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A gas turbine engine bearing assembly for a portion of a shaft that rotates around an axis, including a substantially cylindrical bearing having a length extending between a first end and a second end along the axis of the rotating shaft. A plurality of segmented damper springs are positioned around

A gas turbine engine bearing assembly for a portion of a shaft that rotates around an axis, including a substantially cylindrical bearing having a length extending between a first end and a second end along the axis of the rotating shaft. A plurality of segmented damper springs are positioned around an exterior perimeter of a portion of the cylindrical bearing. Each spring has a width along the axis of the rotating shaft and a portion of each spring defines an outer spherically contoured joint. The width of each spring is less than the length of the bearing.

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1. A gas turbine engine bearing assembly for a portion of a shaft that rotates around an axis, comprising: a substantially cylindrical bearing having a length extending between a first end and a second end along the axis of the rotating shaft;a plurality of segmented damper springs positioned around

1. A gas turbine engine bearing assembly for a portion of a shaft that rotates around an axis, comprising: a substantially cylindrical bearing having a length extending between a first end and a second end along the axis of the rotating shaft;a plurality of segmented damper springs positioned around an exterior perimeter of a portion of the cylindrical bearing, wherein each spring has a width along the axis of the rotating shaft and a portion of each spring defines an outer spherically contoured joint;wherein the width of each spring is less than the length of the bearing; andwherein the bearing is a foil air bearing, and wherein the outer spherically contoured joint of each spring is between a pair of inner mutes. 2. The bearing assembly of claim 1, further comprising a bearing housing, wherein the spherically contoured joint is preloaded within the bearing housing. 3. A gas turbine engine bearing assembly for a portion of a shaft that rotates around an axis, comprising: a bearing housing:a substantially cylindrical bearing having a length extending between a first end and a second end along the axis of the rotating shaft;a plurality of segmented damper springs positioned around an exterior perimeter of a portion of the cylindrical bearing, wherein each spring has a width along the axis of the rotating shaft and a portion of each spring defines an outer spherically contoured joint that is preloaded within the bearing housing;wherein the width of each spring is less than the length of the bearing; andwherein the cylindrical bearing is a foil bearing, and wherein an interior of the bearing at both the first end and the second end includes a plurality of segmented snubbers. 4. The bearing assembly of claim 3, wherein the outer spherically contoured joint of each spring is between a pair of inner mutes. 5. The bearing assembly of claim 4, wherein the spherically contoured joint has a spherical radius of about 1.95 inches and a radial depth of about 0.009 inches and has a preload of about 0.002 inches, and wherein the cylindrical bearing has a length of about 4 inches and an outer diameter of about 3.5 inches, the bearing housing having an inner diameter of about 3.76 inches. 6. A bearing assembly for a gas turbine engine, comprising a plurality of curved spring bars forming a substantially circular array around a portion of an exterior of a foil air bearing sleeve, a bearing housing, each spring bar having an outer mute that defines an external spherically contoured joint that is preloaded within the bearing housing; and the bearing housing has a corresponding spherical cavity for each of the plurality of spherical joints. 7. A bearing assembly for a gas turbine engine, comprising a plurality of curved spring bars forming a substantially circular array around a portion of an exterior of a foil air bearing sleeve, each spring bar having an outer mute that defines an external spherically contoured joint; and wherein an interior of the bearing sleeve extends between a first end and a second end, and wherein the interior at both the first end and the second end includes a retainer ring substantially adjacent a plurality of segmented snubbers. 8. The bearing assembly of claim 7, wherein the spherically contoured joint extends across an entire width of the spring bar, and wherein each spring bar further includes an inner mute at each end, the outer mute being between the two inner mutes. 9. A gas turbine engine bearing assembly for use with a shaft rotating around an axis, comprising a substantially cylindrical foil bearing, wherein a circumferential exterior portion of the foil bearing is within a substantially circular array of curved spring bars, each spring bar including an external spherically contoured protrusion; and a bearing housing having a plurality of spherically contoured cavities, each spherically contoured cavity associated with a corresponding spherically contoured protrusion. 10. The bearing assembly of claim 9, wherein the foil bearing has a length of about 4 inches and an outer diameter of about 3.5 inches, the bearing housing having an inner diameter of about 3.76 inches, and wherein each spring bar has a width of about 0.9 inches. 11. The bearing assembly of claim 9, wherein the spherically contoured protrusion is a self-aligning mount, and wherein the spherical mount is preloaded within the bearing housing. 12. The bearing assembly of claim 11, wherein the spherically contoured protrusion has a spherical radius of about 1.95 inches and a radial depth of about 0.009 inches, and wherein the spherical mount has a preload of about 0.002 inches. 13. The bearing assembly of claim 11, wherein the foil bearing is a foil air bearing, and wherein an interior of at least one end of the bearing includes a retainer ring substantially adjacent a plurality of segmented snubbers. 14. The bearing assembly of claim 13, wherein seven curved spring bars substantially encircle the circumferential exterior portion of the foil bearing. 15. The bearing assembly of claim 13, wherein the spring bars each have a width along the axis, and wherein the spherically contoured protrusion of each spring bar extends across the width of the spring bar. 16. A gas turbine engine bearing assembly for use with a shaft rotating around an axis, comprising a substantially cylindrical foil bearing, wherein a circumferential exterior portion of the foil bearing is within a substantially circular array of curved spring bars, each spring bar including an external spherically contoured protrusion; and a bearing housing, wherein the spherically contoured protrusion is a self-aligning mount, and wherein the spherical mount is preloaded within the bearing housing, and further wherein the foil bearing is a foil air bearing, and wherein an interior of at least one end of the bearing includes a retainer ring substantially adjacent a plurality of segmented snubbers. 17. The bearing assembly of claim 16, wherein seven curved spring bars substantially encircle the circumferential exterior portion of the foil bearing. 18. The bearing assembly of claim 16, wherein the spring bars each have a width along the axis, and wherein the spherically contoured protrusion of each spring bar extends across the width of the spring bar.