High stiffness turbomachine impeller, turbomachine including said impeller and method of manufacturing

Patent metadata

Field	Value
Publication number	US-11041503-B2
Application number	US-201615759838-A
Country	US
Kind code	B2
Filing date	Sep 14, 2016
Priority date	Sep 15, 2015
Publication date	Jun 22, 2021
Grant date	Jun 22, 2021

Abstract

A turbomachine impeller is disclosed, which includes: a hub having a rotation axis; a shroud; a plurality of blades between the hub and the shroud; and a plurality of flow vanes, each flow vane being defined between the hub, the shroud and neighboring blades, each flow vane having a flow vane inlet and a flow vane outlet. Each flow vane extends radially inwardly from the flow vane inlet towards a radially innermost flow vane section, and from the radially innermost flow vane section to a flow vane outlet.

First claim

What is claimed is:

1. A turbomachine impeller with a rotation axis, the turbomachine impeller comprising:
a hub;
a shroud;
a plurality of blades arranged between the hub and the shroud; and
a plurality of flow vanes defined between the hub, the shroud and neighboring blades, each of the plurality of flow vanes comprising a flow vane inlet located between respective first blade edges of two neighboring blades of the plurality of blades and a flow vane outlet located between respective second blade edges of two neighboring blades of the plurality of blades and, wherein an inlet surface is defined between the first blade edges and an outlet surface is defined between the second blade edges,
wherein an inlet surface vector, orthogonal to the inlet surface and oriented outwardly with respect to each flow vane of the plurality of flow vanes, has an outwardly oriented vector component which is orthogonal to the rotation axis, and an outlet surface vector, orthogonal to the outlet surface and oriented outwardly with respect to each flow vane of the plurality of flow vanes, has an outwardly oriented vector component which is orthogonal to the rotation axis and; the hub comprises a front disk portion, a back disk portion and an intermediate hub portion extending therebetween, the intermediate hub portion defining a minimum radial dimension smaller than a respective radial dimension of the front disk portion and the back disk portion, and the plurality of blades are arranged between the front disk portion and the back disk portion.

2. The turbomachine impeller of claim 1 , wherein each of the plurality of flow vanes is configured and arranged such that fluid flow at the flow vane inlet has a radially inwardly oriented flow speed component and fluid flow in the flow vane outlet has a radially outwardly oriented flow speed component.

3. The turbomachine impeller of claim 1 , wherein each of the plurality of flow vanes extends beyond the intermediate hub portion between the front disk portion and the shroud.

4. The turbomachine impeller of claim 1 , wherein each of the plurality of flow vanes extends beyond the intermediate hub portion between the back disk portion and the shroud.

5. The turbomachine impeller of claim 1 , wherein the shroud comprises a shroud portion of a minimal radial dimension, and the respective radial dimension of the back disk portion and/or the front disk portion is not larger than the minimum radial dimension of the shroud portion.

6. The turbomachine impeller of claim 1 , wherein the first blade edges at the flow vane inlet are oriented such that projections thereof on a meridian plane of the impeller form an angle between 0° and 60° with a direction of the rotation axis, and the second blade edges at the flow vane outlet are oriented such that projections thereof on the meridian plane form an angle between 0° and 60° with the direction of the rotation axis.

7. The turbomachine impeller of claim 1 , wherein each blade of the plurality of blades extends from the flow vane inlet to the flow vane outlet.

8. The turbomachine impeller of claim 1 , wherein the plurality of blades comprise a first set of blades and a second set of blades; each blade of the first set of blades extends from a respective first edge at the flow vane inlet to a respective intermediate second edge located in an intermediate position along a respective flow vane of the plurality of flow vanes, and each blade of the second set of blades extends from a respective intermediate first edge along a respective flow vane of the plurality of flow vanes to a second edge at the flow vane outlet.

9. The turbomachine impeller of claim 1 , further comprising a first impeller section and a second impeller section torsionally and axially coupled to one another, wherein one of the first impeller section and the second impeller section comprises the flow vane inlets and the other of the first impeller section and the second impeller section comprises the flow vane outlets.

10. A turbomachine comprising: a casing; and at least a first impeller according to claim 1 supported for rotation in the casing.

11. The turbomachine of claim 10 , further comprising at least a second impeller supported for rotation in the casing and arranged in series with the first impeller.

12. The turbomachine of claim 11 , wherein further comprising a diffuser and a return channel arranged between the first impeller and the second impeller, the return channel comprising stationary return channel blades, each stationary return channel blade having a leading edge and a trailing edge, wherein flow vane inlets of the second impeller face the trailing edges of the return channel blades.

13. The turbomachine of claim 11 , wherein the first impeller and the second impeller are formed by sequentially arranged impeller sections, at least one of the impeller sections forming part of the first impeller and part of the second impeller.

14. The turbomachine impeller of claim 6 , wherein the second blade edges at the flow vane outlet are oriented such that the projections thereof on the meridian plane form an angle between 0° and 30°, with the direction of the rotation axis.

15. The turbomachine impeller of claim 6 , wherein the second blade edges at the flow vane outlet are oriented such that the projections thereof on the meridian plane form an angle between about 0° and about 45° with the direction of the rotation axis.

Assignees

• Nuovo Pignone Tecnologie Srl
• Nuovo Pignone Srl

Inventors

• Iurisci Giuseppe
• Corbo Simone

Classifications

• F04D29/284 Primary

  for compressors · CPC title

• F04D29/285

  the compressor wheel comprising a pair of rotatable bladed hub portions axially aligned and clamped together · CPC title

• F04D17/02

  having non-centrifugal stages, e.g. centripetal · CPC title

• F04D17/122

  the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage compressors · CPC title

• F04D29/30

  Vanes · CPC title