Turbocharger diffuser center body

Patent metadata

Field	Value
Publication number	US-10233779-B2
Application number	US-201514631639-A
Country	US
Kind code	B2
Filing date	Feb 25, 2015
Priority date	Feb 25, 2015
Publication date	Mar 19, 2019
Grant date	Mar 19, 2019

Abstract

A turbocharger turbine having housing walls defining a diffuser. Within the diffuser, a center body within the diffuser is supported by de-swirl vanes extending from the diffuser wall. The center body forms a de-swirl passageway having an increasing mean diameter of flow from an upstream end of the center body to a leading edge of the de-swirl vanes. A trailing edge of the de-swirl vanes is near the downstream end of the center body. Annular-type guide vanes surround the center body within the de-swirl passageway. A wastegate system is configured to vent wastegate flow into the diffuser through injection ports on the de-swirl vanes, annular guide vanes and/or center body.

First claim

What is claimed is:

1. A turbocharger turbine, comprising:
a turbine wheel;
a housing having housing walls that define a turbine passageway, the passageway including a wheel chamber containing the turbine wheel, the wheel chamber extending downstream from an inducer to an exducer of the turbine wheel, and an outlet passage extending axially downstream from the exducer, wherein the outlet passage defines a diffuser having a diffuser wall that increases in axially cross-sectional size from an upstream end of the diffuser to a downstream end of the diffuser; and
a center body within the diffuser, the center body having a center body wall forming a de-swirl passageway within the diffuser wall and forming the periphery of the center body; characterized in that
the center body is supported within the diffuser by one or more de-swirl vanes extending between the center body wall and the diffuser wall;
an upstream end of the center body is substantially the size of a downstream end of a hub of the turbine wheel;
the de-swirl passageway has by an increasing mean diameter of flow from the upstream end of the center body to a leading edge of the one or more de-swirl vanes;
the leading edges of the de-swirl vanes are located in the close axial vicinity of a maximum diffuser wall diameter axial location;
the leading edges of the de-swirl vanes are in the close axial vicinity of the maximum center body diameter axial location; and
downstream of the maximum center body diameter axial location, the center body wall reduces smoothly in diameter down to a distal tip at a downstream end of the center body.

2. The turbocharger turbine of claim 1 , wherein the de-swirl passageway is characterized by a mean diameter at the leading edge of the one or more de-swirl vanes that is in a range of 1.1 to 3.0 times a mean diameter immediately downstream of an upstream end of the center body.

3. The turbocharger turbine of claim 2 , wherein the de-swirl passageway is characterized by a cross-sectional area at the leading edge of the one or more de-swirl vanes that is less than 1.5 times a cross-sectional area immediately downstream of an upstream end of the center body.

4. The turbocharger turbine of claim 1 , wherein from a leading edge to a trailing edge, the de-swirl vanes extend axially in a purely axial direction.

5. The turbocharger turbine of claim 1 , wherein from an inner end to an outer end, the de-swirl vanes extend radially in a purely radial direction.

6. The turbocharger turbine of claim 1 , wherein a trailing edge of the de-swirl vanes is located in the close axial vicinity of the downstream end of the center body.

7. The turbocharger turbine of claim 1 , and further including annular-type guide vanes surrounding the center body between center body wall and diffuser wall.

8. The turbocharger turbine of claim 7 , wherein a leading edge of the annular-type guide vanes is located downstream of a leading edge of the de-swirl vanes.

9. The turbocharger turbine of claim 7 , wherein a leading edge of the annular-type guide vanes is located in the close axial vicinity of a leading edge of the de-swirl vanes.

10. The turbocharger turbine of claim 9 , wherein a trailing edge of the annular-type guide vanes is located in the close axial vicinity of a trailing edge of the de-swirl vanes.

11. The turbocharger turbine of claim 7 , wherein a trailing edge of the annular-type guide vanes is located in the close axial vicinity of a trailing edge of the de-swirl vanes.

12. A method of de-swirling an exhaust gas stream in a turbocharger turbine, wherein the turbine includes
a turbine wheel, and a housing having housing walls that define a turbine passageway extending axially, the passageway including a wheel chamber containing the turbine wheel, the wheel chamber extending downstream from an inducer to an exducer of the turbine wheel, and an outlet passage extending downstream from the exducer, wherein the outlet passage defines a diffuser having a diffuser wall that increases in axially cross-sectional size from an upstream end of the diffuser to a downstream end of the diffuser, comprising:
expanding the portion of the exhaust stream coming from the exducer to a larger mean diameter around a center body within the diffuser, the center body having a center body wall forming a forward de-swirl passageway and an aft de-swirl passageway within the diffuser wall and surrounding the center body, wherein expansion of the exhaust gas stream occurs in the forward de-swirl passageway;
passing the expanded exhaust gas stream through the aft de-swirl passageway such that the exhaust gas stream strikes one or more de-swirl vanes; and
contracting the exhaust gas stream that has struck the one or more de-swirl vanes in the aft de-swirl passageway, wherein the center body wall reduces smoothly in diameter down to a distal tip at a downstream end of the center body.

13. The method of claim 12 , wherein the de-swirl passageway is characterized by a mean diameter at the leading edge of the one or more de-swirl vanes that is in a range of 1.1 to 3.0 times a mean diameter immediately downstream of an upstream end of the center body.

14. The method of claim 12 , further comprising dividing the exhaust gas stream between an aft inner de-swirl passageway and an aft outer de-swirl passageway, the aft inner de-swirl passageway and aft outer de-swirl passageway portion being separated by one or more annular-type guide vanes surrounding the center body between center body wall and diffuser wall.

Assignees

• Honeywell Int Inc
• Garrett Transportation I Inc

Inventors

• Wilkins Christopher W
• Magalhaes Wagner M
• Sugumaran Bharathi Raja
• Babak Martin

Classifications

• F02B33/40

  of non-positive-displacement type · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F01D9/02 Primary

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title

• F01D25/24 Primary

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F02B37/18

  by bypassing exhaust {from the inlet to the outlet of turbine or to the atmosphere} · CPC title