Exhaust-gas turbocharger
US-9222366-B2 · Dec 29, 2015 · US
US9988977B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9988977-B2 |
| Application number | US-201514870643-A |
| Country | US |
| Kind code | B2 |
| Filing date | Sep 30, 2015 |
| Priority date | Oct 14, 2014 |
| Publication date | Jun 5, 2018 |
| Grant date | Jun 5, 2018 |
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A turbocharger ( 10 ) includes a shaft ( 26 ) rotatably supported within a bearing housing ( 28 ), a turbine wheel ( 22 ) connected to the shaft ( 26 ), and a heat shield ( 150, 250 ) disposed between the turbine wheel ( 22 ) and the bearing housing ( 28 ). The heat shield ( 150, 250 ) includes surface features ( 80, 180 ) formed on at least one of a sidewall ( 57 ) portion thereof and a flange ( 63 ) portion thereof that locate the heat shield ( 150, 250 ) relative to the bearing housing ( 28 ) such that the heat shield ( 150, 250 ) is coaxial with the rotational axis of the shaft ( 26 ).
Opening claim text (preview).
What is claimed is: 1. A turbocharger ( 10 ) comprising a bearing housing ( 28 ), a shaft ( 26 ) rotatably supported within the bearing housing ( 28 ), a turbine housing ( 14 ) connected to the bearing housing ( 28 ), a turbine wheel ( 22 ) disposed in the turbine housing ( 14 ) and connected to the shaft ( 26 ), and a heat shield ( 150 ) including a radially extending base ( 51 ) having a central opening ( 52 ) that receives the shaft ( 26 ), a radially extending flange ( 63 ) that is axially offset from the radially extending base ( 51 ), and a sidewall ( 57 ) extending between the base ( 51 ) and the flange ( 63 ), the sidewall ( 57 ) having a first end ( 58 ) connected to a radially-outermost end of the base ( 51 ), and a second end ( 59 ) that is opposed to the first end ( 58 ) and connected to a radially-innermost end ( 65 ) of the flange ( 63 ), wherein the heat shield ( 150 ) includes surface features ( 80 ) formed on the flange ( 63 ) that locate the heat shield ( 150 ) relative to the bearing housing ( 28 ), the surface features ( 80 ) comprising an axially protruding ridge ( 82 ) that is formed in the flange ( 63 ), the ridge ( 82 ) being received within a circumferential groove ( 23 ) formed in the bearing housing ( 28 ) whereby the heat shield ( 150 ) is located relative to the bearing housing ( 28 ) such that the heat shield ( 150 , 250 ) is co-axial with the rotational axis of the shaft ( 26 ). 2. The turbocharger ( 10 ) of claim 1 , wherein the axially protruding ridge ( 82 ) is convex on a bearing housing-facing surface ( 66 ) of the flange ( 63 ), and concave on a turbine housing-facing surface ( 67 ) of the flange ( 63 ). 3. The turbocharger ( 10 ) of claim 1 , wherein the ridge ( 82 ) is continuous in a circumferential direction. 4. The turbocharger ( 10 ) of claim 1 , wherein the ridge ( 82 ) is formed at a location of the flange ( 63 ) that adjoins the sidewall ( 57 ). 5. The turbocharger ( 10 ) of claim 1 , wherein the bearing housing ( 28 ) includes a nose ( 29 ) on the turbine housing-facing surface ( 28 a ) of the bearing housing ( 28 ), axially protruding towards the turbine housing ( 14 ) and centered on a shaft-receiving bore ( 30 ), and wherein a radial clearance is provided between the central opening ( 52 ) of the heat shield ( 150 ) and the bearing housing nose ( 29 ). 6. A turbocharger ( 10 ) comprising a bearing housing ( 28 ), a shaft ( 26 ) rotatably supported within the bearing housing ( 28 ), a turbine housing ( 14 ) connected to the bearing housing ( 28 ), a turbine wheel ( 22 ) disposed in the turbine housing ( 14 ) and connected to the shaft ( 26 ), and a heat shield ( 250 ) including a radially extending base ( 51 ) having a central opening ( 52 ) that receives the shaft ( 26 ), a radially extending flange ( 63 ) that is axially offset from the radially extending base ( 51 ), and a sidewall ( 57 ) extending between the base ( 51 ) and the flange ( 63 ), the sidewall ( 57 ) having a first end ( 58 ) connected to a radially-outermost end of the base ( 51 ), and a second end ( 59 ) that is opposed to the first end ( 58 ) and connected to a radially-innermost end ( 65 ) of the flange ( 63 ), wherein the heat shield ( 250 ) includes surface features ( 180 ) formed on the sidewall ( 57 ) that locate the heat shield ( 250 ) relative to the bearing housing ( 28 ), the surface features ( 180 ) including radially inward-extending protrusions ( 182 , 282 ) that are spaced along a circumference of the sidewall ( 57 ), a radially inward-facing surface ( 60 a ) of the protrusions ( 182 , 282 ) abutting a radially outward-facing surface ( 28 b ) of the bearing housing ( 28 ), whereby the heat shield ( 250 ) is located relative to the bearing housing ( 28 ) such that the heat shield ( 150 , 250 ) is co-axial with the rotational axis of the shaft ( 26 ). 7. The turbocharger ( 10 ) of claim 6 , wherein a ratio (Ls/Lp) of a circumferential dimension (Ls) of the sidewall ( 57 ) to a circumferential dimension (Lp) of the protrusion ( 182 ) is in a range of 20 to 100. 8. The turbocharger ( 10 ) of claim 6 , wherein the heat shield ( 250 ) includes three protrusions ( 182 , 282 ). 9. The turbocharger ( 10 ) of claim 6 , wherein a dimension (Lp) of the protrusion ( 182 , 282 ) in a circumferential direction is less than 10% of a circumferential dimension (Ls) of the sidewall ( 57 ) without protrusion. 10. The turbocharger ( 10 ) of claim 6 , wherein the bearing housing ( 28 ) includes a nose ( 29 ) on the turbine housing-facing surface ( 28 a ) of the bearing housing ( 28 ), axially protruding towards the turbine housing ( 14 ) and centered on a shaft-receiving bore ( 30 ), and wherein a radial clearance is provided between the central opening ( 52 ) of the heat shield ( 250 ) and the bearing housing nose ( 29 ).
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