# US 11,028,767 B2 · Variable geometry turbocharger

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- Number: US 11,028,767 B2
- Document ID: US11028767B2
- Status: Granted
- Kind: B2
- Application number: 16/087,907
- Filed: 2016-03-28
- Published: 2020-07-23
- Granted: 2021-06-08
- Earliest claimed: 2016-03-28
- Assignees: Mitsubishi Heavy Industries Engine & Turbocharger, Ltd.
- Applicants: Mitsubishi Heavy Industries Engine & Turbocharger, Ltd.
- Inventors: Keigo Sakamoto; Yosuke Dammoto; Eigo Katou; Yoji Akiyama; Nariaki Seike; Toyotaka Yoshida; Takeru Chiba
- Web page: https://patentgrep.com/patent/US11028767B2

## CPC

- F02B 37/24: by using pumps or turbines with adjustable guide vanes
- F02B 39/00: Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
- F02C 6/12: Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
- F04D 27/002: {by varying geometry within the pumps, e.g. by adjusting vanes}
- 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)}
- F01D 25/145: {Thermally insulated casings}
- F01D 25/243: {Flange connections; Bolting arrangements (F01D25/265 takes precedence)}
- F02B 37/186: {Arrangements of actuators or linkage for bypass valves}
- F02B 37/22: by varying cross-section of exhaust passages or air passages {, e.g. by throttling turbine inlets or outlets or by varying effective number of guide conduits} (F02B37/24 takes precedence)
- F05D 2220/40: in turbochargers
- F05D 2260/231: Preventing heat transfer
- F05D 2300/5024: Heat conductivity
- Y02T 10/12: Improving ICE efficiencies
- F02B: INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL (gas-turbine plants F02C; hot-gas or combustion-product positive-displacement engine plants F02G)
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02)
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

A variable geometry turbocharger (100) includes a bearing housing (10) including a bearing-housing side support portion (40) configured to support a radially outer portion (38) of a nozzle mount (16) from a side opposite to a scroll flow passage (4) in an axial direction of a turbine rotor (2), and wherein at least one of the following condition (a) or (b) is satisfied: (a) the bearing-housing side support portion (40) includes at least one bearing-housing side recess portion (46) formed so as to be recessed in the axial direction so as not to be in contact with the radially outer portion (38); (b) the radially outer portion (38) of the nozzle mount (16) includes at least one nozzle-mount side recess portion (62) formed so as to be recessed in the axial direction so as not to be in contact with the bearing-housing side support portion (40).

## Claims

### Claim 1

A variable geometry turbocharger, comprising:
a turbine rotor;
a turbine housing which accommodates the turbine rotor and which forms a scroll flow passage on a radially outer side of the turbine rotor;
a bearing housing accommodating a bearing which rotatably supports the turbine rotor, the bearing housing being coupled to the turbine housing; and
a variable nozzle mechanism for adjusting a flow of exhaust gas to the turbine rotor from the scroll flow passage,
wherein the variable nozzle mechanism includes:
a nozzle vane disposed in an exhaust gas flow passage for guiding the exhaust gas from the scroll flow passage to the turbine rotor;
a nozzle mount having an annular shape and supporting the nozzle vane rotatably, the nozzle mount forming a flow passage wall on a bearing-housing side of the exhaust gas flow passage; and
a nozzle plate having an annular shape and being disposed so as to face the nozzle mount, the nozzle plate forming a flow passage wall, of the exhaust gas flow passage,
a plurality of bolts disposed at intervals in a circumferential direction of the turbine rotor and configured to fasten the turbine housing and the bearing housing in the axial direction,
wherein the bearing housing includes a bearing-housing side support portion configured to support a radially outer portion of the nozzle mount from a side opposite to the scroll flow passage in an axial direction of the turbine rotor,
wherein the bearing-housing side support portion includes at least one bearing-housing side recess portion formed so as to be recessed toward a side opposite to the nozzle mount in the axial direction,
wherein the at least one bearing-housing side recess portion includes a plurality of bearing-housing side recess portions disposed at intervals in a circumferential direction of the turbine rotor, and
wherein the bearing-housing side recess portion is formed in an angular range which does not overlap with a center position of a bolt adjacent to the bearing-housing side recess portion, of the plurality of bolts, in the circumferential direction.

### Claim 2 (depends on 1)

The variable geometry turbocharger according to claim 1,
wherein the bearing-housing side recess portion is formed to be 5 degrees or more apart from the center position of the bolt adjacent to the bearing-housing side recess portion, of the plurality of bolts, in the circumferential direction.

### Claim 3 (depends on 1)

The variable geometry turbocharger according to claim 1,
wherein the turbine housing includes a turbine-housing side support portion configured to support the radially outer portion of the nozzle mount from a side opposite to the bearing-housing side support portion in the axial direction,
wherein the nozzle mount is nipped by the turbine-housing side support portion and the bearing-housing side support portion, and
wherein the turbine-housing side support portion is disposed so as to protrude toward an inner side of the bearing-housing side support portion in a radial direction of the turbine rotor, along a surface of the nozzle mount.

### Claim 4 (depends on 3)

The variable geometry turbocharger according to claim 3,
wherein the turbine-housing side support portion includes a contact portion to be in contact with the radially outer portion of the nozzle mount, and a non-contact portion formed on an inner side of the contact portion in the radial direction, the non-contact portion facing the nozzle mount via a gap.

### Claim 5 (depends on 3)

The variable geometry turbocharger according to claim 3,
wherein an expression 0≤(r1-r3)/(r2-r3)≤0.75 is satisfied, where r1 is a distance between a radially inner end of the turbine-housing side support portion and a rotational axis of the turbine rotor, r2 is a distance between a radially outer end of the nozzle mount and the rotational axis, and r3 is a distance between a radially outer end of the nozzle plate and the rotational axis.

### Claim 6 (depends on 5)

The variable geometry turbocharger according to claim 5,
wherein an expression 0≤(r1-r3)/(r2-r3)≤0.30 is satisfied.

### Claim 7 (depends on 1)

The variable geometry turbocharger according to claim 1, further comprising:
a heat shield member disposed between the bearing-housing side support portion and the nozzle mount.

### Claim 8 (depends on 7)

The variable geometry turbocharger according to claim 7,
wherein the heat shield member has a lower thermal conductivity than each of a thermal conductivity of the bearing housing and a thermal conductivity of the nozzle mount.

### Claim 9 (depends on 7)

The variable geometry turbocharger according to claim 7,
wherein the heat shield member is formed of austenitic stainless steel or nickel-based alloy.

### Claim 10 (depends on 7)

The variable geometry turbocharger according to claim 7,
wherein the heat shield member comprises a ring-shaped heat-shield plate disposed so that the bearing-housing side support portion and the nozzle mount do not make contact with each other over an entire angular range in a circumferential direction of the turbine rotor.

### Claim 11 (depends on 7)

The variable geometry turbocharger according to claim 7,
wherein the heat shield member comprises a coating applied to the radially outer portion of the bearing-housing side support portion or the nozzle mount.