Centrifugal compressor

Patent metadata

Field	Value
Publication number	US-11073163-B2
Application number	US-201816491359-A
Country	US
Kind code	B2
Filing date	Mar 27, 2018
Priority date	Mar 31, 2017
Publication date	Jul 27, 2021
Grant date	Jul 27, 2021

Abstract

A centrifugal compressor includes impellers arranged in a plurality of stages in a direction of an axis line so that a working fluid flowing from one side inlet in the direction of the axis line is pumped outward in a radial direction, and a casing that surrounds the impellers, and that has a return channel through which the working fluid discharged from the impeller on a front stage side between the impellers adjacent to each other is guided inward in the radial direction so as to be introduced to the impeller on a rear stage side, and a plurality of return vanes disposed at an interval in a circumferential direction inside the return channel. The return vane is configured so that the thickness of a hub side in a leading edge side region is thicker than the thickness of a shroud side.

First claim

What is claimed is:

1. A centrifugal compressor comprising:
a rotating shaft that is rotatable about an axis line;
impellers arranged in a plurality of stages along the rotating shaft in an axial direction so that a working fluid flowing from one side inlet in the axial direction is pumped outward in a radial direction;
a casing that surrounds the rotating shaft and the impellers, and that has at least one return channel through which the working fluid discharged from the impeller on a front stage side between the impellers adjacent to each other is guided inward in the radial direction so as to be introduced to the impeller on a rear stage side; and
a plurality of return vanes disposed inside the at least one return channel at intervals in a circumferential direction,
wherein each return vane of the plurality of return vanes is configured so that a thickness of a hub side on one side in the axial direction in a region including a leading edge is thicker than a thickness of a shroud side on another side in the axial direction.

2. The centrifugal compressor according to claim 1 , wherein the thickness of the return vane monotonically decreases from the hub side toward the shroud side, in the region including the leading edge.

3. The centrifugal compressor according to claim 1 , wherein the region including the leading edge is 10% to 30% of a region from the leading edge toward a trailing edge in a radial dimension of the return vane.

4. The centrifugal compressor according to claim 1 , wherein the thickness is constant in a trailing edge side region of the return vane.

5. The centrifugal compressor according to claim 1 , wherein a leading edge side region of the return vane and a trailing edge side region of the return vane are smoothly and continuously connected to each other.

6. The centrifugal compressor according to claim 1 , wherein there is no thickness difference between the hub side and the shroud side, in a boundary between a leading edge side region of the return vane and a trailing edge side region of the return vane.

7. The centrifugal compressor according to claim 1 , wherein the thickness linearly decreases with constant inclination in a leading edge side region of the return vane.

Assignees

• Mitsubishi Heavy Ind Ltd

Inventors

• Saito Ryosuke

Classifications

• F04D29/444 Primary

  Bladed diffusers · CPC title

• F04D29/441

  especially adapted for elastic fluid pumps · CPC title

• F04D29/44 Primary

  Fluid-guiding means, e.g. diffusers · CPC title

• F04D17/12

  Multi-stage pumps · 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