Turbine exhaust seal

Patent metadata

Field	Value
Publication number	US-10550705-B2
Application number	US-201414566541-A
Country	US
Kind code	B2
Filing date	Dec 10, 2014
Priority date	Dec 10, 2014
Publication date	Feb 4, 2020
Grant date	Feb 4, 2020

Abstract

A turbine housing assembly seal can include a cylindrical portion that defines an opening having an axis where the cylindrical portion is disposed at a cylinder radius from the axis; a lower edge disposed at a lower edge radius that exceeds the cylinder radius; an sloped annular portion that extends radially inwardly from the lower edge; a lower bend that extends from the sloped annular portion to a lower axial position of the cylindrical portion; an upper bend that extends from an upper axial position of the cylindrical portion; and an upper edge that extends radially outwardly from the upper bend to an upper edge radius that exceeds the cylinder radius and that is less than the lower edge radius.

First claim

What is claimed is:

1. A turbine housing assembly comprising:
a shroud component that defines a rotational axis of a turbine wheel, wherein the shroud component comprises an annular wall that comprises a contoured turbine wheel side surface and an opposing shroud component volute side surface at a shroud component volute side surface radius;
a turbine housing that comprises an annular wall that comprises a turbine wheel side surface and an opposing turbine housing volute side surface at a turbine housing volute side surface radius; and
a turbine housing assembly seal that is disposed between and axially compressively pre-loaded by the turbine housing and the shroud component, wherein the turbine housing assembly seal comprises:
a cylindrical portion that defines an opening having an axis wherein the cylindrical portion is disposed at a cylinder radius from the axis that is greater than the shroud component volute side surface radius and that is greater than the turbine housing volute side surface radius and wherein the cylindrical portion faces the shroud component volute side surface and the turbine housing volute side surface;
a lower edge disposed at a lower edge radius that exceeds the cylinder radius;
a sloped annular portion that extends radially inwardly from the lower edge, wherein the sloped annular portion comprises a slope angle greater than 10 degrees;
a lower bend that extends from the sloped annular portion to a lower axial position of the cylindrical portion;
an upper bend that extends from an upper axial position of the cylindrical portion; and
an upper edge that extends radially outwardly from the upper bend to an upper edge radius that exceeds the cylinder radius and that is less than the lower edge radius.

2. The turbine housing assembly seal of claim 1 comprising an uncompressed axial height wherein an axial span of the cylindrical portion is greater than 25 percent of the uncompressed axial height.

3. The turbine housing assembly seal of claim 1 wherein the sloped annular portion comprises a slope angle less than 30 degrees.

4. The turbine housing assembly seal of claim 1 wherein the sloped annular portion comprises a slope angle less than 20 degrees.

5. The turbine housing assembly seal of claim 1 wherein the lower bend comprises a radius of curvature and wherein the upper bend comprises a radius of curvature.

6. The turbine housing assembly seal of claim 5 wherein the radius of curvature of the lower bend is approximately equal to the radius of curvature of the upper bend.

7. The turbine housing assembly seal of claim 1 wherein the cylindrical portion comprises a constant cylinder radius over an axial span.

8. The turbine housing assembly seal of claim 7 wherein, in a compressed state, the cylindrical portion comprises a constant cylinder radius over the axial span.

9. The turbine housing assembly seal of claim 1 wherein the seal comprises opposing surfaces separated by a material thickness.

10. The turbine housing assembly seal of claim 1 comprising metal.

11. The turbine housing assembly seal of claim 1 comprising an alloy.

12. The turbine housing assembly seal of claim 1 wherein the seal comprises a curved portion disposed between the upper bend and the upper edge.

13. The turbine housing assembly seal of claim 12 wherein the curved portion comprises an upper contact surface.

14. The turbine housing assembly seal of claim 1 wherein the seal comprises a curved portion disposed between the sloped annular portion and the lower edge.

15. The turbine housing assembly seal of claim 12 wherein the curved portion comprises a lower contact surface.

16. A turbine housing assembly seal comprising:
a cylindrical portion that defines an opening having an axis (z) wherein the cylindrical portion is disposed at a cylinder radius (r i ) from the axis (z) and comprises an axial span (Δz 3 );
a lower edge disposed at a lower edge radius (r L ) that exceeds the cylinder radius (r i );
an sloped annular portion that extends radially inwardly from the lower edge at a free-standing slope angle (α) greater than 10 degrees and less than 30 degrees that has an axial span (Δz 1 );
a lower bend that extends from the sloped annular portion to a lower axial position of the cylindrical portion and that comprises an axial span (Δz 2 );
an upper bend that extends from an upper axial position of the cylindrical portion; and
an upper edge that extends radially outwardly from the upper bend to define an axial span (Δz 4 ) wherein the upper edge has an upper edge radius (r u ) that exceeds the cylinder radius (r i ) and that is less than the lower edge radius (r L ), wherein a difference between the lower edge radius (r L ) and the cylinder radius (r i ) exceeds an axial height (Δz T ) defined by the sum of the axial spans (Δz 1 , Δz 2 , Δz 3 , Δz 4 ) to impart a substantially linear spring with a constant (k) that, responsive to axial compressive loading in an assembled state of the turbine housing assembly seal in a turbocharger assembly that pre-loads the turbine housing assembly seal, maintains the cylindrical portion at a substantially axial orientation while the slope angle (α) decreases.

Assignees

• Garrett Transportation I Inc

Inventors

• Solanki Shankar Pandurangasa
• Barthelet Pierre
• Gerard Arnaud
• Eumont Vincent
• Morand Nicolas
• Abel Francis

Classifications

• F01D11/005

  Sealing means between non relatively rotating elements · CPC title

• F05D2220/40

  in turbochargers · CPC title

• F01D11/003 Primary

  by packing rings; Mechanical seals · CPC title

• F01D1/22

  traversed by the working-fluid substantially radially · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title