A rotary machine includes a rotary shaft that rotates around an axis, a plurality of rotor blades arranged on an outer peripheral side of the rotary shaft in a circumferential direction in which the rotor blade has a blade root, a platform, and a blade main body; and each damper member provided radially inward of the platform, in which the platform includes a first end surface that faces one side in the circumferential direction, and a second end surface that faces the other side in the circumferential direction so that the second end surface faces the first end surface of the adjacent other platform, and the damper member includes a first damper provided on the first end surface and having a first abutting surface, a second damper that has a second abutting surface slidably abutting the first abutting surface of the first damper and is abuttable on the second end surface, and an elastic member that bonds together the first damper and the second damper.

A method for producing a vibration-damping structure combination for damping vibrations for movable masses, having a first structure and a further structure, the further structure movable within a stop surface defined by a first structure surface of the first structure. The method includes a) providing the first structure, having the first structure surface and which defines a coating surface of a coating at least in some sections; b) coating the first structure surface of the first structure with the coating, the coating surface of the coating being applied such that a cavity is formed; c) filling the cavity with the filler; d) curing the filler until the further structure having a further structure surface is formed, which lies against the coating surface; and e) removing the coating, the further structure thus being movable relative to the first structure within the stop surface defined by the first structure surface.

A method for producing a vibration-damping structure combination for damping vibrations for movable masses, having a first structure and a further structure, the further structure movable within a stop surface defined by a first structure surface of the first structure. The method includes a) providing the first structure, having the first structure surface and which defines a coating surface of a coating at least in some sections; b) coating the first structure surface of the first structure with the coating, the coating surface of the coating being applied such that a cavity is formed; c) filling the cavity with the filler; d) curing the filler until the further structure having a further structure surface is formed, which lies against the coating surface; and e) removing the coating, the further structure thus being movable relative to the first structure within the stop surface defined by the first structure surface.

An airfoil includes a base, a tip, a suction side face, and a pressure side face. The pressure side face includes an outer surface, an inner surface located between the outer surface and the suction side face, and a transition surface that extends between and interconnects the outer surface and the inner surface so as to form a pocket in the airfoil.

An airfoil includes a base, a tip, a suction side face, and a pressure side face. The pressure side face includes an outer surface, an inner surface located between the outer surface and the suction side face, and a transition surface that extends between and interconnects the outer surface and the inner surface so as to form a pocket in the airfoil.

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 turbine includes a shaft configured to rotate about a rotor axis; a pair of rotating blade rows, the pair of rotating blade rows including a pair of disks that extend radially outward from the shaft and are disposed at an interval in a direction of the rotor axis, each one of the pair of rotating blade rows including a plurality of rotating blades arranged in a circumferential direction on an outer peripheral end of the disk; and a pair of stator vane rows disposed in a one-to-one manner on a first side of the pair of rotating blade rows in the direction of the rotor axis, each one of the pair of stator vane rows including a plurality of stator vanes arranged in the circumferential direction, wherein a number of the rotating blades on each one of the pair of rotating blade rows is the same, and a number of the stator vanes on each one of the pair of stator vane rows is the same.

A turbine includes a shaft configured to rotate about a rotor axis; a pair of rotating blade rows, the pair of rotating blade rows including a pair of disks that extend radially outward from the shaft and are disposed at an interval in a direction of the rotor axis, each one of the pair of rotating blade rows including a plurality of rotating blades arranged in a circumferential direction on an outer peripheral end of the disk; and a pair of stator vane rows disposed in a one-to-one manner on a first side of the pair of rotating blade rows in the direction of the rotor axis, each one of the pair of stator vane rows including a plurality of stator vanes arranged in the circumferential direction, wherein a number of the rotating blades on each one of the pair of rotating blade rows is the same, and a number of the stator vanes on each one of the pair of stator vane rows is the same.

A bearing assembly for a gas turbine engine comprises a bearing; a bearing bracket, which holds the bearing and is secured by a predetermined breaking device on a connecting element, which can be connected or is connected to a support structure of the gas turbine engine; and a clutch for transmitting a torque from a first clutch element connected in a fixed manner to the rotor of the bearing to a second clutch element supported on the bearing bracket, wherein the clutch elements are spaced apart when the predetermined breaking device is intact and can be brought into contact with one another by destruction of the predetermined breaking device. A gas turbine engine and a method are furthermore provided.

A bearing assembly for a gas turbine engine comprises a bearing; a bearing bracket, which holds the bearing and is secured by a predetermined breaking device on a connecting element, which can be connected or is connected to a support structure of the gas turbine engine; and a clutch for transmitting a torque from a first clutch element connected in a fixed manner to the rotor of the bearing to a second clutch element supported on the bearing bracket, wherein the clutch elements are spaced apart when the predetermined breaking device is intact and can be brought into contact with one another by destruction of the predetermined breaking device. A gas turbine engine and a method are furthermore provided.