# US 2019/0170156 A1 · Radial Compressor

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- Number: US 2019/0170156 A1
- Document ID: US20190170156A1
- Status: Published application
- Kind: A1
- Application number: 16/203,419
- Filed: 2018-11-28
- Published: 2019-06-06
- Earliest claimed: 2017-12-01
- Assignees: MAN Energy Solutions SE
- Applicants: Man Energy Solutions SE
- Inventors: Hannes Benetschik; Sebastian Spengler; Matthias STRAUSS
- Web page: https://patentgrep.com/patent/US20190170156A1

## CPC

- F04D 29/4233: {with volutes extending mainly in axial or radially inward direction}
- F02C 6/12: Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
- F04D 17/10: for compressing or evacuating
- F04D 29/4213: {suction ports}
- F04D 29/667: {by influencing the flow pattern, e.g. suppression of turbulence}
- F04D 29/685: {Inducing localised fluid recirculation in the stator-rotor interface}
- F05D 2220/40: in turbochargers
- F05D 2240/90: Mounting on supporting structures or systems
- F05D 2250/71: curved
- F05D 2260/96: Preventing, counteracting or reducing vibration or noise
- F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02)
- 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)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

A radial compressor of an exhaust gas turbocharger, with a rotating impeller, a fixed housing; a main flow passage defined by the housing for feeding a medium to be compressed towards the impeller; a secondary flow chamber arranged radially outside the main flow passage, which is separated from the main flow passage by a contour wall and is connected to the main flow passage via a secondary flow opening; struts extending in the secondary flow chamber, via which the contour wall is connected to the housing. The struts are curved having a first connecting section of the contour wall that extends in the radial direction and a second connecting section on the housing that extends in the axial direction.

## Claims

### Claim 1

A radial compressor, of an exhaust gas turbocharger, comprising:
An impeller configured to rotate;
fixed housing;
a main flow passage defined by the housing configured to feed a medium to be compressed in a direction of the impeller;
a contour wall;
a secondary flow chamber arranged radially outside the main flow passage, which is separated from the main flow passage by the contour wall and which in a region of the impeller is connected to the main flow passage via a secondary flow opening;
struts that extend in the secondary flow chamber, via which the contour wall is connected to the housing;
wherein the struts are curved such that as seen in a meridional section a first connection section of a respective strut on the contour wall extends in a radial direction or predominantly in the radial direction and a second connection section of the respective strut on the housing extends in an axial direction or predominantly in the axial direction.

### Claim 2 (depends on 1)

The radial compressor according to claim 1, wherein seen in the meridional section a longitudinal center axis of the first connection section includes with the radial direction an angle of at least one of:
maximally 20°;
maximally 10°; and
maximally 5°.

### Claim 3 (depends on 1)

The radial compressor according to claim 1, wherein seen in the meridional section a longitudinal center axis of the second connection section includes with the axial direction an angle of at least one of
maximally 20°;
maximally 10°; and
maximally 5°.

### Claim 4 (depends on 1)

The radial compressor according to claim 1, wherein in an axial section the first connection section and the second connection section of a respective strut are offset relative to one another in a circumferential direction.

### Claim 5 (depends on 2)

The radial compressor according to claim 2, wherein the angles, which seen in an axial section include respective adjacent struts, have a non-integral divisor to 360°.

### Claim 6 (depends on 1)

The radial compressor according to claim 1, wherein in an axial section the struts are unevenly distributed in a circumferential direction, such that in a circumferential section, which faces a tongue of a spiral housing, a lower number of struts is formed than on a circumferential section facing away from the tongue of the spiral housing.

### Claim 7 (depends on 1)

The radial compressor according to claim 1, wherein the housing comprises:
a suction section arranged, as seen in a flow direction of the medium to be compressed, upstream of the impeller;
an insert piece section extending in a region of the impeller; and
a spiral housing section arranged downstream of the impeller.

### Claim 8 (depends on 7)

The radial compressor according to claim 7, wherein at least the spiral housing section is formed as a separate assembly of the housing.

### Claim 9 (depends on 7)

The radial compressor according to claim 7, wherein the suction section and the insert piece section are formed as a separate assembly of the housing.

### Claim 10 (depends on 7)

The radial compressor according to claim 7, wherein the struts, with their second connecting sections, act on the suction section of the housing.

### Claim 11 (depends on 3)

The radial compressor according to claim 3, wherein the angles, which seen in the axial section include respective adjacent struts, have a non-integral divisor to 360°.