Turbocharger with turbine shroud

Patent metadata

Field	Value
Publication number	US-9810238-B2
Application number	US-201514642634-A
Country	US
Kind code	B2
Filing date	Mar 9, 2015
Priority date	Mar 9, 2015
Publication date	Nov 7, 2017
Grant date	Nov 7, 2017

Abstract

A turbine assembly includes a turbine housing and a turbine wheel disposed within the turbine housing. The turbine wheel includes a rotational axis and a plurality of blades. The turbine assembly includes a turbine shroud disposed between the turbine housing and the turbine wheel along a radial direction. The turbine shroud is separate from the turbine housing. The turbine shroud includes an annular portion extending generally in an axial direction with respect to the rotational axis and a plate portion intersecting the annular portion to form a convex curved surface. At least a portion of the blades is disposed in at least a portion of the annular portion. Each blade includes a leading edge and a tip portion. Each leading edge is angled with respect to the rotational axis, and each tip portion forms a concave portion that curves around the curved surface of the turbine shroud.

First claim

We claim:

1. A turbine assembly comprising:
a turbine housing;
a turbine wheel disposed within the turbine housing, the turbine wheel including a first end opposite a second end and a rotational axis extending between the first end and the second end, the turbine wheel including a plurality of blades;
a turbine shroud disposed between the turbine housing and the turbine wheel along a radial direction, the turbine shroud being separate from the turbine housing, the turbine shroud including:
an annular portion extending generally in an axial direction with respect to the rotational axis, at least a portion of the plurality of blades being disposed in at least a portion of the annular portion, and
a plate portion intersecting the annular portion to form a convex curved surface;

wherein each of the plurality of blades of the turbine wheel includes a leading edge and a tip portion, each leading edge being angled with respect to the rotational axis, each tip portion forming a concave portion that curves around the curved surface of the turbine shroud; and
a heat shield disposed adjacent the second end of the turbine wheel, the turbine shroud being attached to the heat shield, wherein the heat shield further includes a plurality of bores extending along the radial direction for receiving a plurality of pins configured to radially attach the heat shield to a bearing housing, wherein the plurality of pins are press fit into respective bores in the heat shield and slidably received in respective bores in the bearing housing.

2. The turbine assembly of claim 1 , wherein a gap is formed between at least a portion of the turbine shroud and the turbine housing.

3. The turbine assembly of claim 1 , wherein the turbine shroud is symmetric with respect to the rotational axis, and the turbine housing is asymmetric with respect to the rotational axis.

4. The turbine assembly of claim 1 , wherein each of the plurality of blades has a leading edge that forms an angle of about 10 to about 40 degrees with respect to the rotational axis.

5. The turbine assembly of claim 1 , wherein the leading edge and the tip portion of each of the plurality of blades intersect to form a first corner.

6. The turbine assembly of claim 5 , wherein the curved surface of the turbine shroud is disposed adjacent the first corner of each of the plurality of blades such that each first corner is aligned with the curved surface of the turbine shroud along the radial direction and along the axial direction.

7. The turbine assembly of claim 1 , wherein a gap between a first point on the curved surface and the first corner is less than about 0.025 inches during operation of the turbine assembly.

8. The turbine assembly of claim 1 , wherein:
the concave portion is located between an intermediate point on the tip portion and the first corner; and
a gap between a second point on the curved surface of the turbine shroud and the intermediate point on the tip portion is less than about 0.025 inches during the operation of the turbine assembly.

9. The turbine assembly of claim 1 , wherein:
each of the plurality of blades have a trailing edge intersecting the tip portion to form a second corner; and
a gap between the second corner and a point on the annular portion of the turbine shroud is less than about 0.025 inches during the operation of the turbine assembly.

10. The turbine assembly of claim 1 , wherein the turbine shroud further includes a nozzle portion, the nozzle portion including the plate portion and a plurality of nozzle vanes attached to the plate portion, the plurality of nozzle vanes being configured to receive a flow of exhaust from a turbine inlet in the turbine housing.

11. The turbine assembly of claim 1 , further including a sealing element disposed around the annular portion and configured to limit a flow of exhaust between the turbine housing and the turbine shroud.

12. A turbocharger comprising:
a compressor housing including a compressor wheel;
a turbine housing including a turbine wheel, the turbine wheel including a first end opposite a second end and a rotational axis extending between the first end and the second end;
a shaft attached at a first end to the compressor wheel and attached at a second end to the turbine wheel;
a bearing housing connecting the compressor housing to the turbine housing;
a turbine shroud disposed between the turbine housing and the turbine wheel along a radial direction, the turbine shroud being separate from the turbine housing; and
a heat shield radially attached to the bearing housing by a plurality of pins extending along the radial direction, the heat shield being disposed between the bearing housing and the turbine wheel, wherein the plurality of pins are press fit into respective bores in the heat shield and slidably received in respective bores in the bearing housing.

13. The turbocharger of claim 12 , wherein the turbine housing is rotatable around the rotational axis relative to the heat shield and the turbine shroud.

14. The turbocharger of claim 12 , wherein the turbine shroud is attached to the heat shield by a plurality of fasteners.

Assignees

• Caterpillar Inc

Inventors

• Annati Richard E
• Mccormack Jeffrey W
• Frick Matthew J

Classifications

• F05D2220/40

  in turbochargers · CPC title

• F01D9/045 Primary

  for radial flow machines or engines · CPC title

• F04D29/4226 Primary

  Fan casings · CPC title