Variable nozzle unit and variable geometry system turbocharger

Patent metadata

Field	Value
Publication number	US-2016245160-A1
Application number	US-201615144015-A
Country	US
Kind code	A1
Filing date	May 2, 2016
Priority date	Jan 29, 2014
Publication date	Aug 25, 2016
Grant date	—

Abstract

A second nozzle shaft of each variable nozzle has an outer diameter smaller than that of a first nozzle shaft. The first nozzle shaft is integrally formed on one side surface of each variable nozzle. A portion is provided on the other side surface of each variable nozzle. The portion encloses the second nozzle shaft, and can contact a second nozzle ring. An inner nozzle flange and an outer nozzle flange which can contact a first nozzle ring are integrally formed on baes sides of the first nozzle shaft on a blade surface and a blade surface of each variable nozzle, respectively.

First claim

What is claimed is:

1 . A variable nozzle unit disposed between a turbine scroll passage and a turbine wheel in a turbine housing of a variable geometry system turbocharger, and configured to adjust a passage area of an exhaust gas to be supplied to the turbine wheel side, comprising:
a first nozzle ring disposed in the turbine housing and having a plurality of first supporting holes formed at intervals in a circumferential direction; a second nozzle ring provided integrally with the first nozzle ring at a location axially spaced apart from and opposite to the first nozzle ring, and having a plurality of second supporting holes formed so as to match the plurality of first supporting holes of the first nozzle ring; a plurality of variable nozzles disposed at intervals in the circumferential direction and between the first nozzle ring and the second nozzle ring, the variable nozzles being capable of rotating in a forward or reverse direction about a shaft center parallel to a shaft center of the turbine wheel, and each variable nozzle having a first nozzle shaft and a second nozzle shaft, the first nozzle shaft being integrally formed on one side surface and rotatably supported with the corresponding first supporting hole of the first nozzle ring, and the second nozzle shaft being integrally formed on the other side surface and rotatably supported with the corresponding second supporting hole of the second nozzle ring; and a link mechanism configured to synchronously rotate the plurality of variable nozzles in the forward or reverse direction, wherein an outer diameter of one nozzle shaft of the first nozzle shaft and the second nozzle shaft of each variable nozzle is smaller than an outer diameter of the other nozzle shaft, wherein a portion enclosing the one nozzle shaft on one of the one side surface and the other side surface of each of the variable nozzles is configured to be capable of contacting with one nozzle ring of the first nozzle ring and the second nozzle ring, and wherein a nozzle flange is integrally formed on a base side of the other nozzle shaft on a blade surface of each of the variable nozzles so that the nozzle flange can contact the other nozzle ring.

2 . The variable nozzle unit according to claim 1 , wherein
the second nozzle ring is located on a side further away from a bearing housing of the variable geometry system turbocharger than the first nozzle ring, the one nozzle shaft is the second nozzle shaft, the other nozzle shaft is the first nozzle shaft, the one nozzle ring is the second nozzle ring, and the other nozzle ring is the first nozzle ring.

3 . The variable nozzle unit according to claim 1 , wherein
the first nozzle ring includes a facing surface to the second nozzle ring, an opposite surface side of the facing surface of the first nozzle ring communicates with the turbine scroll passage, each of the first supporting holes of the first nozzle ring is bottomless, and each of the second supporting holes of the second nozzle ring is bottomed.

4 . The variable nozzle unit according to claim 2 , wherein
the first nozzle ring includes a facing surface to the second nozzle ring, an opposite surface side of the facing surface of the first nozzle ring communicates with the turbine scroll passage, each of the first supporting holes of the first nozzle ring is bottomless, and each of the second supporting holes of the second nozzle ring is bottomed.

5 . A variable geometry system turbocharger that uses energy of an exhaust gas from an engine to supercharge air to be supplied to the engine side, the variable geometry system turbocharger comprising a variable nozzle unit according to claim 1 .

Assignees

• Ihi Corp

Inventors

• Ueda Takafumi
• Iwakami Akira
• Takahashi Yukio

Classifications

• Y02T10/12

  Improving ICE efficiencies · CPC title

• F02B37/24 Primary

  by using pumps or turbines with adjustable guide vanes · CPC title

• F05D2220/40

  in turbochargers · CPC title

• F01D17/165

  for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line (F01D17/167 takes precedence) · CPC title