Abstract: A bearing assembly for a rotary machine is disclosed herein. The bearing assembly includes a bearing housing, a squeeze film cylinder, a damper spring, and a journal bearing. The squeeze film cylinder is located within the bearing housing. The damper spring includes a first portion, a second portion, and a spring portion. The first portion is located proximal the first end. The second portion is located proximal the second end. The spring portion extends axially between the first portion and the second portion and is located within the bearing housing.

Abstract: A centrifugal gas compressor radial magnetic bearing (125) may include windings (126), a lamination sleeve (130), and a lamination (127). The lamination (127) aligned with the windings (126) may provide for efficient operation of the radial magnetic bearing (125). The centrifugal gas compressor shaft (120) may include a tapered region (118) with an adjacent shelf (124) for alignment with the forward surface (131) and taper of the lamination sleeve (130). The lamination sleeve (130) may include one or more axial hydraulic fitting ports (136) for coupling the lamination sleeve (130) and shaft (120) with an interference fit.

Abstract: Radial magnetic bearings (125) of a centrifugal gas compressor (100) may lose power and fail to support the shaft (120) resulting in damage to the shaft (120). Auxiliary bearings (135) may be used to support the shaft (120) during such a failure. A landing guard (140) may be installed as a sacrificial piece between the shaft (120) and the auxiliary bearings (135). Landing guard (140) includes slots (144) that may be used with pins (121) in the shaft (120) to prevent an angular displacement between the landing guard (140) and the shaft (120).

Abstract: A bearing assembly for a rotary machine is disclosed herein. The bearing assembly includes a bearing housing, a squeeze film cylinder, a damper spring, and a journal bearing. The squeeze film cylinder is located within the bearing housing. The damper spring includes a first portion, a second portion, and a spring portion. The first portion is located proximal the first end. The second portion is located proximal the second end. The spring portion extends axially between the first portion and the second portion and is located within the bearing housing.

Abstract: A thrust collar (161) includes a central disk (162), a forward wing (163), and an aft wing (164). The central disk (162) is a disk shaped hollow cylinder with a central axis (97). The forward wing (163) and the aft wing (164) are thin walled hollow cylinders extending axially from an inner portion of the central disk (162) about the central axis (97) in opposite directions. The forward wing (163) includes a forward mounting pilot (165) extending radially inward from the forward wing (163) distal to the central disk (162). The aft wing (164) includes an aft mounting pilot (167) extending radially inward from the aft wing (164) distal to the central disk (162).

Abstract: A thrust collar (161) includes a central disk (162), a forward wing (163), and an aft wing (164). The central disk (162) is a disk shaped hollow cylinder with a central axis (97). The forward wing (163) and the aft wing (164) are thin walled hollow cylinders extending axially from an inner portion of the central disk (162) about the central axis (97) in opposite directions. The forward wing (163) includes a forward mounting pilot (165) extending radially inward from the forward wing (163) distal to the central disk (162). The aft wing (164) includes an aft mounting pilot (167) extending radially inward from the aft wing (164) distal to the central disk (162).

Abstract: A shaft (120) configured to be mounted within a centrifugal gas compressor (100) includes a suction end (116), a discharge end (117), and a shaft surface. The shaft surface includes a hardened surface (123) located between the suction end (116) and the discharge end (117). The hardened surface (123) is a localized portion of the shaft surface having a different surface treatment than a remainder of the shaft surface. The hardened surface (123) is harder than the remainder of the shaft surface. The hardened surface (123) is configured to axially align with a central auxiliary bearing (137).

Abstract: Radial magnetic bearings (125) of a centrifugal gas compressor (100) may lose power and fail to support the shaft (120) resulting in damage to the shaft (120). Auxiliary bearings (135) may be used to support the shaft (120) during such a failure. A landing guard (140) may be installed as a sacrificial piece between the shaft (120) and the auxiliary bearings (135). Landing guard (140) includes slots (144) that may be used with pins (121) in the shaft (120) to prevent an angular displacement between the landing guard (140) and the shaft (120).

Abstract: A centrifugal gas compressor radial magnetic bearing (125) may include windings (126), a lamination sleeve (130), and a lamination (127). The lamination (127) aligned with the windings (126) may provide for efficient operation of the radial magnetic bearing (125). The centrifugal gas compressor shaft (120) may include a tapered region (118) with an adjacent shelf (124) for alignment with the forward surface (131) and taper of the lamination sleeve (130). The lamination sleeve (130) may include one or more axial hydraulic fitting ports (136) for coupling the lamination sleeve (130) and shaft (120) with an interference fit.