US 9,752,584 B2Granted

Compressor arrangement

AssigneeMAN Diesel & Turbo SE

InventorsKlaus Hörmeyer, Roland Emmrich, Bernhard Eisenberg, Dirk Anding, Henning Ressing

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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.

Claims5

Dependent claims

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.

3 more elements

Dependencies are inferred from the claim text.

Facts

Application: 14/495,501Filed 24 Sep 2014
Priority: DE 10 2013 015 99326 Sep 2013
Published: US 2015/0139788 A121 May 2015
Granted: 5 Sep 2017
Term ends: Not estimatedThe source records don’t support an estimate.

Classification8 codes

F04D 17/025
Having non-centrifugal stages, e.g. centripetal: comprising axial flow and radial flow stages
F01D 5/143
Of the blades of successive rotor or stator blade-rows: contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
F02C 3/08
Having a turbine driving a compressor: the compressor comprising at least one radial stage
F04D 29/666
Especially adapted for elastic fluid pumps: by means of rotor construction or layout, e.g. unequal distribution of blades or vanes

Family

US 2015/0139788 A1Pre-grant publication · published 21 May 2015
US 9,752,584 B2This patent

From the US filing history. Foreign family members aren’t listed.

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