clamps the first and second platforms on the airfoil.

A seal support structure is provided for a circumferential seal. In one embodiment, the seal support structure includes an engine support structure, a seal support, and a shoulder joining the engine support and seal support. The shoulder offsets the engine support from the seal support, and the shoulder and the seal support structure are configured to dampen vibration for the circumferential seal. The seal support structure may employ one or more dampening elements or materials to interoperate with a seal support structure to dampen vibration to a seal system.