Diffuser vane and centrifugal compressor

Patent metadata

Field	Value
Publication number	US-11035380-B2
Application number	US-201916961489-A
Country	US
Kind code	B2
Filing date	Mar 8, 2019
Priority date	Mar 9, 2018
Publication date	Jun 15, 2021
Grant date	Jun 15, 2021

Abstract

This diffuser vane ( 60 ), of which a blade height direction is aligned with an axial direction, has an airfoil shape in cross section orthogonal to the blade height direction, and comprises a body which, starting from a leading edge at the end on the radially inner side toward the radially outer side, extends toward the front side in an impeller rotating direction (R) and reaches a trailing edge at the end on the radially outer side. In the body of the diffuser vane, the turning angle of a shroud-side blade shape (S) that is the airfoil of an end face on one side in the axial direction is different from the turning angle of a hub-side blade shape (H) that is the airfoil of an end face on the other side in the axial direction. The airfoils form a transition continuously between the shroud-side blade shape and the hub-side blade shape. The turning angle of the hub-side blade shape is smaller than the turning angle of the shroud-side blade shape.

First claim

The invention claimed is:

1. A diffuser vane which is provided in a diffuser channel through which a fluid that is sucked in by an impeller rotating around an axis from one side in an axial direction and is pressurized along to a radial outer side flows, a plurality of the diffuser vanes being provided in the diffuser channel at intervals in a circumferential direction of the axis, the diffuser vane comprising:
a vane body, of which a blade height direction is aligned with the axial direction and which has an airfoil shape in cross section orthogonal to the blade height direction, extends toward a front side in a rotating direction of the impeller, starting from a leading edge at an end portion on a radial inner side toward the radial outer side and reaches a trailing edge at an end portion on the radial outer side,
wherein a turning angle of a shroud-side blade shape that is an airfoil shape of an end surface on a shroud side, which is one side in the axial direction, in the vane body is different from a turning angle of a hub-side blade shape that is an airfoil shape of an end surface on a hub side, which is the other side in the axial direction, in the vane body and the airfoil shape of the vane body forms a continuous transition between the shroud-side blade shape and the hub-side blade shape, and
wherein the turning angle of the hub-side blade shape is smaller than the turning angle of the shroud-side blade shape.

2. The diffuser vane according to claim 1 ,
wherein a chord length of the hub-side blade shape is larger than a chord length of the shroud-side blade shape.

3. The diffuser vane according to claim 2 ,
wherein a leading edge blade angle of the hub-side blade shape is smaller than a leading edge blade angle of the shroud-side blade shape.

4. The diffuser vane according to claim 1 ,
wherein, in an axial view as seen in the axial direction, a leading edge of the hub-side blade shape and a leading edge of the shroud-side blade shape are positioned on the same first virtual circle around the axis, the leading edge of the hub-side blade shape is positioned rearward of the leading edge of the shroud-side blade shape in the rotating direction of the impeller, a trailing edge of the hub-side blade shape and a trailing edge of the shroud-side blade shape are positioned on the same second virtual circle around the axis, and the trailing edge of the hub-side blade shape is positioned forward of the trailing edge of the shroud-side blade shape in the rotating direction of the impeller.

5. The diffuser vane according to claim 1 ,
wherein the vane body includes
a two-dimensional airfoil shape portion that extends toward the hub side from the end surface on the shroud side while maintaining the shroud-side blade shape, and
a three-dimensional airfoil shape portion that is connected to a hub side of the two-dimensional airfoil shape portion and transitions into the hub-side blade shape while continuously extending up to the end surface on the hub side such that the airfoil shape is changed, and

wherein the three-dimensional airfoil shape portion is formed over a range of 50% or less of a blade height of the vane body.

6. The diffuser vane according to claim 1 ,
wherein the turning angle of the shroud-side blade shape is smaller than the turning angle of the hub-side blade shape.

7. The diffuser vane according to claim 6 ,
wherein a chord length of the shroud-side blade shape is larger than a chord length of the hub-side blade shape.

8. The diffuser vane according to claim 6 ,
wherein a leading edge blade angle of the shroud-side blade shape is smaller than a leading edge blade angle of the hub-side blade shape.

9. The diffuser vane according to claim 6 ,
wherein, in an axial view as seen in the axial direction, a leading edge of the shroud-side blade shape and a leading edge of the hub-side blade shape are positioned on the same first virtual circle around the axis, the leading edge of the shroud-side blade shape is positioned rearward of the leading edge of the hub-side blade shape in the rotating direction of the impeller, a trailing edge of the shroud-side blade shape and a trailing edge of the hub-side blade shape are positioned on the same second virtual circle around the axis, and the trailing edge of the shroud-side blade shape is positioned forward of the trailing edge of the hub-side blade shape in the rotating direction of the impeller.

10. The diffuser vane according to claim 6 ,
wherein the vane body includes
a two-dimensional airfoil shape portion that extends toward the shroud side from the end surface on the hub side while maintaining the hub-side blade shape, and
a three-dimensional airfoil shape portion that is connected to a shroud side of the two-dimensional airfoil shape portion and transitions into the shroud-side blade shape while continuously extending up to the end surface on the shroud side such that the airfoil shape is changed, and

wherein the three-dimensional airfoil shape portion is formed over a range of 50% or less of a blade height of the vane body.

11. A centrifugal compressor comprising:
the impeller;
a casing that accommodates the impeller and includes the diffuser channel that extends to the radial outer side from an outlet of the impeller and a return channel that is connected to a radial outer end portion of the diffuser channel and turns toward the radial inner side; and
the diffuser vane according to claim 1 .

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• Saito Ryosuke
• Masutani Jo

Classifications

• F05D2250/52

  Outlet · CPC title

• F04D29/50

  for reversing fluid flow {(rotors for reverse action F04D29/2283)} · CPC title

• F04D29/444 Primary

  Bladed diffusers · CPC title

• F05D2250/70

  Shape · 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