Turbocharger having a nozzle ring centered by a guiding projection

• US 10,677,099 B2
• Filed: 10/23/2017
• Issued: 06/09/2020
• Est. Priority Date: 12/21/2016
• Status: Active Grant

• Current Assignee: MAN Energy Solutions SE (Volkswagen AG)
• Original Assignee: MAN Energy Solutions SE (Volkswagen AG)
• Inventors: Hossbach, Bjorn
• Primary Examiner(s): Nguyen, Ninh H.
• Assistant Examiner(s): Haghighian, Behnoush
• Application Number:
  US15/790,783
• Publication Number:
  US 20180171825A1
• Time in Patent Office: 960 Days
• CPC Class Codes: F01D 11/005 Sealing means between non relatively rotating elements
• 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: 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: F01D 25/246 Fastening of diaphragms or stator-rings
• CPC Class Codes: F02B 37/24 by using pumps or turbines with adjustable guide vanes
• CPC Class Codes: F02C 6/12 Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
• CPC Class Codes: F02C 7/28 Arrangement of seals
• CPC Class Codes: F05D 2220/40 in turbochargers
• CPC Class Codes: F05D 2230/53 by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
• CPC Class Codes: F05D 2230/64 using positioning or alignment devices for aligning or centring, e.g. pins

Abstract

A turbocharger (1), having a turbine (2) for expanding a first medium, having a compressor (3) for compressing a second medium utilizing energy extracted in the turbine (2) during the expansion of the first medium, wherein the turbine (2) has a turbine housing (4) and a turbine rotor (5). The compressor (3) has a compressor housing (6) and a compressor rotor (7) that is coupled to the turbine rotor (5) via a shaft (8). The turbine housing (4) and the compressor housing (6) are each connected to a bearing housing (9) arranged there between, in which the shaft (8) is mounted. The turbine housing (4) has an inflow housing (11), a nozzle ring (15) with guide blades (16) and an insert piece (13). The nozzle ring (15) is centered and radially guided by a projection (17) on the bearing housing (9).

Claims

1. A turbocharger comprising:

a turbine configured for expanding a first medium, the turbine comprising;

a turbine housing; and

a turbine rotor rotatably mounted within the turbine housing,

wherein the turbine housing comprises;

an inflow housing;

a nozzle ring mounted within the inflow housing and having guide blades for controlling flow of the first medium from the turbine rotor;

an axially extending stepped projection arranged on the nozzle ring; and

an insert piece that delimits a flow duct of the inflow housing;

a shaft;

a compressor configured for compressing a second medium utilizing energy extracted in the turbine during the expansion of the first medium, the compressor comprising;

a compressor housing; and

a compressor rotor rotatably mounted within the compressor housing, the compressor rotor being coupled to the turbine rotor by the shaft; and

a bearing housing positioned between, and connected to, the turbine housing and the compressor housing, the shaft being mounted within the bearing housing, the bearing housing having an axially groove having a radially extending step,

wherein the nozzle ring is centered about the shaft and radially guided onto the bearing housing by the stepped projection that mates with the stepped axial groove of the bearing housing.

2. The turbocharger of claim 1, wherein the axially extending projection of the nozzle ring engages the axially extending groove.

3. The turbocharger of claim 1, wherein the nozzle ring further comprises a first cover ring and a second cover ring, wherein the guide blades of the nozzle ring are positioned between the first cover ring and the second cover ring.

4. The turbocharger of claim 3, wherein the projection is formed on the first cover ring.

5. The turbocharger of claim 1, wherein the nozzle ring and the insert piece are embodied integrally.

6. The turbocharger of claim 1, wherein the nozzle ring and the insert piece are embodied as monolithic assembly.

7. The turbocharger of claim 1, further comprising spring elements positioned to act on a section of the inflow housing and on a section of the insert piece so as to push the insert piece and the nozzle ring toward the bearing housing.

8. The turbocharger of claim 7, wherein the spring elements position the insert piece and the nozzle ring axially relative to the shaft.

9. The turbocharger of claim 1, further comprising a sealing element positioned between the inflow housing and the insert piece.

10. The turbocharger of claim 1, wherein the axial groove is defined by two axially extending walls at its radial edges and two radially extending walls that are joined by an axially extending wall therebetween.