Garrett Transportation I Inc.

Honeywell International Inc.

Matthew S Oakes

Ashraf Mohamed

Filip Eckl

Kevin Slupski

Dennis L Brookshire

George Adeff

Michael A Moyer

Christopher Arthur Carvalho

Charles Robert Cadle

Kolja Nikolic

Kevin Zhang

Chris Meade

Turbochargers for use in an engine having an internal combustion engine. The design includes, in examples, a shaft having a rotation axis, a turbine housing, a compressor housing, a center housing extending from the turbine housing to the compressor housing with the shaft therethrough, a turbine wheel disposed in the turbine housing and operatively connected to the shaft, and a compressor wheel disposed in the compressor housing and operatively connected to the shaft. A turbine backplate structure is provided having one or more grooves adjacent a back side of the turbine wheel. The turbine backplate structure may be formed on the central housing, or may be a separate backplate installed in the central housing.

Spiral grooved thrust generator on turbine wheel back plate

Turbine assemblies and related turbocharger systems having direct turbine interfaces are provided. One exemplary turbine assembly includes a first turbine housing having an outlet portion defining a fluid outlet of a first turbine and a second turbine housing having an inlet portion defining a fluid inlet of a second turbine, wherein at least a portion of the inlet portion radially surrounds at least a portion of the outlet portion to provide a direct interface from the fluid outlet of the first turbine to the fluid inlet of the second turbine in an axial direction.

Turbocharger systems with direct turbine interfaces

A variable geometry turbocharger assembly comprises a unison ring which rotates about a longitudinal axis defined by a shaft on which a turbine wheel and compressor wheel are attached in order to pivot a plurality of vanes and thereby control a flow of exhaust gas to the turbine wheel. The unison ring rotates on at least one guide pin which is secured to the turbocharger. The guide pins may be press-fit into apertures in a center housing at an outer pilot surface. In other embodiments the guide pins may be press-fit into a different part of the turbocharger such as a nozzle ring. The guide pins may each have a wear surface which defines a circumferential radius of curvature which is substantially equal to a circumferential radius of curvature of a radially inner surface of the unison ring.

Variable geometry turbocharger with guide pins

Growing community of inventors

Torrance, CA, United States of America

Matthew S Oakes