IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0623234
(2012-09-20)
|
등록번호 |
US-8684677
(2014-04-01)
|
발명자
/ 주소 |
- Mann, Stuart J.
- Parker, John Frederick
- Taylor, Martin David
- Morphet, Robert
|
출원인 / 주소 |
- Cummins Turbo Technologies Limited
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
4 |
초록
▼
According to an embodiment of the present invention, there is provided a variable geometry turbine comprising: a turbine wheel mounted on a turbine shaft within a housing assembly for rotation about a turbine axis, the housing assembly defining a gas flow inlet passage upstream of the turbine wheel;
According to an embodiment of the present invention, there is provided a variable geometry turbine comprising: a turbine wheel mounted on a turbine shaft within a housing assembly for rotation about a turbine axis, the housing assembly defining a gas flow inlet passage upstream of the turbine wheel; an annular wall member defining a wall of the inlet passage and which is displaceable in a direction substantially parallel to the turbine axis to control gas flow through the inlet passage; at least one moveable rod operably connected via a first end of the rod to the annular wall member, the rod being moveable to control displacement of the annular wall member, the rod extending in a direction substantially parallel to the turbine axis; wherein the rod is provided with a region of reduced radius which extends only partly around the rod, the region of reduced radius being remote from a second end of the rod to which a component of an actuator assembly for moving the rod is connectable.
대표청구항
▼
1. A variable geometry turbine comprising: a turbine wheel mounted on a turbine shaft within a housing assembly for rotation about a turbine axis, the housing assembly defining a gas flow inlet passage upstream of the turbine wheel;an annular wall member defining a wall of the inlet passage and whic
1. A variable geometry turbine comprising: a turbine wheel mounted on a turbine shaft within a housing assembly for rotation about a turbine axis, the housing assembly defining a gas flow inlet passage upstream of the turbine wheel;an annular wall member defining a wall of the inlet passage and which is displaceable in a direction substantially parallel to the turbine axis to control gas flow through the inlet passage;at least one moveable rod operably connected via a first end of the rod to the annular wall member, the rod being moveable to control displacement of the annular wall member, the rod extending in a direction substantially parallel to the turbine axis;wherein the rod is provided with a region of reduced radius which extends only partly around the rod, the region of reduced radius being remote from a second end of the rod to which a component of an actuator assembly for moving the rod is connectable. 2. The turbine as claimed in claim 1, wherein the region of reduced radius is adjacent to or forms part of the first end of the rod, and is proximal to the annular wall member. 3. The turbine as claimed in claim 2, wherein the turbine comprises a guide configured to guide movement of the rod, and/or to support the rod. 4. The turbine as claimed in claim 2, wherein the annular wall member is provided with a plurality of vanes arranged, in use, to deflect gas flowing through the inlet passageway towards the direction of rotation of the turbine wheel. 5. The turbine as claimed in claim 2, wherein the first end of the rod comprises the reduced radius region, and wherein the reduced radius region has a radius that is sufficiently small to fit into a cavity provided in the annular wall member, whereas a region of the rod not having the reduced radius region has a radius that is too large to fit into the cavity provided in the annular wall member. 6. The turbine as claimed in claim 1, wherein the turbine comprises a guide configured to guide movement of the rod, and/or to support the rod. 7. The turbine as claimed in claim 6, wherein the region of reduced radius is arranged to ensure that, in use, and when the rod is moved along the guide, the region of reduced radius provides a clearance between the rod and the guide. 8. The turbine as claimed in claim 7, wherein the rod is provided with an edge, the edge being formed at a point on the rod where the region of reduced radius is adjacent to a region of nominal radius of the rod. 9. The turbine as claimed in claim 7, wherein the guide defines an aperture through which the rod is moveable. 10. The turbine as claimed in claim 6, wherein the rod is provided with an edge, the edge being formed at a point on the rod where the region of reduced radius is adjacent to a region of nominal radius of the rod. 11. The turbine as claimed in claim 10, wherein the region of reduced radius is arranged to ensure that, in use, and when the rod is moved along the guide, the edge passes along the guide. 12. The turbine as claimed in claim 6, wherein the guide defines an aperture through which the rod is moveable. 13. The turbine as claimed in claim 6, wherein, in use, a first side of the rod is pushed into the guide, and wherein the region of reduced radius is formed on a second, substantially opposite side of the rod to the first side of the rod. 14. The turbine as claimed in claim 1, wherein the annular wall member is provided with a plurality of vanes arranged, in use, to deflect gas flowing through the inlet passageway towards the direction of rotation of the turbine wheel. 15. The turbine as claimed in claim 1, wherein the first end of the rod comprises the reduced radius region, and wherein the reduced radius region has a radius that is sufficiently small to fit into a cavity provided in the annular wall member, whereas a region of the rod not having the reduced radius region has a radius that is too large to fit into the cavity provided in the annular wall member. 16. The turbine as claimed in claim 1, wherein the first end of the rod comprises the reduced radius region, and wherein the reduced radius region has a radius that is sufficiently small to fit into an area extending between inner and outer radii of the annular wall member, whereas a region of the rod not having the reduced radius region has a radius that is too large to fit into the area extending between the inner and outer radii of the annular wall member. 17. The turbine as claimed in claim 1, wherein the region of reduced radius forms a surface which is substantially flatter than a surface of a part of the rod not having the region of reduced radius. 18. The turbine as claimed in claim 17, wherein the rod is oriented such that the substantially flatter surface faces in an inwardly or outwardly radial direction with respect to the turbine axis. 19. The turbine as claimed in claim 1, wherein the region of reduced radius has a radius which is 10% to 60% less than a nominal radius of the rod. 20. The turbine as claimed in claim 1, wherein the turbine forms part of a turbocharger.
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