Piloting of a bearing housing-supported adjustment ring

Patent metadata

Field	Value
Publication number	US-10107187-B2
Application number	US-201514955126-A
Country	US
Kind code	B2
Filing date	Dec 1, 2015
Priority date	Dec 10, 2014
Publication date	Oct 23, 2018
Grant date	Oct 23, 2018

Abstract

A variable turbine geometry turbine turbocharger (1) includes vanes (30) configured to control flow of exhaust gas to a turbine wheel (12), and an adjustment ring (40) connected to each vane (30) that controls the angular orientation of all the vanes (30) in unison. The adjustment ring (40) is supported on the bearing housing (16) and is supported on, and piloted relative to, an axially extending nose portion (17) of the bearing housing (16) by surface features (60) formed along an inner edge (43) of the adjustment ring (40).

First claim

What is claimed, is:

1. A turbocharger ( 1 ) comprising
a bearing housing ( 16 ) including
a bore ( 15 ) that defines a longitudinal axis (R), and
a nose portion ( 17 ) that protrudes axially from one end of the bearing housing ( 16 ) and at least partially surrounds the bore ( 15 );

a turbine housing ( 4 ) secured to the bearing housing ( 16 ) and defining an exhaust gas inlet ( 6 ), an exhaust gas outlet ( 8 ) and a volute ( 10 ) disposed between the exhaust gas inlet ( 6 ) and the exhaust gas outlet ( 8 );
a turbine wheel ( 12 ) disposed in the turbine housing ( 4 ) between the volute ( 10 ) and the exhaust gas outlet ( 8 ); and
a variable turbine geometry (VTG) device ( 29 ) disposed in the turbine housing ( 4 ) between the volute ( 10 ) and the turbine wheel ( 12 ), the VTG device ( 29 ) including pivotable vanes ( 30 ) that control the flow of exhaust gas to the turbine wheel ( 12 ), and
an adjustment ring ( 40 ) that controls the rotational orientation of the vanes ( 30 ), the adjustment ring ( 40 ) rotatably supported on the nose portion ( 17 ) and wherein the adjustment ring ( 40 ) includes a radially-outward facing outer edge ( 45 ) that has an inwardly scalloped profile comprising a plurality of rounded, radially outwardly-protruding apexes and a plurality of radially inward-facing scallops alternating along the inwardly scalloped profile relative to the radially-outward facing outer edge ( 45 ) and wherein each apex of the plurality of rounded, radially outwardly-protruding apexes defines a hole.

2. The turbocharger ( 1 ) of claim 1 , wherein one of a radially inward-facing edge ( 43 ) of the adjustment ring ( 40 ) and a radially outward-facing surface ( 17 a ) of the nose portion ( 17 ) comprises piloting surface features ( 60 ) that center the adjustment ring ( 40 ) relative to the nose portion ( 17 ).

3. The turbocharger ( 1 ) of claim 2 , wherein the piloting surface features ( 60 ) comprise surface features ( 60 ) formed on the radially inward-facing edge of the adjustment ring ( 40 ).

4. The turbocharger ( 1 ) of claim 2 , wherein the piloting surface features ( 60 ) comprise circumferentially spaced profile segments ( 61 ) formed on the radially inward-facing edge of the adjustment ring ( 40 ), each profile segment ( 61 ) defining contact area ( 62 ) having a curvature that corresponds to the curvature of the nose portion ( 17 ).

5. The turbocharger ( 1 ) of claim 1 wherein a radially inward-facing edge ( 43 ) of the adjustment ring ( 40 ) comprises piloting surface features ( 60 ) that center the adjustment ring ( 40 ) relative to the nose portion ( 17 ), and the piloting surface features ( 60 ) include a profile segment ( 61 ) having a contact area ( 62 ), a first relief portion ( 65 ) that is recessed relative to and adjoins one end ( 63 ) of the contact area ( 62 ), and a second relief portion ( 66 ) that is recessed relative to and adjoins an opposed end ( 64 ) of the contact area ( 62 ).

6. The turbocharger ( 1 ) of claim 1 wherein a radially inward-facing edge ( 43 ) of the adjustment ring ( 40 ) comprises piloting surface features ( 60 ) that center the adjustment ring ( 140 ) relative to the nose, and the piloting surface features ( 60 ) include a profile segment ( 61 ) having a contact area ( 62 ) that engages the nose portion ( 17 ), a ramp portion ( 65 ) that is angled relative to and adjoins one end ( 63 ) of the contact area ( 62 ), and a relief portion ( 66 ) that adjoins an opposed end ( 64 ) of the contact area ( 62 ) and is radially spaced from the nose portion ( 17 ).

