Device for lubricating a component in a turbomachine
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-025/26
F01D-025/24
출원번호
US-0241912
(2005-10-04)
등록번호
US-7252476
(2007-08-07)
우선권정보
FR-04 11435(2004-10-27)
발명자
/ 주소
Prestel,Sebastien Jean Laurent
Renon,Olivier
Soupizon,Jean Luc
출원인 / 주소
SNECMA
대리인 / 주소
Oblon, Spivak, McClelland, Maier & Neustadt, P.C.
인용정보
피인용 횟수 :
2인용 특허 :
2
초록▼
A device for lubricating a component in a turbomachine, in particular a shaft bearing in a turbojet, the device comprising an annular support part defining a lubrication chamber around the component, an annular cover mounted in sealed manner on the part and including a lubricating oil inlet, and an
A device for lubricating a component in a turbomachine, in particular a shaft bearing in a turbojet, the device comprising an annular support part defining a lubrication chamber around the component, an annular cover mounted in sealed manner on the part and including a lubricating oil inlet, and an annular channel for passing a flow of pressurizing and cooling air, which channel is formed between the part and the cover, and communicates with ducts in the support part and an annular enclosure formed in the cover for passing the pressurizing and cooling air.
대표청구항▼
What is claimed is: 1. A lubrication device for lubricating a shaft bearing in a turbojet, the device comprising: an annular component support part mounted on stationary elements and defining a lubrication chamber around the shaft bearing; and an annular cover including an oil inlet for lubricating
What is claimed is: 1. A lubrication device for lubricating a shaft bearing in a turbojet, the device comprising: an annular component support part mounted on stationary elements and defining a lubrication chamber around the shaft bearing; and an annular cover including an oil inlet for lubricating the shaft bearing, the annular cover having a radial end face mounted in a sealed manner on a radial end face of said annular support part, sealing being provided by an annular gasket mounted between the support part and the cover, said cover including an annular enclosure for feeding pressurizing and cooling air, the enclosure is fed at its upstream end by ducts formed through the support part and having their downstream ends opening out around the annular gasket, wherein the device includes means for providing a flow of pressurizing and cooling air between the radial end face of the support part and the radial end face of said cover around said annular gasket. 2. A lubrication device according to claim 1, wherein the annular gasket is mounted between cylindrical bearing surfaces of the support part and of the cover, and the means for providing a flow of pressurized and cooling air opens out in a vicinity of the annular gasket at an interface between said cylindrical bearing surfaces. 3. A lubrication device according to claim 1, wherein the means for providing a flow of pressurized and cooling air comprises an annular channel formed in the radial end face of the cover facing the downstream ends of the ducts in the support part, and includes orifices in alignment with said ducts and opening out into said enclosure. 4. A lubrication device according to claim 3, wherein said annular channel opens out to an interface between cylindrical bearing surfaces of the support part and of the cover via a chamfer in a peripheral edge of the radial end face of the support part. 5. A lubrication device according to claim 1, wherein an axially-extending annular gap is formed between the radial end face of the support part and the radial end face of the cover level with the downstream ends of the ducts in the support part. 6. A lubrication device according to claim 5, wherein an annular channel is formed by a chamfer in a peripheral edge of the radial end face of the support part, said chamfer interconnecting the axially-extending gap and an interface of cylindrical bearing surfaces of the support part and of the cover. 7. A lubrication device according to claim 6, wherein the annular channel communicates with the enclosure of the cover via at least one hole in the radial end face of the cover. 8. A lubrication device according to claim 5, wherein another sealing gasket is mounted in the axially-extending annular gap and includes orifices for passing pressurizing and cooling air, the orifices are in alignment with the ducts in the support part. 9. A turbojet, comprising: a turbine whose shaft is guided by a bearing fitted with lubrication means, wherein the lubrication means include a lubrication device according to claim 1. 10. A lubrication device, comprising: an annular component support part having a radial end face and defining a lubrication chamber around a component; an annular cover having a radial end face disposed to the radial end face of the annular support part, the annular cover including an inlet configured to lubricate the component, and an annular enclosure configured to feed air; an annular gasket configured to seal the annular component support part and the annular cover; and an annular channel configured to provide a flow of the air around the annular gasket. 11. A lubrication device according to claim 10, wherein the annular gasket is mounted between cylindrical bearing surfaces of the annular component support part and of the annular cover, and the annular channel opens out in a vicinity of the annular gasket at an interface between the cylindrical bearing surfaces. 12. A lubrication device according to claim 10, wherein the annular component support part includes ducts, and the annular channel is formed in the radial end face of the annular cover facing downstream ends of the ducts, and includes orifices in alignment with the ducts and opening into the annular enclosure. 13. A lubrication device according to claim 12, wherein the annular channel opens out to an interface between cylindrical bearing surfaces of the annular component support part and of the annular cover via a chamfer in a peripheral edge of the radial end face of the annular component support part. 14. A lubrication device according to claim 10, wherein the annular component support part includes ducts, and an axially-extending annular gap is formed between the radial end face of the annular component support part and the radial end face of the annular cover level with downstream ends of the ducts. 15. A lubrication device according to claim 14, wherein the annular channel is formed by a chamfer in a peripheral edge of the radial end face of the annular component support part, the chamfer interconnecting the axially-extending gap and an interface of cylindrical bearing surfaces of the annular component support part and of the annular cover. 16. A lubrication device according to claim 15, wherein the annular channel communicates with the enclosure via at least one hole in the radial end face of the annular cover. 17. A lubrication device according to claim 14, wherein another sealing gasket is mounted in the axially-extending annular gap and includes orifices to pass the air, the orifices are in alignment with the ducts. 18. A lubrication device according to claim 10, wherein the air is at a higher pressure than the pressure inside the lubrication chamber. 19. A lubrication device according to claim 10, wherein the air is at a higher pressure than the pressure outside the lubrication device. 20. A turbojet, comprising: a turbine whose shaft is guided by a bearing fitted with a lubrication device according to claim 10.
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이 특허에 인용된 특허 (2)
Hovan, Edward J., Bearing compartment for a gas turbine engine.
Stevens Leonard W. (Vernon CT) Siwik William S. (Manchester CT) Moore William A. (Durham CT) Brown Wayne M. (North Granby CT) Barnard Andrew A. (Glastonbury CT), Bearing compartment protection system.
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