Turbine for an exhaust gas turbocharger

• US 9,664,193 B2
• Filed: 06/06/2014
• Issued: 05/30/2017
• Est. Priority Date: 12/08/2011
• Status: Active Grant

• Current Assignee: IHI Charging Systems International GmbH (IHI Corporation)
• Original Assignee: IHI Charging Systems International GmbH (IHI Corporation)
• Inventors: Hirth, Torsten, Guthoerle, Manfred, Mueller, Andreas, Schulz, Timo, Fledersbacher, Peter, Van Lil, Carsten
• Primary Examiner(s): Kim, Craig
• Assistant Examiner(s): Brockman, Eldon
• Application Number:
  US14/298,836
• Publication Number:
  US 20140294576A1
• Time in Patent Office: 1,089 Days
• CPC Class Codes: F01D 17/143 the shiftable member being a wall, or part thereof of a radial diffuser
• CPC Class Codes: F01D 17/16 by means of nozzle vanes
• CPC Class Codes: F04D 17/08 Centrifugal pumps
• CPC Class Codes: F05D 2220/40 in turbochargers

Abstract

In a turbine for an exhaust gas turbocharger with a turbine casing having a receiving chamber for accommodating a turbine wheel and at least one volute through which the exhaust gas is guided via a feed passage into the receiving chamber and wherein at least one guide element is provided in the turbine casing so as to project into the feed passage in a guide region for guiding the exhaust gas onto the turbine wheel, the guide element comprises a first length region in the axial direction of the turbine, in which the guide element is designed with respect to its aerodynamic properties differently from its aerodynamic design in a second length region adjoining the first length region.

Claims

1. A turbine (10) for an exhaust gas turbocharger with a turbine casing (12) defining a receiving chamber (14) accommodating turbine wheel (9) and at least one volute (4) by which exhaust gas is guided via a feed passage (5) into the receiving chamber (14), the turbine (10) including:

at least one guide vane element (1) arranged in the feed passage (5) fixed relative to the turbine casing (12) so as to project at least in a guide region (30) into the feed passage (5) for guiding the exhaust gas, and comprising a first length region (a) in the guide region (30) relative to the axial direction of the turbine (10), in which the guide vane element (1) has guide vanes (18) designed with a radial airfoil thickness greater than that of a second length region (d) adjoining, and extending axially further from, the first length region (a) in the guide region (30) of the guide vane element (1), with the second length region joining the first length region via a curved transition region (32), and a sliding sleeve element (2) arranged movably in the axial direction along the reduced thickness region of the vanes (18) of the vane element (1) between an open position which maximally opens a flow cross-section of the feed passage (5) in both length regions (a, d) and a closed position which maximally restricts and merely opens the flow cross-section in the first length region (a), the sliding sleeve element (2) having an axial front end which is curved corresponding to the curved transition region (32) of the guide vane element (1) so as to be accommodated thereby in its closed position whereby, upon movement of the sliding element (2) from the closed position effecting swirl generation in the first length (a) to the position any disturbance of the generation of swirling in the first length region (a) is at least mitigated.

2. The turbine (10) according to claim 1, wherein the length regions (a, d) are joined in the axial direction via the transition region (32) which comprises a contour which is at least partially one of circular arc-shaped and elliptical arc-shaped.

3. The turbine (10) according to claim 2, wherein the sliding element (2) comprises an end face (44) which has a second contour corresponding at least essentially to the arc-shaped transition region (32).

4. The turbine (10) according to claim 3, wherein the first contour and the second contour of the sliding element (2) are arranged at least essentially coinciding in the closed position.

5. The turbine (10) according to claim 1, wherein the guide region (30) of the guide vane element (1) extends over the full axial length of the feed passage (5), and a partition wall (46) of the turbine (10), which fluidly separates the volute (4) from a receiving chamber (7) for accommodating an adjusting mechanism of the sliding element (2) has an inner diameter (D_T) which is smaller than an inlet diameter (D_L) of the guide vane element (1), on which the exhaust gas enters the guide vane element (1).

6. The turbine (10) according to claim (1), wherein a reciprocal value (FB/FA) of the ratio (FA/FB) of a first profile area (FA) of the guide vanes (18) of the guide vane element (1), which extends at least essentially vertically to the axial direction and which is covered in the second length region (d) the closed position by the sliding element (2), to a second profile area (FB) of the guide vane element (1), which extends at least essentially vertically to the axial direction, and which in the closed position of the sliding element (2) is unblocked, is within a range of 10% to 75%.

7. The turbine (10) according to claim 1, wherein at least one dividing element (f) is provided by means of which the length regions (a, d) are fluidly separated from each other.

8. The turbine (10) according to claim 7, wherein the dividing element (1) is engaged in a corresponding groove (48) of the guide vane element (1).