# US 10,119,402 B2 · Compressor wheel of a radial compressor of an exhaust-gas turbocharger

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- Number: US 10,119,402 B2
- Document ID: US10119402B2
- Status: Granted
- Kind: B2
- Application number: 14/441,912
- Filed: 2013-11-14
- Published: 2015-10-15
- Granted: 2018-11-06
- Earliest claimed: 2012-11-26
- Assignees: BorgWarner Inc.
- Applicants: BorgWarner Inc.
- Inventors: Alessio Scheri; Aleksandra Dimova; Thomas Lischer; Henning Scheel
- Web page: https://patentgrep.com/patent/US10119402B2

## CPC

- F01D 5/043: {of the axial inlet- radial outlet, or vice versa, type}
- F01D 5/048: {Form or construction}
- F01D 5/146: {of blades with tandem configuration, split blades or slotted blades}
- F02B 39/00: Component parts, details, or accessories relating to, driven charging or scavenging pumps, not provided for in groups F02B33/00 - F02B37/00
- F04D 29/284: {for compressors}
- F01D 5/045: {the wheel comprising two adjacent bladed wheel portions, e.g. with interengaging blades for damping vibrations}
- F04D 29/30: Vanes
- F05D 2220/40: in turbochargers
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F02B: INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL (gas-turbine plants F02C; hot-gas or combustion-product positive-displacement engine plants F02G)
- F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

A compressor wheel (1) of a radial compressor (2) of an exhaust-gas turbocharger (3), having a hub (8); and having two blade rows (9, 10) which are arranged adjacent to one another on the hub (8), a first blade row (9) forming the leading blade row, and the adjacent, second blade row (10) forming the trailing blade row, wherein the number of blades (11) of the first blade row (9) is equal to the number of blades (12) of the second blade row (10).

## Claims

### Claim 1

An exhaust-gas turbocharger (3) having a radial compressor (2) including a compressor wheel (1) having a hub (8); and two blade rows (9, 10) arranged on the hub (8) including an inducer blade row (9) comprising a plurality of inducer blades and an exit blade row (10) comprising a plurality of exit blades, the blade rows cooperating for inducting air in axially, accelerating it centrifugally, and discharging air radially outward, wherein the number of inducer blades (11) of the inducer blade row (9) is equal to the number of exit blades (12) of the exit blade row (10), each inducer blade (11) cooperating with an exit blade (12) to form a blade pair, wherein each inducer blade (11) of the blade pair and each exit blade (12) of the blade pair has a leading edge (13, 14), a trailing edge (15, 16), a pressure side and a suction side, wherein a spacing (D) is provided between the trailing edge (15) of the inducer blade (11) of the blade pair and the leading edge (14) of the exit blade (12) of the blade pair as viewed in the inflow direction (A), and the exit blade (12) of the blade pair is advanced in the direction of rotation relative to the inducer blade (11) of the blade pair, and wherein all air flowing through said spacing (D) flows from the pressure side of the inducer blades to the suction side of the exit blades.

### Claim 2 (depends on 1)

The exhaust-gas turbocharger as claimed in claim 1, wherein at least one splitter blade is provided.