Compressor assembly having a vaneless space

Patent metadata

Field	Value
Publication number	US-10066639-B2
Application number	US-201514642175-A
Country	US
Kind code	B2
Filing date	Mar 9, 2015
Priority date	Mar 9, 2015
Publication date	Sep 4, 2018
Grant date	Sep 4, 2018

Abstract

A compressor assembly is disclosed. The compressor assembly may have a compressor housing. The compressor housing may have an inner wall. The compressor assembly may also have a compressor impeller disposed within the compressor housing. Further, the compressor assembly may have a bearing housing attached to the compressor housing. The bearing housing may have a body portion and a web extending outward from the body portion to a web end. The compressor assembly may also have a diffuser ring disposed between the inner wall and the web. The diffuser ring may have at least one vane. In addition, the compressor assembly may have a vaneless space extending between the compressor impeller and the vane. The vaneless space may be inclined at an angle relative to a plane disposed orthogonal to a rotational axis of the compressor assembly.

First claim

What is claimed is:

1. A turbocharger, comprising:
a turbine housing;
a turbine wheel disposed within the turbine housing and configured to be driven by exhaust received from an engine;
a compressor housing, including an inner wall;
a compressor impeller disposed within the compressor housing;
a shaft connecting the turbine wheel and the compressor impeller;
a bearing housing attached to the compressor housing and the turbine housing, the bearing housing including:
a body portion; and
a web extending outward from the body portion to a web end;
a diffuser ring disposed between the inner wall and the web, the diffuser ring including at least one vane; and
a vaneless space extending between the compressor impeller and the at least one vane, the vaneless space being inclined at an angle relative to a plane disposed orthogonal to a rotational axis of the turbocharger, and wherein a radial extent of the vaneless space is at least 20% of a maximum radius of the compressor impeller.

2. The turbocharger of claim 1 , wherein the web includes:
a ledge disposed between the body portion and the web end;
a first web face extending from the body portion to the ledge; and
a second web face extending from the ledge to the web end, wherein a portion of the vaneless space is disposed between the inner wall and the second web face.

3. The turbocharger of claim 2 , wherein the diffuser ring includes:
a back plate extending from a back plate leading edge to a back plate trailing edge, the back plate leading edge being disposed adjacent the ledge; and
a plurality of vanes extending from the back plate towards the inner wall, wherein a remaining portion of the vaneless space is disposed between the inner wall and the back plate.

4. The turbocharger of claim 3 , wherein the compressor impeller includes:
a compressor hub extending from a hub front end to a hub rear end; and
a plurality of compressor blades disposed on the compressor hub in a plurality of rows, the rows including a rearmost row disposed adjacent the hub rear end, wherein the vaneless space extends from outer edges of the compressor blades in the rearmost row to the vanes.

5. The turbocharger of claim 4 , wherein
the vanes extend from vane leading edges to vane trailing edges,
the vane leading edges intersect the back plate between the back plate leading edge and the back plate trailing edge, and
the vaneless space extends from the outer edges of the compressor blades in the rearmost row to the vane leading edges.

6. The turbocharger of claim 2 , wherein
the angle is a first angle, and
the inner wall is disposed at a second angle relative to the plane.

7. The turbocharger of claim 6 , wherein the second web face is disposed at a third angle relative to the plane.

8. The turbocharger of claim 7 , wherein the first angle, the second angle, and the third angle are equal.

9. The turbocharger of claim 1 , wherein a radial extent of the vaneless space ranges between 20% to 40% of a maximum radius of the compressor impeller.

Assignees

• Caterpillar Inc

Inventors

• Annati Richard E
• Musgrave Dean S

Classifications

• F01D25/243

  Flange connections; Bolting arrangements (F01D25/265 takes precedence) · CPC title

• F04D17/06

  Helico-centrifugal pumps · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F04D29/624

  especially adapted for elastic fluid pumps · CPC title

• F04D29/4206

  especially adapted for elastic fluid pumps · CPC title