Centering mechanisms for turbocharger bearings
View Patent ↗An turbocharger assembly can include a compressor side ring disposed at least partially in a compressor side annular notch of a bearing, the ring in contact with a bore wall of a housing and the bearing to hinder axial flow of lubricant to a compressor end of the bearing and to reduce variation in a lubricant squeeze film thickness defined by and between the bearing and the bore wall and a turbine side ring disposed at least partially in a turbine side annular notch, the ring in contact with the bore wall and the bearing to hinder axial flow of lubricant to the turbine end of the bearing and to reduce variation in the lubricant squeeze film thickness. Various other springs, bearings, housings, assemblies, etc., are also disclosed.
1. An assembly comprising:
a turbocharger center housing that comprises a bore wall that defines a bore having a bore axis extending between a compressor end and a turbine end of the housing, a lower recess extending from the bore radially outwardly and azimuthally with respect to the bore axis, a lubricant inlet for flow of lubricant to the bore, and a lubricant outlet adjacent to the lower recess for flow of lubricant from the lower recess;
a bearing, disposed in the bore, that comprises
a compressor end and, proximate thereto, a compressor side journal, a compressor side annular channel, and openings in the compressor side annular channel for flow of lubricant from the bore to the compressor side journal, and, disposed axially between the compressor side annular channel and the compressor end, a compressor side annular notch, and
a turbine end and, proximate thereto, a turbine side journal, a turbine side annular channel, and openings in the turbine side annular channel for flow of lubricant from the bore to the turbine side journal, and, disposed axially between the turbine side annular channel and the turbine end, a turbine side annular notch;
a compressor side ring disposed at least partially in the compressor side annular notch and in contact with the bore wall and the bearing to hinder axial flow of lubricant to the compressor end of the bearing and to reduce variation in a lubricant squeeze film thickness defined by and between the bearing and the bore wall; and
a turbine side ring disposed at least partially in the turbine side annular notch and in contact with the bore wall and the bearing to hinder axial flow of lubricant to the turbine end of the bearing and to reduce variation in the lubricant squeeze film thickness.
2. The assembly of claim 1 wherein at least one of the rings comprises a planar spring.
3. The assembly of claim 1 wherein at least one of the rings comprises a mesh ring.
4. The assembly of claim 1 wherein at least one of the rings comprises a cylindrical ring.
5. The assembly of claim 1 wherein at least one of the rings comprises a ring member that comprises one or more tabs.
6. The assembly of claim 1 wherein at least one of the rings comprises a gap defined by a first end and a second end.
7. The assembly of claim 1 wherein the lubricant inlet and the lubricant outlet are located axially between the compressor side annular notch and the turbine side annular notch.
8. The assembly of claim 1 further comprising another lubricant inlet for flow of lubricant to the bore.
9. The assembly of claim 8 wherein the lubricant inlets and the lubricant outlet are located axially between the compressor side annular notch and the turbine side annular notch.
10. A method comprising:
providing an assembly that comprises
a turbocharger center housing that comprises a bore wall that defines a bore having a bore axis extending between a compressor end and a turbine end of the housing, a lower recess extending from the bore radially outwardly and azimuthally with respect to the bore axis, a lubricant inlet for flow of lubricant to the bore, and a lubricant outlet adjacent to the lower recess for flow of lubricant from the lower recess,
a bearing, disposed in the bore, that comprises
a compressor end and, proximate thereto, a compressor side journal, a compressor side annular channel, and openings in the compressor side annular channel for flow of lubricant from the bore to the compressor side journal, and, disposed axially between the compressor side annular channel and the compressor end, a compressor side annular notch, and
a turbine end and, proximate thereto, a turbine side journal, a turbine side annular channel, and openings in the turbine side annular channel for flow of lubricant from the bore to the turbine side journal, and, disposed axially between the turbine side annular channel and the turbine end, a turbine side annular notch,
a compressor side ring disposed at least partially in the compressor side annular notch and in contact with the bore wall and the bearing to hinder axial flow of lubricant to the compressor end of the bearing and to reduce variation in a lubricant squeeze film thickness defined by and between the bearing and the bore wall; and
a turbine side ring disposed at least partially in the turbine side annular notch and in contact with the bore wall and the bearing to hinder axial flow of lubricant to the turbine end of the bearing and to reduce variation in the lubricant squeeze film thickness;
flowing lubricant to the bore to form a lubricant squeeze film;
hindering axial flow of the lubricant to the compressor end by the compressor side ring and axial flow of the lubricant to the turbine end by the turbine side ring; and
reducing variation in the lubricant film thickness by the compressor side ring and the turbine side ring.
11. The method of claim 10 wherein at least one of the rings comprises a planar spring.
12. The method of claim 10 wherein at least one of the rings comprises a mesh ring.
13. The method of claim 10 wherein at least one of the rings comprises a cylindrical ring.
14. The method of claim 10 wherein at least one of the rings comprises a ring member that comprises one or more tabs.
15. The method of claim 10 wherein at least one of the rings comprises a gap defined by a first end and a second end.
16. The method of claim 10 wherein the lubricant inlet and the lubricant outlet are located axially between the compressor side annular notch and the turbine side annular notch.
17. The method of claim 10 further comprising another lubricant inlet for flow of lubricant to the bore.
18. The method of claim 17 wherein the lubricant inlets and the lubricant outlet are located axially between the compressor side annular notch and the turbine side annular notch.