Turbine hub with surface discontinuity and turbocharger incorporating the same

Patent metadata

Field	Value
Publication number	US-9896937-B2
Application number	US-201314395528-A
Country	US
Kind code	B2
Filing date	Apr 11, 2013
Priority date	Apr 23, 2012
Publication date	Feb 20, 2018
Grant date	Feb 20, 2018

Abstract

A turbocharger ( 5 ) comprising a housing ( 10 ) including a compressor shroud ( 14 ) and a turbine shroud ( 12 ). The turbocharger ( 5 ) also includes a compressor wheel ( 18 ) and a turbine wheel ( 116, 216, 316, 416 ). The compressor wheel ( 18 ) includes a compressor hub ( 44 ) and a plurality of circumferentially spaced compressor blades ( 45, 46 ) extending radially from the compressor hub ( 44 ). The turbine wheel ( 116, 216, 316, 416 ) includes a turbine hub ( 124, 224, 324, 424 ) and a plurality of circumferentially spaced blades ( 126, 226, 326, 426 ) extending radially from the turbine hub ( 124, 224, 324, 424 ) with a hub surface ( 125, 225, 325, 425 ) extending between adjacent blades ( 126, 226, 326, 426 ). The turbine wheel ( 116, 216, 316, 416 ) also includes at least one surface discontinuity ( 135, 235, 335, 435 ) on the turbine hub surface ( 125, 225, 325, 425 ).

First claim

What is claimed is:

1. A turbocharger ( 5 ), comprising:
a housing ( 10 ) including a compressor shroud ( 14 ) and a turbine shroud ( 12 );
a compressor wheel ( 18 ), including:
a compressor hub ( 44 ); and
a plurality of circumferentially spaced compressor blades ( 45 , 46 ) extending radially from the compressor hub ( 44 ); and

a turbine wheel ( 216 ), including:
a turbine hub ( 224 );
a plurality of circumferentially spaced blades ( 226 ) extending radially from the turbine hub ( 224 ) with a hub surface ( 225 ) extending between adjacent blades ( 226 ); and
at least one protruding surface discontinuity ( 235 ) on the turbine hub surface ( 225 ) and separated from the blades.

2. The turbocharger ( 5 ) according to claim 1 , wherein the surface discontinuity ( 235 ) is in the form of a plurality of protuberances.

3. A turbocharger turbine wheel ( 116 ), comprising:
a turbine hub ( 124 ), wherein the hub ( 124 ) includes at least one circumferentially extending surface discontinuity ( 135 ) extending around an entire circumference of the hub and operative to energize a boundary layer of a fluid flow (F) associated with the hub ( 124 ); and
a plurality of circumferentially spaced blades ( 126 ) extending radially from the hub ( 124 ).

4. The turbocharger turbine wheel ( 116 ) according to claim 3 , including a plurality of circumferentially extending surface discontinuities ( 135 ).

5. The turbocharger turbine wheel ( 116 ) according to claim 3 , wherein the circumferentially extending surface discontinuity ( 135 ) is in the form of a rib ( 135 ).

6. The turbocharger turbine wheel ( 116 ) according to claim 5 , including a plurality of circumferentially extending ribs ( 135 ).

7. A turbocharger turbine wheel ( 216 ), comprising:
a turbine hub ( 224 );
a plurality of circumferentially spaced blades ( 226 ) extending radially from the turbine hub ( 224 ) with a hub surface ( 225 ) extending between adjacent blades ( 226 ); and
at least one protruding surface discontinuity ( 235 ) on the turbine hub surface ( 225 ) and separate from the blades.

8. The turbocharger turbine wheel ( 216 ) according to claim 7 , wherein the surface discontinuity ( 235 ) is in the form of a protuberance ( 235 ).

Assignees

• Borgwarner Inc

Inventors

• Dextraze Stephanie

Classifications

• F01D5/145 Primary

  Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title

• F01D5/146

  of blades with tandem configuration, split blades or slotted blades · CPC title

• F04D29/30

  Vanes · CPC title

• F01D5/20

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title

• F04D29/685

  Inducing localised fluid recirculation in the stator-rotor interface · CPC title