Exhaust gas turbocharger for an internal combustion engine

• US 5,454,225 A
• Filed: 09/07/1994
• Issued: 10/03/1995
• Est. Priority Date: 09/09/1993
• Status: Expired due to Fees

• Current Assignee: Mercedes-Benz AG (Mercedes-Benz Group AG)
• Original Assignee: Mercedes-Benz AG (Mercedes-Benz Group AG)
• Inventors: Sumser, Siegfried, Erdmann, Wolfgang, Schmidt, Erwin, Wunderlich, Klaus, Hanauer, Horst
• Primary Examiner(s): KOCZO JR, MICHAEL
• Application Number:
  US08/301,807
• Time in Patent Office: 391 Days
• Field of Search: 60/602, 415/116, 415/151, 415/166
• US Class Current: 60/602
• CPC Class Codes: F01D 17/165 for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line F01D17/167 takes precedence
• CPC Class Codes: F01D 17/167 of vanes moving in translation
• CPC Class Codes: F01D 9/045 for radial flow machines or engines
• CPC Class Codes: F02B 37/025 Multiple scrolls or multiple gas passages guiding the gas to the pump drive
• CPC Class Codes: F02B 37/24 by using pumps or turbines with adjustable guide vanes
• CPC Class Codes: F05D 2220/40 in turbochargers
• CPC Class Codes: Y02T 10/12 Improving ICE efficiencies

Abstract

In an exhaust gas turbocharger for an internal combustion engine comprising a compressor and an exhaust gas turbine mounted on a common shaft, the exhaust gas turbine includes a rotor with radial and semi-axial flow inlet areas and a single-flow duct surrounding the rotor and having port regions in the form of annular nozzle structures with guide vanes disposed adjacent each flow inlet area which are divided from one another by a ring of streamlined shape which is mounted to the guide vanes of one of the adjacent nozzle structures, said guide vanes having at least portions which are movable for adjusting the flow cross-section of the respective annular nozzle structures for controlling the flow through the radial and semi-axial flow inlet areas.

Claims

1. An exhaust gas turbocharger for an internal combustion engine comprising a compressor and an exhaust gas turbine mounted on a common shaft, said exhaust gas turbine including a rotor with radial and semi-axial flow inlet areas and a single-flow duct surrounding said rotor and having port regions in the form of annular nozzle structures disposed adjacent each flow inlet area of said rotor, and at least one variable guide vane structure with guide vanes arranged in said flow duct for controlling the effective flow cross-section of the annular nozzle structures, and a ring of streamlined shape disposed in said flow duct between said radial and semi-axial flow areas so as to divide the two areas and define said annular nozzles at opposite sides thereof, said ring being mounted on at least one of the guide vane structures of said radial and semi-axial annular flow areas.

2. A turbocharger according to claim 1, wherein said guide vane structures are each arranged between said streamlined ring and one of the side walls of said flow duct and are adjustable independently of one another.

3. A turbocharger according to claim 1, wherein said streamlined ring is divided concentrically to the axis of rotation of the rotor so as to provide two ring sections which are movable relative to one another.

4. A turbocharger according to claim 1, wherein said streamlined ring has an outer contour which is rotationally symmetrical in relation to the axis of rotation of the rotor.

5. A turbocharger according to claim 1, with a flow duct of spiral shape, wherein the cross-section of said streamlined ring is contoured so as to decrease in its axial and radial extent relative to the axis of rotation of the rotor along its circumference, in the direction of gas flow, and has a nose region projecting into the spiral flow duct.

6. A turbocharger according to claim 1, wherein said guide vane structures are divided, comprising a fixed guide vane structure part and a rotatable guide vane structure part arranged in said annular nozzles, at least one of the divided guide vane structures being adapted to vary the flow cross-section of one of the annular nozzles.

7. A turbocharger according to claim 1, wherein one of the guide vanes of the guide vane structures guiding the radial inflow to the rotor of and the guide vanes of the guide vane structure guiding the semi-axial inflow to the rotor are of one-piece design and designed to be pivotable about a vane longitudinal axis.

8. A turbocharger according to claim 1, wherein the guide vane structure is divided by two intersecting dividing surfaces, one dividing surface being the circumferential surface of a cylinder which extends concentrically to the axis of rotation of the rotor and the other dividing surface being the lateral surface of a cone, the associated cone tip of which lies on the axis of rotation of the rotor.

9. A turbocharger according to claim 1, wherein at least one of said annular nozzles is capable of being closed completely by the adjustable guide vane structure.

10. A turbocharger according to claim 1, wherein the ends of the divided guide vane structures adjacent the two flow inlet areas of the rotor are matched to the contour of a rotor periphery.

11. A turbocharger according to claim 1, wherein said streamlined ring is divided into two relatively rotatable parts, and also at least one of the adjacent vane structures is divided circumferentially into a first part connected to one of said relatively movable parts of said divided ring and a second part connected to the other part of said divided ring, and means are provided for rotating said one part of said ring with the vane structure part connected thereto relative to the other vane structure part for controlling the flow cross-section of said vane structure.