Turbine exhaust seal

Patent metadata

Field	Value
Publication number	US-2016169018-A1
Application number	US-201414566541-A
Country	US
Kind code	A1
Filing date	Dec 10, 2014
Priority date	Dec 10, 2014
Publication date	Jun 16, 2016
Grant date	—

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 seal comprising:
a cylindrical portion that defines an opening having an axis wherein 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.

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 greater than 10 degrees.

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

5 . The turbine housing assembly seal of claim 1 wherein the sloped annular portion comprises a slope angle greater than 10 degrees and less than 20 degrees.

6 . 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.

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

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

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

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

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

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

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

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

15 . 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.

16 . The turbine housing assembly seal of claim 13 wherein the curved portion comprises a lower contact surface.

17 . A method comprising:
shaping a sheet of material to form a turbine housing assembly seal that comprises a cylindrical portion that defines an opening having an axis wherein 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.

18 . The method of claim 17 comprising loading the seal between a shroud component and a turbine housing to transition the seal from an uncompressed state to a compressed state and to form an upper seal interface and a lower seal interface.

19 . The method of claim 18 comprising, via the seal interfaces, hindering flow of exhaust from an exhaust volute defined at least in part by the turbine housing to a turbine wheel space that comprises a lower portion defined by the shroud component and an upper portion defined by the turbine housing wherein an axial gap exists between the lower portion and the upper portion of the turbine wheel space.

20 . The method of claim 19 wherein the cylindrical portion at least partially axially overlaps with the axial gap.

Assignees

• Honeywell Int 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

• 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

• F01D11/003 Primary

  by packing rings; Mechanical seals · CPC title