Gas turbine engine and foil bearing system
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0974961
(2010-12-21)
|
등록번호 |
US-9238973
(2016-01-19)
|
발명자
/ 주소 |
|
출원인 / 주소 |
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
0 인용 특허 :
10 |
초록
▼
A gas turbine engine including a compressor, a turbine and a static structure is disclosed herein. The gas turbine engine further includes a foil bearing system operative to transmit rotor loads from at least one of the compressor and the turbine to the static structure. The foil bearing system incl
A gas turbine engine including a compressor, a turbine and a static structure is disclosed herein. The gas turbine engine further includes a foil bearing system operative to transmit rotor loads from at least one of the compressor and the turbine to the static structure. The foil bearing system includes a foil bearing and a self-aligning foil bearing mount to align the foil bearing with an axis of rotation of the compressor and the turbine. A snubber operative to transmit rotor loads to the static structure in parallel with the foil bearing is also disclosed.
대표청구항
▼
1. A gas turbine engine, comprising: a compressor;a turbine;a static structure;a foil bearing system operative to transmit rotor loads from at least one of the compressor and the turbine to the static structure, wherein the foil bearing system includes a foil bearing and a self-aligning foil bearing
1. A gas turbine engine, comprising: a compressor;a turbine;a static structure;a foil bearing system operative to transmit rotor loads from at least one of the compressor and the turbine to the static structure, wherein the foil bearing system includes a foil bearing and a self-aligning foil bearing mount coupled to the foil bearing, wherein the self-aligning foil bearing mount is operative to align the foil bearing with an axis of rotation of the at least one of the compressor and the turbine;a snubber operative to transmit rotor loads from at least one of the compressor and the turbine to the static structure in parallel with the foil bearing,wherein the self-aligning foil bearing mount includes at least two components configured to align the foil bearing by sliding displacement between the at least two components;wherein the foil bearing system is configured to prevent a rotation of the at least two components of the self-aligning foil bearing mount about the axis of rotation of the rotor; andwherein the self-aligning foil bearing mount is a spherical bearing, a first one of the at least two components of the bearing mount includes a convex crown having a spherical shape and being circumferentially disposed about the axis of rotation of the rotor and a second one of the at least two components is a concave receiver surface having a spherical shape, wherein the concave receiver surface receives the convex crown to permit the sliding displacement between the at least two components, wherein the convex crown is configured to rotate about an axis of rotation that is perpendicular to the axis of rotation of the rotor. 2. The gas turbine engine of claim 1, wherein the self-aligning foil bearing mount includes a static component and a movable component, and wherein the self-aligning foil bearing mount is operable to self-align by displacing the movable component relative to the static component. 3. The gas turbine engine of claim 2, wherein the movable component is operable to rotate relative to the static component. 4. The gas turbine engine of claim 3, wherein rotation of the movable component is rotation of the entirety of the movable component. 5. The gas turbine engine of claim 2, wherein the static component includes a first surface; wherein the movable component includes a second surface in sliding contact with the first surface; and wherein displacement of the movable component relative to the static component includes the second surface sliding against the first surface. 6. The gas turbine engine of claim 2, wherein self-alignment is not achieved by flexure of the self-aligning foil bearing mount. 7. The gas turbine engine of claim 1, further comprising a shaft coupled to at least one of the compressor and the turbine, wherein rotor loads are transmitted from the shaft through the foil bearing, and from the foil bearing to the static structure via the self-aligning foil bearing mount. 8. The gas turbine engine of claim 7, wherein the shaft couples the compressor to the turbine. 9. The gas turbine engine of claim 1, further comprising a rotating journal and a housing disposed opposite to the rotating journal, and wherein the snubber is operative to limit the proximity of the housing relative to the journal. 10. A gas turbine engine, comprising: a rotor;a static structure;a foil bearing system operative to transmit rotor loads from the rotor to the static structure, wherein the foil bearing system includes:a foil bearing; anda self-aligning foil bearing mount operative to align the foil bearing with an axis of rotation of the rotor, wherein the self-aligning foil bearing mount has a static component and a movable component; and wherein the self-aligning foil bearing mount is operable to self-align with the axis of rotation of the rotor by sliding displacement of the movable component relative to the static component;wherein the foil bearing system is configured to prevent a rotation of the movable component about the axis of rotation of the rotor; andwherein the self-aligning foil bearing mount is a spherical bearing, the movable component of the bearing mount is a convex crown having a spherical shape and the static component is a concave receiver surface having a spherical shape, wherein the concave receiver surface receives the convex crown to permit the sliding displacement of the movable component relative to the static component wherein the convex crown is configured to rotate about an axis of rotation that is perpendicular to the axis of rotation of the rotor;wherein the movable component is configured such that the rotation of the movable component is the rotation of the entirety of the movable component. 11. The gas turbine engine of claim 10, further comprising a snubber operative to transmit rotor loads from the rotor to the static structure in parallel with the foil bearing. 12. The gas turbine engine of claim 11, further comprising a bearing housing for housing the foil bearing, wherein the snubber is positioned within the bearing housing. 13. The gas turbine engine of claim 12, wherein the snubber is positioned adjacent to the bearing housing. 14. The gas turbine engine of claim 12, wherein the snubber is formed of a composite material. 15. The gas turbine engine of claim 10, wherein the foil bearing is a compliant foil radial air bearing. 16. A foil bearing system for a gas turbine engine, comprising: a foil bearing operative to transmit rotor loads from a rotor of the gas turbine engine to a static structure of the gas turbine engine; andmeans for capturing and aligning the foil bearing with an axis of rotation of the rotor wherein the means for capturing includes a mount with a convex crown circumferentially disposed about the axis of rotation;wherein the convex crown is configured to rotate about an axis of rotation that is perpendicular to the axis of rotation of the rotor. 17. The foil bearing system of claim 16, further comprising means for sharing the rotor loads with the foil bearing. 18. The foil bearing system of claim 16, wherein the means for aligning includes a spherical bearing. 19. The gas turbine engine of claim 1, wherein the foil bearing is positioned directly adjacent the foil bearing mount; and the snubber is positioned behind a top foil such that rotor loads are fist transmitted through the top foil and then to the snubber. 20. The gas turbine engine of claim 10, wherein the foil bearing is positioned directly adjacent the foil bearing mount; and a snubber is positioned behind a top foil such that rotor loads are first transmitted through the top foil and then to the snubber.
이 특허에 인용된 특허 (10)
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Merritt Brent J. ; Wytas ; Jr. Clarence J., Bearing arrangement for air cycle machine.
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Shapiro Wilbur (Schenectady NY), Face seal with hydrodynamic thrust pads.
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Omori, Naomichi, Foil bearing.
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Klaass Reinhard M. (Phoenix AZ) Suriano Francis J. (Scottsdale AZ), Foil bearing alignment.
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Fortmann William E. (West Simsbury CT) Mrazek James A. (South Glastonbury CT) Telakowski Robert (Windsor Locks CT) Sherman Robert (West Hartford CT), High speed rotary machine bearing mount structure.
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Wieland Kurt H. (Rolling Hills Estates CA), Method and apparatus to provide thermal isolation of process gas bearings.
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Rossmann Axel (Karlsfeld DEX), Rotor for axial-flow turbomachines.
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Ide Russell D. (641 Arnold Rd. Coventry RI 02816), Self positioning beam mounted bearing and bearing and shaft assembly including the same.
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Buckmann Paul S. (Roseville CA), Self-aligning rotor-hydrostatic bearing system.
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Saville Marshall, Tilting pad foil thrust and journal bearings.
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