Turbocharger compressor and method

Patent metadata

Field	Value
Publication number	US-10167876-B2
Application number	US-201614987176-A
Country	US
Kind code	B2
Filing date	Jan 4, 2016
Priority date	Jan 4, 2016
Publication date	Jan 1, 2019
Grant date	Jan 1, 2019

Abstract

A compressor for a turbocharger for use with an internal combustion engine includes a compressor wheel having a central hub having a centerline, a root portion, and an end portion. A plurality of blades is formed around the central hub. The plurality of blades includes a group of full-blades extending from the root portion of the central hub up to a maximum distance from the root portion along the centerline, the maximum distance being adjacent the end portion of the central hub. The plurality of blades includes a group of half-blades, the half-blades extending from the root portion of the hub to an area along the centerline that is between 60% and 65% of the maximum distance along the centerline. The plurality of blades is organized in repeating sets of blades arranged around the compressor wheel, each repeating set including at least one full-blade and at least one half-blade.

First claim

We claim:

1. A turbocharger for use with an internal combustion engine, comprising:
a turbine housing surrounding a rotatable turbine wheel that is connected to a shaft;
a center housing that includes a bearing arrangement that rotatably supports the shaft, the shaft extending through the center housing;
a compressor housing surrounding an end of the shaft; and
a compressor wheel connected to the end of the shaft and being rotatably disposed within the compressor housing, the compressor wheel comprising:
a central hub having a centerline, a root portion and an end portion, the root portion being adjacent a connection interface of the central hub to a shaft;
a plurality of blades formed around the central hub, the plurality of blades including a group of full-blades extending from the root portion of the central hub up to a maximum distance from the root portion along the centerline, the maximum distance being adjacent the end portion of the central hub;
wherein the plurality of blades further includes a group of half-blades, the half-blades extending from the root portion of the hub to an area along the centerline that is between 55% and 70% of the maximum distance along the centerline;
wherein the plurality of blades further includes a group of partial-blades;
wherein the plurality of blades is organized in repeating sets of blades arranged around the compressor wheel, each repeating set including one half-blade that is immediately followed by one full-blade with respect to a particular radial location relative to a rotation of the compressor wheel; and
wherein one partial-blade is disposed immediately adjacent each repeating set.

2. The turbocharger of claim 1 , wherein the central hub has a generally circular cross section at a varying diameter, which diameter decreases non-linearly in a direction from the root portion towards the end portion.

3. The turbocharger of claim 1 , wherein each full-blade and each half-blade operates to redirect air radially outward with respect to the centerline and around the root portion when the compressor wheel is operating within the compressor housing.

4. The turbocharger of claim 3 , wherein each half-blade operates to split an air stream that moves along and is impelled by an adjacent full-blade.

5. The turbocharger of claim 1 , wherein each full-blade includes a first leading edge disposed close to the end portion.

6. The turbocharger of claim 5 , wherein the first leading edge of each full-blade is swept back towards the root portion.

7. The turbocharger of claim 6 , wherein the first leading edge of each full-blade extends at an acute angle, α, with respect to an axis that is perpendicular to the centerline.

8. The turbocharger of claim 7 , wherein the angle, α, is about 9.5 degrees.

9. The turbocharger of claim 5 , wherein each full-blade forms a first tip at a radially outer end of the respective first leading edge.

10. The turbocharger of claim 9 , wherein the first tips of the full-blades are axially aligned relative to the centerline and disposed at a first distance, X1, with respect to a root diameter of the central hub, and wherein the first distance is the maximum distance.

11. The turbocharger of claim 10 , wherein each of the half-blades includes a second leading edge that forms a second tip.

12. The turbocharger of claim 11 , wherein the second tips are axially aligned relative to the centerline and disposed at a second distance, X2, with respect to the root diameter of the central hub.

13. The turbocharger of claim 12 , wherein the group of partial-blades extends from the root portion of the central hub up to a partial-blade area along the centerline that is between 40% and 55% of the maximum distance along the centerline.

14. The turbocharger of claim 13 , wherein each partial-blade includes a leading edge and a tip, the tips of the partial-blades being axially aligned relative to the centerline and disposed at a third distance, X3, with respect to the root diameter of the central hub.

15. The turbocharger of claim 14 , wherein X2≈0.62*X1.

16. The turbocharger of claim 14 , wherein X3≈0.46*X1.

17. The turbocharger of claim 14 , wherein X3 is ≈0.73*X2.

18. The turbocharger of claim 13 , wherein as the compressor wheel is rotating during operation, at a particular radial orientation relative to the root portion of the compressor wheel, a partial-blade passing by the particular radial orientation is followed by a half-blade and then by a full-blade.

19. The turbocharger of claim 13 , wherein the half-blade has a half-blade leading edge, and the partial-blade has a partial-blade leading edge, and wherein as the compressor wheel is rotating during operation, at a particular radial orientation relative to the rotation of the compressor wheel, the first leading edge passing by the particular radial orientation is followed by a partial-blade leading edge and then by a half-blade leading edge.

20. The turbocharger of claim 13 , wherein the plurality of blades consists of six full-blades, six half-blades and six partial-blades.

Assignees

• Caterpillar Inc

Inventors

• Annati Richard E
• Reinhart Eric
• Singer Daniel

Classifications

• F01D5/048

  Form or construction · CPC title

• F02B37/00

  Engines characterised by provision of pumps driven at least for part of the time by exhaust · CPC title

• F05D2220/40

  in turbochargers · CPC title

• F04D29/30 Primary

  Vanes · CPC title

• F05D2240/303

  related to the leading edge of a rotor blade · CPC title