IMPELLER FOR A FLUID ENERGY MACHINE

• US 20150125302A1
• Filed: 01/01/2015
• Published: 05/07/2015
• Est. Priority Date: 07/26/2012
• Status: Active Grant

• Current Assignee: IHI Charging Systems International GmbH (IHI Corporation)
• Original Assignee: IHI Charging Systems International GmbH (IHI Corporation)
• Inventors: ROBERTO, DE SANTIS, JUST, DANIEL
• Granted Patent: US 9,951,787 B2
• Time in Patent Office: Days
• US Class Current: 416/183
• CPC Class Codes: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147
• CPC Class Codes: F01D 5/143 Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
• CPC Class Codes: F04D 17/00 Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps F04D21/00 takes precedence
• CPC Class Codes: F04D 29/284 for compressors
• CPC Class Codes: F05D 2250/90 Variable geometry

Abstract

In an impeller for a fluid energy machine with a hub and a plurality of rotor blades which are mounted on the hub and around which a medium may flow through the fluid energy machine and which form a blade duct between two neighboring rotor blades with a blade duct length which extends in the axial direction of the impeller, wherein each rotor blade is connected to the hub via a first transition region with a first curvature and via a second transition region with a second curvature and with a straight conical blade duct bottom of the blade duct formed between the first transition region and the second transition region.

Claims

1. An impeller for a fluid energy machine, with a hub (2) having an axis of rotation (D) and a plurality of rotor blades (3) which are provided on the hub (2) and around which a medium flowing through the fluid energy machine may flow and wherein a blade duct (12) is formed between two neighboring rotor blades (3) with a blade duct length (SL) which extends in the axial direction of the impeller (1), each rotor blade (3) being connected with the hub (2) via a first transition region (6) with a first curvature (K1) and via a second transition region (7) with a second curvature (K2), the impeller having a blade duct bottom (13) of the blade duct (12) between the first transition region (6) and the second transition region (7) which is at least in sections formed with different rates of inclination with respect to the axis D of the hub (2).

2. The impeller according to claim 1, wherein the blade duct bottom (13) is/to extend at least partially/formed to extend axially along an essentially straight line, defining a surface (F) inclined relative to a hub tangent plane (NT) and including an angle (α

) with the hub tangent plane (NT), wherein a section line (S) between the surface (F) and the hub tangent plane (NT) defines a total length (GL) of the surface (F) which extends in the circumferential direction of the hub (2).

3. The impeller according to claim 2, wherein, with the impeller (1) configured in the form of a compressor wheel, the angle (α

) at the wheel exit (11), or with the impeller (1) configured in the form of a turbine wheel, the angle (α

) at the wheel entrance exhibits a value ranging between 0.5° and

10°

.

4. The impeller according to claim 2, wherein with the impeller (1) configured in the form of a compressor wheel, the total length (GL) of the surface (F) at least at the wheel exit (11), or with the impeller (1) is configured in the form of a turbine wheel, the total length (GL) of the surface (F) at least at the wheel entrance exhibits a value ranging between 1 mm and half of the distance between two neighboring rotor blades (3).

5. The impeller according to one of claim 2, wherein the total length (GL) of the surface (F) is formed continuously decreasing in the direction of the wheel entrance if the impeller (1) is configured in the form of a compressor wheel, or if the impeller (1) is configured in the form of a turbine wheel, is formed continuously decreasing in the direction of the wheel exit (11).

6. The impeller according to claim 5, wherein the total length (GL) has a value of 0 mm at approx. 35% of the total length of the rotor blade (3) if the impeller (1) is configured in the form of a compressor wheel starting from the wheel exit (11) in the direction of the wheel entrance or, if the impeller (1) is configured in the form of a turbine wheel starting from the wheel entrance in the direction of the wheel exit (11).

7. The impeller according to claim 2, wherein the angle (α

) is continuously decreasing if the impeller (1) is configured in the form of a compressor wheel starting from the wheel exit (11) in the direction of the wheel entrance or if the impeller (1) is configured in the form of a turbine wheel starting from the wheel entrance in the direction of the wheel exit (11).

8. The impeller according to claim 2, wherein the angle (α

) at approx. 35% of the total length of the rotor blade (3) has a value of 0°

if the impeller (1) is configured in the form of a compressor wheel starting from the wheel exit (11) in the direction of the wheel entrance or if the impeller (1) is configured in the form of a turbine wheel starting from the wheel entrance in the direction of the wheel exit (11).

9. The impeller according to claim 1, wherein the first transition region (6) is formed different from the second transition region (7).

10. The impeller according to one of the previous claims, wherein

the impeller (1) is essentially made from an aluminum alloy.