Turbocharger

• US 8,485,779 B2
• Filed: 11/12/2008
• Issued: 07/16/2013
• Est. Priority Date: 12/12/2007
• Status: Active Grant

• Current Assignee: IHI Corporation
• Original Assignee: IHI Corporation
• Inventors: Matsuyama, Yoshimitsu
• Primary Examiner(s): Look, Edward
• Assistant Examiner(s): Flores, Juan G
• Application Number:
  US12/743,966
• Publication Number:
  US 20100247296A1
• Time in Patent Office: 1,707 Days
• Field of Search: 415/159, 415/160, 415163-165
• US Class Current: 415/164
• 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: 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

A sealing device for prevention of exhaust gas in a scroll passage from leaking via a gap to a turbine impeller is arranged upstream, in a travel direction of the exhaust gas, of through-holes via which the vane shafts extend through a rear exhaust introduction wall, whereby pressure in a gap communicating with the through-holes of the rear wall is kept lower than pressure in an exhaust nozzle so as to displace nozzle vanes to the rear wall.

Claims

1. A turbocharger comprising:

a turbine housing having a scroll passage outwardly of an exhaust nozzle which is arranged outwardly of a turbine impeller rotatably supported on a bearing housing and guides exhaust gas from the scroll passage to the turbine impeller, said exhaust nozzle having a plurality of nozzle vanes between front and rear exhaust introduction walls on sides of the bearing and turbine housings, respectively, vane shafts fixed to opposite sides of each of said nozzle vanes extending through the front and rear walls and being rotatably supported, the rear wall being arranged to have a gap between said rear wall and the turbine housing, through-holes of the rear wall communicating with said gap,

wherein a sealing device for preventing the exhaust gas from said scroll passage from leaking via said gap to the turbine impeller is arranged upstream, in a travel direction of the exhaust gas, of the through-holes via which the vane shafts extend through the rear wall, whereby pressure in said gap communicating with said through-holes of the rear wall is kept lower than pressure in the exhaust nozzle and the exhaust gas in the exhaust nozzle flows through the through-holes into the gap so as to displace the nozzle vanes to the rear wall.

2. The turbocharger as claimed in claim 1, wherein a portion of each of the vane shafts extending through the rear wall which is fixed to a corresponding nozzle vane is formed with a flange shrouding a corresponding through-hole.

3. The turbocharger as claimed in claim 1, wherein the turbine housing presents a portion confronting a vertical surface of the rear wall such that the gap is provided therebetween, an outer periphery of the portion is cut out to provide a step comprising a vertical opposed surface which is substantially parallel to a rear surface of the rear wall, and a disc spring seal is fitted between the step and the rear surface of the rear wall.

4. The turbocharger as claimed in claim 3, wherein the disc spring seal is ring-shaped, and has a vertical rectilinear portion contiguous with an inner peripheral end and pressed against the vertical surface of the step, a slant portion extending slantingly from the rectilinear portion toward the rear wall, and a curved portion peripherally of the slant portion and curved in a direction away from the rear wall.

5. The turbocharger as claimed in claim 4, wherein the inner peripheral end of the disc spring seal is curved from the rectilinear portion in a direction approaching to the rear wall and extending vertically and inwardly into substantially S-shape.

6. The turbocharger as claimed in claim 3, wherein the disc spring seal is frustoconical, and inner and outer peripheral edges of the disc spring seal are mutually offset with respect to an axis of the spring.

7. The turbocharger as claimed in claim 6, wherein an axial height of the disc spring seal between the rectilinear portion of the curved portion is greater than a distance between the opposed surface and the rear surface of the rear wall.

8. The turbocharger as claimed in claim 3, wherein the step further comprises an annular tapered surface, diameters of which being decreased in a direction away from the rear wall.

9. The turbocharger as claimed in claim 3, wherein the step further comprises a cylindrical surface parallel with an axis of a turbine shaft.

10. The turbocharger as claimed in claim 9, wherein the disc spring seal is substantially ring-shaped and circumferentially cut out partly, the disc spring seal presents an inner peripheral end curved in a direction away from the rear wall and fitted on the cylindrical surface, and an outer peripheral end formed with a curved portion abutting the rear surface of the rear wall, and the disc spring seal is frustoconical with increased diameters from the inner peripheral end toward the rear wall.

11. The turbocharger as claimed in claim 1, wherein the turbine housing presents an extension extending into a position spaced apart from an outer periphery of the rear wall, and sealing rings are arranged between the extension and the outer periphery of the rear wall.

12. The turbocharger as claimed in claim 11, where a groove is provided in the extension, and the sealing rings are fitted in the groove.