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.

A balancing system and method for an engine of an aircraft includes a housing retaining a magnetorheological fluid including magnetic particles within a carrier fluid. Electromagnets are coupled to the housing. The electromagnets are associated with fan blades of the engine. A balancing control unit is in communication with the electromagnets and sensors of the fan blades.

A balancing system and method for an engine of an aircraft includes a housing retaining a magnetorheological fluid including magnetic particles within a carrier fluid. Electromagnets are coupled to the housing. The electromagnets are associated with fan blades of the engine. A balancing control unit is in communication with the electromagnets and sensors of the fan blades.

A damper seal received in a cavity of a turbine blade includes a central body with two ends and a two sides. A portion extends from each end, one side has a faceted edge, and a projection extends from the other side to receive a lug of the turbine blade to align the damper seal relative to the turbine blade.

A damper seal received in a cavity of a turbine blade includes a central body with two ends and a two sides. A portion extends from each end, one side has a faceted edge, and a projection extends from the other side to receive a lug of the turbine blade to align the damper seal relative to the turbine blade.

A stator assembly for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, at least one stator vane including a platform, a seal member connected to the platform, and a damper between the platform and the seal member. The damper includes a plurality of first fingers and a plurality of second fingers, which are provided in an alternating arrangement.

A stator assembly for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, at least one stator vane including a platform, a seal member connected to the platform, and a damper between the platform and the seal member. The damper includes a plurality of first fingers and a plurality of second fingers, which are provided in an alternating arrangement.

A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (21-25) that are configured on the inner ring segment; at and/or in at least one detuning region (A; B) of the inner ring segment, that extends circumferentially in a portion of the inner ring segment that, from one end face (11; 12) of the inner ring segment to an inner guide vane (22; 24) that is circumferentially adjacent to an outermost guide vane (21; 25) adjacent to the end face and/or extends at most over an outermost third of a length (L) of the inner ring segment bounded by an end face (11; 12) of the inner ring segment, at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.

A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (20) that are configured on the inner ring segment; a detuning region (V) of the inner ring segment extending in each case from a trailing edge (21) of at least one guide vane (20), in particular of at least 50% of the guide vanes (50), axially toward a leading edge (22) of the guide vane (20) over at most 50% of a width (B) of the inner ring segment (10) and/or at most 5 mm and/or circumferentially on both sides, in each case over at most 25% of a spacing (A) between adjacent guide vanes (20), at and/or in which at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.

A guide vane segment for a turbomachine stage that has an inner ring segment (10) and a plurality of guide vanes (20) that are configured on the inner ring segment; a detuning region (V) of the inner ring segment extending in each case from a trailing edge (21) of at least one guide vane (20), in particular of at least 50% of the guide vanes (50), axially toward a leading edge (22) of the guide vane (20) over at most 50% of a width (B) of the inner ring segment (10) and/or at most 5 mm and/or circumferentially on both sides, in each case over at most 25% of a spacing (A) between adjacent guide vanes (20), at and/or in which at least one cavity (112) is configured which contains at least one impulse element (100) with clearance of motion for providing impact contacts.