7. The turbocharger ( 1 ) of claim 5 , wherein the profile segment ( 61 ) when viewed along the longitudinal axis (R) provides the radially inward-facing edge ( 43 ) of the adjustment ring ( 40 ) with an irregular profile that extends circumferentially along a segment of the adjustment ring inner edge ( 43 ) and is repeated along the circumference of the adjustment ring inner edge ( 43 ) to provide a regularly repeating profile pattern along the adjustment ring inner edge ( 43 ).

8. The turbocharger ( 1 ) of claim 2 , wherein the piloting surface features ( 460 ) comprise surface features ( 461 ) formed on the radially outward-facing surface ( 17 a ) of the nose portion ( 17 ).

9. The turbocharger ( 1 ) of claim 2 , wherein the piloting surface features ( 460 ) comprise circumferentially spaced profile segments ( 461 ) formed on the radially outward-facing surface ( 17 a ) of the nose portion ( 17 ), each profile segment ( 461 ) defining a contact area ( 462 ) that engages the adjustment ring ( 440 ).

10. The turbocharger ( 1 ) of claim 1 , wherein
the bearing housing ( 16 ) includes an insert ( 80 ) that surrounds the nose portion ( 17 a ) and provides a bearing surface for the adjustment ring ( 40 ),
the adjustment ring ( 40 ) is rotatably supported on the insert ( 80 ),
the insert ( 80 ) is formed of a material that is different than the material used to form the bearing housing nose portion ( 17 a ), and
one of a radially inward-facing edge ( 43 ) of the adjustment ring ( 40 ) and a radially outward-facing surface ( 81 ) of the insert ( 80 ) comprises piloting surface features ( 60 ) that center the adjustment ring ( 40 ) relative to the nose portion ( 17 ).

11. An adjustment ring ( 40 ) configured to control the rotational orientation of vanes ( 30 ) of a variable turbine geometry (VTG) device ( 29 ) of a turbocharger ( 1 ), the adjustment ring ( 40 ) comprising the form of an annular plate and including a radially inward-facing inner edge ( 43 ) that defines a central opening ( 44 ), the inner edge ( 43 ) having a non-circular profile and comprising piloting surface features ( 60 ) that define a bearing surface upon which the adjustment ring ( 40 ) is supported relative to turbocharger ( 1 ); and
wherein the adjustment ring ( 40 ) includes a radially-outward facing outer edge ( 45 ) that has an inwardly scalloped profile comprising a plurality of rounded, radially outwardly-protruding apexes and a plurality of radially inward-facing scallops alternating along the inwardly scalloped profile relative to the radially-outward facing outer edge ( 45 ) and wherein each apex of the plurality of rounded, radially outwardly-protruding apexes defines a hole.

12. The adjustment ring ( 40 ) of claim 11 , wherein the piloting surface features ( 60 ) comprise circumferentially spaced profile segments ( 61 ) formed on the radially inward-facing inner edge ( 43 ) of the adjustment ring ( 40 ), each profile segment ( 61 ) defining a curved contact area ( 62 ).

13. The adjustment ring ( 40 ) of claim 11 wherein the piloting surface features ( 60 ) include a profile segment ( 61 ) having a contact area ( 62 ), a first relief portion ( 65 ) that is recessed relative to and adjoins one end ( 63 ) of the contact area ( 62 ), and a second relief portion ( 66 ) that is recessed relative to and adjoins an opposed end ( 64 ) of the contact area ( 62 ).

14. The adjustment ring ( 40 ) of claim 13 , wherein the profile segment ( 61 ) provides the radially inward-facing edge ( 43 ) of the adjustment ring ( 40 ) with an irregular profile that extends circumferentially along a segment of the inner edge ( 43 ) and is repeated along the circumference of the inner edge ( 43 ) to provide a regularly repeating profile pattern along the inner edge ( 43 ).

Assignees

• Borgwarner Inc

Inventors

• Howell Ryan
• Williams Greg

Classifications

• Y02T10/144

  Cross-Sectional Technologies · mapped topic

• F05D2270/58

  by mechanical means, e.g. levers, gears or cams · CPC title

• F02B37/24 Primary

  by using pumps or turbines with adjustable guide vanes · CPC title

• F01D17/165

  for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F05D2220/40

  in turbochargers · CPC title