Heat shield for mixed flow turbine wheel turbochargers
US-2016341072-A1 · Nov 24, 2016 · US
Turbocharger for an internal combustion engine, and turbine housing
US11002154B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-11002154-B2 |
| Application number | US-201916564458-A |
| Country | US |
| Kind code | B2 |
| Filing date | Sep 9, 2019 |
| Priority date | Mar 30, 2017 |
| Publication date | May 11, 2021 |
| Grant date | May 11, 2021 |
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- Title
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Abstract
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Example embodiments relate to a turbocharger for a combustion machine, having a bearing housing, in which a rotor shaft is mounted so as to be rotatable about a rotor axis of rotation. An exhaust-gas turbine with a turbine wheel is arranged rotationally conjointly on the rotor shaft and which has an impeller blade arrangement with multiple turbine blades, and with a turbine housing is mechanically fixed to the bearing housing and which surrounds the turbine wheel With respect to a meridional view of the exhaust-gas turbine, the turbine housing and the turbine wheel are designed and adapted to one another such that the following condition is satisfied: L cover L axTip > 1 - Tip clr R in × 3 π 4 × 1 ( 1 - R out R in ) .
First claim
Opening claim text (preview).
The invention claimed is: 1. A turbocharger for a combustion machine, comprising: a bearing housing, in which a rotor shaft is mounted so as to be rotatable about a rotor axis of rotation; and an exhaust-gas turbine with a turbine wheel which is arranged rotationally conjointly on the rotor shaft and which has an impeller blade arrangement with multiple turbine blades, and with a turbine housing which is mechanically fixed to the bearing housing and which surrounds the turbine wheel; wherein, with respect to a meridional view, the exhaust-gas turbine includes at least one turbine blade of the turbine wheel has a flow inlet edge and a flow outlet edge for exhaust-gas mass flow, the flow inlet edge has a maximum inlet radius R in and the flow outlet edge has a maximum outlet radius R out , in each case with respect to the rotor axis of rotation; the at least one turbine blade has an outer contour which faces toward the turbine housing and which extends from the flow inlet edge to the flow outlet edge and which has an axial extent length L axTip ; the turbine housing has a housing contour which is situated opposite the outer contour; the outer contour of the at least one turbine blade has an axial length segment L cover of the axial extent length L axTip in which the at least one turbine blade is axially covered by the turbine housing; and a smallest radial distance Tip clr with respect to the rotor axis of rotation is formed between the housing contour and the outer contour; and wherein the turbine housing and the turbine wheel are configured relative to one another such that the following condition is satisfied: L cover L axTip > 1 - Tip cir R in × 3 π 4 × 1 ( 1 - R out R in ) . 2. The turbocharger as claimed in claim 1 , wherein, for the ratio Tip clr to R in , the following applies: Tip cir R in ≤ 2.5 % . 3. The turbocharger as claimed in claim 1 , wherein, for the ratio Tip clr to R in , the following applies: Tip cir R in ≤ 2.0 % . 4. The turbocharger as claimed in claim 1 , wherein, for the ratio Tip clr to R in , the following applies: Tip cir R in ≤ 1.5 % . 5. The turbocharger as claimed in claim 1 , wherein, for the ratio L cover to L axtip , the following applies: L cover L axTip > 0.2 . 6. The turbocharger as claimed in claim 1 , wherein, for the ratio L cover to L axtip , the following applies: L cover L axTip > 0.25 . 7. The turbocharger as claimed in claim 1 , wherein, for the ratio L cover to L axtip , the following applies: L cover L axTip > 0.3 . 8. The turbocharger as claimed in claim 1 , wherein, for the ratio R out to R in , the following applies: 0.8 < R out R in < 0.95 . 9. The turbocharger as claimed in claim 1 , wherein for the ratio R out to R in , Rout Rin > 0.8 . 10. The turbocharger as claimed in claim 1 , wherein for the ratio R out to R in , Rout Rin < 0.95 . 11. A method for producing a turbocharger as claimed in claim 1 , comprising: determi
Assignees
Inventors
Classifications
- F01D5/147Primary
Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title
in turbochargers · CPC title
- F01D25/28Primary
Supporting or mounting arrangements, e.g. for turbine casing · CPC title
Radial bearings · CPC title
responsive to undesired position of rotor relative to stator {or to breaking-off of a part of the rotor}, e.g. indicating such position · CPC title
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- What does patent US11002154B2 cover?
- Example embodiments relate to a turbocharger for a combustion machine, having a bearing housing, in which a rotor shaft is mounted so as to be rotatable about a rotor axis of rotation. An exhaust-gas turbine with a turbine wheel is arranged rotationally conjointly on the rotor shaft and which has an impeller blade arrangement with multiple turbine blades, and with a turbine housing is mechanica…
- Who is the assignee on this patent?
- Cpt Group Gmbh, Vitesco Tech Gmbh
- What technology area does this patent fall under?
- Primary CPC classification F01D5/147. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue May 11 2021 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 3 related publications on this page (citations in our corpus or others sharing the same primary CPC).