Bearing-like structure to control deflections of a rotating component
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02K-003/02
출원번호
US-0093498
(2005-12-12)
등록번호
US-8205431
(2012-06-26)
국제출원번호
PCT/US2005/044825
(2005-12-12)
§371/§102 date
20080513
(20080513)
국제공개번호
WO2007/084100
(2007-07-26)
발명자
/ 주소
Kumar, Keshava
Ewing, Joseph
Burd, Steven
출원인 / 주소
United Technologies Corporation
대리인 / 주소
Carlson Gaskey & Olds P.C.
인용정보
피인용 횟수 :
0인용 특허 :
14
초록▼
A bearing like surface on a stationary component reduces deflection of an adjacent rotating component. The stationary component is generally parallel to and offset from a rotational component. The rotational component rotates about a central axis. Protrusions located on the stationary component are
A bearing like surface on a stationary component reduces deflection of an adjacent rotating component. The stationary component is generally parallel to and offset from a rotational component. The rotational component rotates about a central axis. Protrusions located on the stationary component are in contact with the rotational component to prevent deflection of the rotational component while reducing the friction between the rotational and stationary component. The protrusions have a generally flat surface that may be used to affix the protrusions to the stationary component. An arced surface of the protrusions is in contact with the rotating component. The number, size and the shape of the protrusions are determined by the requirements of the application.
대표청구항▼
1. A turbine engine comprising: a fan having a rotating component that axially deflects; and a stationary component having a portion facing and adjacent to said rotating component wherein at least two protrusions extend from said portion toward said rotating component to limit axial deflection of sa
1. A turbine engine comprising: a fan having a rotating component that axially deflects; and a stationary component having a portion facing and adjacent to said rotating component wherein at least two protrusions extend from said portion toward said rotating component to limit axial deflection of said fan. 2. The turbine engine of claim 1, wherein said at least one protrusion is a plurality of protrusions. 3. The turbine engine of claim 2, wherein said plurality of protrusions are spaced concentric about a center of said rotating component. 4. The turbine engine of claim 2, wherein said plurality of protrusions are evenly spaced from one another. 5. The turbine engine of claim 1, wherein said at least one protrusion is in contact with said rotating component. 6. The turbine engine of claim 5, wherein said at least one protrusion has an arced surface contacting said rotating component and a generally flat surface contacting said stationary component. 7. The turbine engine of claim 1, wherein said rotating component is a fan blade and said stationary component is a fan housing. 8. The turbine engine of claim 1, wherein said at least one protrusion and said stationary component are formed as one-piece. 9. The turbine engine of claim 1, wherein said at least one protrusion is coated to provide a lower friction surface. 10. The turbine engine of claim 1, wherein said at least one protrusion is initially spaced from said rotating component. 11. A turbine engine comprising: a fan having at least one fan blade rotating about a central axis; a stationary component having a portion facing and adjacent to said at least one fan blade; and a plurality of protrusions extending from said stationary component toward said at least one fan blade to limit axial deflection of said fan, wherein said plurality of protrusions are spaced concentrically about said central axis. 12. The turbine engine of claim 11, wherein said plurality of protrusions are each in contact with said at least one fan blade. 13. The turbine engine of claim 12, wherein said plurality of protrusions have an arced surface contacting said at least one fan blade and a generally flat surface contacting said stationary component. 14. The turbine engine of claim 11, wherein said plurality of protrusions and said stationary component are formed as one-piece. 15. The turbine engine of claim 11, wherein each of said plurality of protrusions are coated to provide a lower friction surface. 16. The turbine engine of claim 11, wherein said plurality of protrusions are initially spaced from said rotating component. 17. A device comprising: a rotating compressor component defining a central axis about which said component rotates; a stationary component having a portion facing and adjacent to said rotating component; and a plurality of protrusions extending from said stationary component portion and said rotating compressor component and towards the other to limit axial deflection of said rotating compressor component, wherein said plurality of protrusions are spaced concentric about said central axis. 18. The device of claim 17, wherein said plurality of protrusions are forward on said stationary component. 19. The device of claim 17, wherein said plurality of protrusions do not contact the other of said stationary component and said rotating component, wherein said rotating component rotates at low speeds. 20. The device of claim 17, wherein said at least one protrusion has an arced surface. 21. The turbine engine of claim 1, wherein the rotating component is a fan blade. 22. The turbine engine of claim 1, wherein the protrusion extends axially forward from the portion. 23. The turbine engine of claim 1, further comprising an axial compressor axially forward of the fan blade. 24. The turbine engine of claim 1, wherein the fan blade is a hollow fan blade having an inducer section, a hollow fan blade section, and a diffuser section, wherein the rotating component is disposed in the diffuser section. 25. The turbine engine of claim 24, wherein the airflow from the axial compressor is turned radially outwards in the inducer section, wherein airflow is turned axially forward in the diffuser section. 26. The turbine engine of claim 24, wherein a combustor section and turbine section are radially outward of the fan blade. 27. The turbine engine of claim 1, wherein the rotating component has an axially rearward face adjacent and opposing an axially forward face of the at least one protrusion. 28. The turbine engine of claim 1, wherein the plurality of protrusions is arranged to contact an axial face of the rotating component. 29. The turbine engine of claim 11, wherein the plurality of protrusions extend from said portion toward said rotating component to limit axial deflection of said fan. 30. The device of claim 17, wherein the plurality of protrusions extend from said portion toward said rotating component to limit axial deflection of said fan.
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이 특허에 인용된 특허 (14)
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