# US 9,752,584 B2 · Compressor arrangement

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- Number: US 9,752,584 B2
- Document ID: US9752584B2
- Status: Granted
- Kind: B2
- Application number: 14/495,501
- Filed: 2014-09-24
- Published: 2015-05-21
- Granted: 2017-09-05
- Earliest claimed: 2013-09-26
- Assignees: MAN Diesel & Turbo SE
- Applicants: Klaus Hörmeyer; Roland Emmrich; Bernhard Eisenberg; Dirk Anding; Henning Ressing
- Inventors: Klaus Hörmeyer; Roland Emmrich; Bernhard Eisenberg; Dirk Anding; Henning Ressing
- Web page: https://patentgrep.com/patent/US9752584B2

## CPC

- F04D 17/025: {comprising axial flow and radial flow stages}
- F01D 5/143: {Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour}
- F02C 3/08: the compressor comprising at least one radial stage (F02C3/10 takes precedence)
- F04D 29/666: {by means of rotor construction or layout, e.g. unequal distribution of blades or vanes}
- F02C 3/14: characterised by the arrangement of the combustion chamber in the plant (combustion chambers per se F23R; F02C3/205 takes precedence)
- 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)
- 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)

## Abstract

A compressor arrangement has a common shaft, an axial compressor having at least a single-stage, and a radial compressor having at least single-stage. Assemblies of the, or each, axial compressor stage on the rotor side and assemblies of the, or each, radial compressor stage on the rotor side are attached to a common shaft (4). A ratio between a maximum diameter of the shaft (4) in the region of the axial compressor (2) and a minimum radial impeller seat diameter of the shaft (4) in the region of the radial compressor (3) is between 1.5 and 3.0.

## Claims

### Claim 1

A compressor arrangement (1), comprising:
an axial compressor (2) having at least one axial compressor stage;
a radial compressor (3) having at least one radial compressor stage; and
a common shaft (4) having a maximum diameter in a region of the axial compressor (2) and a minimum radial impeller seat diameter in a region of the radial compressor (3),
wherein the axial compressor stage on a rotor side and the radial compressor stage on the rotor side are attached to the common shaft (4), and
wherein a ratio between the maximum diameter of the shaft (4) in the region of the axial compressor (2) and the minimum radial impeller seat diameter of the shaft (4) in the region of the radial compressor (3) is between 1.5 and 3.0.

### Claim 2 (depends on 1)

The compressor arrangement according to claim 1, wherein the ratio between the maximum diameter of the shaft (4) in the region of the axial compressor (2) and the minimum radial impeller seat diameter of the shaft (4) in the region of the radial compressor (3) is between 1.8 and 3.0.

### Claim 3 (depends on 2)

The compressor arrangement according to claim 2, wherein the ratio between the maximum diameter of the shaft (4) in the region of the axial compressor (2) and the minimum radial impeller seat diameter of the shaft (4) in the region of the radial compressor (3) is between 2.0 and 3.0.

### Claim 4 (depends on 2)

The compressor arrangement according to claim 2, wherein the ratio between the maximum diameter of the shaft (4) in the region of the axial compressor (2) and the minimum radial impeller seat diameter of the shaft (4) in the region of the radial compressor (3) is between 1.8 and 2.5.

### Claim 5 (depends on 2)

The compressor arrangement according to claim 2, wherein the ratio between the maximum diameter of the shaft (4) in the region of the axial compressor (2) and the minimum radial impeller seat diameter of the shaft (4) in the region of the radial compressor (3) is between 2.0 and 2.5.