Two-spool bypass turbojet with a rear electricity generator, and an air flow connection device and system
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-015/10
F01D-015/00
F02C-006/00
H02K-007/18
H02K-009/00
출원번호
US-0282663
(2005-11-21)
등록번호
US-7372175
(2008-05-13)
우선권정보
FR-04 12505(2004-11-25)
발명자
/ 주소
Bouiller,Philippe
Rousselin,Stephane
출원인 / 주소
SNECMA
대리인 / 주소
Oblon, Spivak, McClelland, Maier & Neustadt, P.C.
인용정보
피인용 횟수 :
7인용 특허 :
7
초록▼
A two-spool bypass turbojet includes a low-pressure spool having a rear portion carrying a low-pressure turbine provided with a low-pressure rotor. The turbojet includes a support structure connected to a casing and to a rear bearing in which the rotor is mounted. The bearing can be situated in an e
A two-spool bypass turbojet includes a low-pressure spool having a rear portion carrying a low-pressure turbine provided with a low-pressure rotor. The turbojet includes a support structure connected to a casing and to a rear bearing in which the rotor is mounted. The bearing can be situated in an enclosure including a liquid lubricant feed. The enclosure can be put to atmospheric pressure via an air feed pipe connected to the enclosure via a link. The turbojet further includes an electricity generator connected to the rear end of the low-pressure rotor that extends downstream from the link, which link is secured to the rotor and includes a device for guiding the liquid lubricant from the feed to the bearing.
대표청구항▼
What is claimed is: 1. A two-spool bypass turbojet comprising a low-pressure spool having, at its rear end, a low-pressure turbine provided with a low-pressure rotor, said turbojet including a support structure connected to a casing and to a rear bearing on which said rotor is mounted, said rear be
What is claimed is: 1. A two-spool bypass turbojet comprising a low-pressure spool having, at its rear end, a low-pressure turbine provided with a low-pressure rotor, said turbojet including a support structure connected to a casing and to a rear bearing on which said rotor is mounted, said rear bearing being situated in an enclosure having means for feeding said bearing with liquid lubricant, said enclosure being put to atmospheric pressure by an air feed pipe coaxial with said rotor and connected to said enclosure via link means enabling gas communication between said enclosure and said air feed pipe while guaranteeing sealing against liquid lubricant from said enclosure, the turbojet further comprising an electricity generator coaxial with said spool and situated outside said enclosure, said generator being disposed and being connected to the rear end of said low-pressure rotor which extends downstream from said link means, said link means being secured to said rotor and including guide means for guiding the liquid lubricant between said feed means and said bearing, wherein said guide means comprise a guide wall extending axially, at least the face of said guide wall that faces towards the axis of the turbojet being inclined radially outwards on going from said feed means towards said bearing. 2. A turbojet according to claim 1, wherein said link means are annular. 3. A turbojet according to claim 1, wherein said link means include at least one radial passage passing through said rotor and connected to said air feed pipe and to at least one radial-axis tube secured to said rotor and extending said passage in an outward direction. 4. A turbojet according to claim 1, wherein said electricity generator comprises a primary magnetic circuit constrained to rotate with said rotor and a secondary magnetic circuit secured to said casing. 5. A turbojet according to claim 1, wherein said electricity generator is configured to operate as a starter for said turbojet. 6. A turbojet according to claim 1, wherein said electricity generator is configured to power an accessory located outside said enclosure. 7. A turbojet according to claim 6, wherein said accessory is a pump. 8. A two-spool bypass turbojet comprising a low-pressure spool having, at its rear end, a low-pressure turbine provided with a low-pressure rotor, said turbojet including a support structure connected to a casing and to a rear bearing on which said rotor is mounted, said rear bearing being situated in an enclosure having means for feeding said bearing with liquid lubricant, said enclosure being put to atmospheric pressure by an air feed pipe coaxial with said rotor and connected to said enclosure via link means enabling gas communication between said enclosure and said air feed pipe while guaranteeing sealing against liquid lubricant from said enclosure, the turbojet further comprising an electricity generator coaxial with said spool and situated outside said enclosure, said generator being disposed and being connected to the rear end of said low-pressure rotor which extends downstream from said link means, said link means being secured to said rotor and including guide means for guiding the liquid lubricant between said feed means and said bearing, wherein said link means include at least one radial passage passing through said rotor and connected to said air feed pipe and to at least one radial-axis tube secured to said rotor and extending said passage in an outward direction, and wherein said guide means comprise a guide wall extending axially, at least the face of said guide wall that faces towards the axis of the turbojet being inclined radially outwards on going from said feed means towards said bearing, and wherein said link means comprise at least one chimney presenting a duct coaxial with said tube that extends radially outwards from said guide wall. 9. A turbojet according to claim 8, wherein said tube is a part that is separate from said chimney, wherein said tube is mounted in said duct, and wherein said guide wall is disposed at the radially-outer end of said duct. 10. A turbojet according to claim 8, wherein the radially-inner end of said chimney includes an axial extension directed downstream and provided with a radial rim facing outwards. 11. A turbojet according to claim 8, wherein the radially-inner end of said chimney includes a transverse extension extended radially by a radial wall extending to said guide wall and co-operating with said transverse extension, said chimney, and said guide wall to define an axial opening allowing the liquid lubricant to flow. 12. A turbojet according to claim 8, wherein said rotor is fitted in front of said radial passage with a rearwardly-open cavity extending under the rear bearing, said cavity communicating with said rear bearing via a passage, and wherein the front of said chimney and of said guide wall is disposed at the location of the opening of said cavity, the downstream end of said guide wall extending inside said cavity.
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