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A bearing assembly for a gas turbine engine rotor includes a damper bearing configured to support the rotor, a bearing centering sub-assembly configured to position the damper bearing relative to the rotor, and a retainer. The damper bearing includes a frame that defines a bearing bore, an inner rac

A bearing assembly for a gas turbine engine rotor includes a damper bearing configured to support the rotor, a bearing centering sub-assembly configured to position the damper bearing relative to the rotor, and a retainer. The damper bearing includes a frame that defines a bearing bore, an inner race, and an outer race, said inner and outer races within said bearing bore. The bearing centering apparatus sub-assembly includes a plurality of first springs and a plurality of second springs. The retainer is coupled to the bearing housing and is configured to maintain an axial position of the bearing outer race with respect to the support structure.

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A bearing assembly for a gas turbine engine rotor includes a damper bearing configured to support the rotor, a bearing centering sub-assembly configured to position the damper bearing relative to the rotor, and a retainer. The damper bearing includes a frame that defines a bearing bore, an inner rac

A bearing assembly for a gas turbine engine rotor includes a damper bearing configured to support the rotor, a bearing centering sub-assembly configured to position the damper bearing relative to the rotor, and a retainer. The damper bearing includes a frame that defines a bearing bore, an inner race, and an outer race, said inner and outer races within said bearing bore. The bearing centering apparatus sub-assembly includes a plurality of first springs and a plurality of second springs. The retainer is coupled to the bearing housing and is configured to maintain an axial position of the bearing outer race with respect to the support structure. rom that in the area where the blades exist, and said portion of grooves and said other portion of grooves are disposed alternately. 7. A turbo-type machine as defined in claim 6, wherein the cross-section area of said other portion of grooves in said area where the blades exist is set to be smaller than that of said portion of grooves. 8. A turbo-type machine, comprising: a casing for storing an impeller having blades within an inside thereof; and a plural number of grooves formed on an inner surface of said casing, connecting between an inlet side of the blades and an area on said inner surface where the blades exist, in a direction of pressure gradient of fluid, wherein, openings are drilled on said grooves, each penetrating from a bottom surface thereof through thickness of said casing, in a portion near to a front edge of the blade within the area where no blade exist, and further is provided a ring-like chamber on an outer peripheral surface of said casing, wherein said ring-like chamber is conducted to a position in a stream upper than said penetrating openings in said casing. 9. A turbo-type machine, comprising: a casing for storing an impeller having blades within an inside thereof; a suction inlet, being dipped within fluid to be transferred, together with at least said casing; and a plural number of grooves formed on an inner surface of said casing, connecting between an inlet side of the blades and an area on said inner surface where the blades exist, in a direction of pressure gradient of fluid, wherein, openings are drilled on said grooves, each penetrating from a bottom surface thereof through thickness of said casing, in a portion near to a front edge of the blade within the area where no blade exist. 10. A turbo-type machine, comprising: a casing for storing an impeller having blades within an inside thereof; and a plural number of grooves formed on an inner surface of said casing, connecting between an inlet side of the blades and an area on said inner surface where the blades exist, in a direction of pressure gradient of fluid, wherein, an edge portion of a tip of each of said blades, said edge portion being defined by a pressure surface and an outer peripheral surface in a direction of thickness thereof, has a round form having a radius from 1/4 to 1/2 of a thickness of said blade. 11. A turbo-type machine, comprising: a casing for storing an impeller having blades within an inside thereof; and a plural number of grooves formed on an inner surface of said casing, connecting between an inlet side of the blades and an area on said inner surface where the blades exist, in a direction of pressure gradient of fluid, wherein, a fin is formed at each tip of said blades of said impeller in a peripheral direction thereof, extending in a direction on side of a negative pressure surface of said blade, a ratio of a width of said fin to a thickness of the blade being in a range of 1/4:1 to 1:1. 12. A turbo-type machine, comprising: a casing for storing an impeller having blades within an inside thereof; and a plural number of grooves formed on an inner surface of said casing, connecting between an inlet side of the blades and an area on said inner surface where the blades exist, in a direction of pressure gradient of fluid, wherein, a cross-section area of said grooves within the area where the blades exist is set to be smaller than that of said grooves within an area outside where the blades exist, and a depth of said grooves within the area where the blades exist is deeper than that of said grooves in the area outside where the blades exist.